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H800XP Ch5

The Hawker 750, 800XP, 850XP, and 900XP Aircraft Flexible Maintenance Schedule outlines a customizable maintenance plan for operators based on their flying schedules. It emphasizes the importance of adhering to maintenance recommendations and regulatory requirements, with specific guidelines for inspection periods, tolerances, and task numbering. The schedule includes various inspection groups and mandates that any deviations from the outlined procedures must be approved by the relevant airworthiness authority.

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0% found this document useful (0 votes)

127 views269 pages

H800XP Ch5

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nirmal

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Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)

05-00-00 (Rev A0)

TIME LIMITS/MAINTENANCE CHECKS

1. General
A. The intent of this Aircraft Flexible Maintenance Schedule (AFMS) is to provide each operator with the option of selecting the
maintenance plan best suited to their own flying schedule. The charts shown in Figure 1 and Figure 2 are used in selecting the
inspection method chosen.
NOTE: For composition of schedule and breakdown of inspections, refer to the applicable sections below.
B. It is the responsibility of the Operator, that subsequent maintenance recommendations, including airworthiness information
promulgated in Service Bulletins, Service Letters, etc. issued by the constructors and vendors, should be evaluated and, where
appropriate, should be incorporated in this Schedule by the approve amendment procedures.
C. The requirements of this Schedule shall normally be implemented at or before the periods specified. Extensions to prescribed
periods are subject to agreement with the individual Operators' Airworthiness Authority and should be made only when the
periods cannot be complied with due to circumstances which could not have been reasonably foreseen by the Operator or by
his contracted Maintenance Organization.
D. All the tasks in the Out of Phase, Component Requirements and Airworthiness Limitations Document (ALD) are calculated as
starting from the date of original certification (issuance of original standard airworthiness certificate) or from component
installation during completion. FAA or applicable regulatory required inspections and maintenance must be done in accordance
with specific regulatory requirements. All Textron Aviation, Inc. recommended inspections, maintenance and servicing shall be
based on the date of release for service following aircraft completion. These statements are not applicable to the airplane
engines or the APU, which must be maintained in accordance with their own manufacturers recommended or required
maintenance instructions.
E. The airplane must be maintained in accordance with the Maintenance Schedule based on original certification during
completion. Both a 400 Hour Detailed Walk-Around Inspection and 12 month (E Inspection) are required at the time of
completion if the difference between the date of original certification and completion is more than six months or if the airplane
has more than 50 hours total flight time.
F. Any variation to the inspection must be approved by either an FAA Flights Standards District Office (FSDO) or applicable
Airworthiness Authority.
NOTE: The requirements referred to in this Maintenance Schedule are applicable to equipment installed to Textron
Aviation, Inc. approved modifications. For airplanes with equipment installed to any other FAA approved
modifications, refer to that particular Design Authority responsible for the installation. Refer to the relevant
Vendor Publication for any Servicing/Maintenance instructions which are not specifically defined in this
schedule.
2. Periods and Tolerances
A. General Instructions
(1) Flying Times
(a) All periods quoted in the Schedule in 'flying hours' are based on flight (take-off to touch-down) times. Where, due to
airport congestion, block (chock-to-chock) times exceed flight times by an average of more than 20 percent,
corresponding adjustments should be made to the overhaul periods of selected components such as
starter/generators, hydraulic pumps and cut-out valves.
(2) Fatigue Lives and Mandatory Limitations
(a) All registered airplanes must comply with the requirements of the local Airworthiness Authority.
(b) All other life limitations classified as mandatory by the constructor/manufacturer must also be observed unless varied
by the Airworthiness Authority.
(c) The Structural Inspection frequencies quoted in this Schedule are based on a set of assumed typical operating
conditions. These assumptions take into account the experience obtained in service with the earlier variants of
airplanes together with the enhanced capabilities of the Hawker 750, Hawker 800XP, Hawker 850XP and Hawker
900XP.
(d) The projected utilization has been described in the form of Flight Plans or Mission Profiles; whilst these have been
invested with a degree of conservatism it is not possible for Textron Aviation, Inc. to make sure that they will cover
every airplane in service.
(e) Should the actual utilization differ significantly from the assumed mission profiles then due allowance must be made

Copyright © Textron Aviation Inc. Page 1 of 22

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:40:07 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-00-00 (Rev A0)

for the effects on the structural damage tolerance and fatigue characteristics and, hence, the inspection and
replacement schedules.
(f) For the purposes of compiling the Structural Inspection frequencies the typical mission profiles allow for:
• One cabin pressurization to full differential (8.55 psi).
• One full cycle of flap operation (take off and landing).
• One full undercarriage cycle including braked, full stop landing per flight where a flight is defined as a single
completed take-off and landing sequence. Touch and go landings, or rollers, are considered to be equivalent
to full stop landings for maintenance purposes.
(g) It is also assumed that the majority of flights are at altitudes of 25,000 feet and above using normal climb and descent
procedures, with an allowance for flights at lower altitudes. The rate of fatigue damage to the structure could be
greater than predicted for the assumed typical utilization if more than 30% of the flights involve cruises at altitudes
below 15,000 feet or if less than 70% of the flights involve cruises at or above 25,000 feet.
(h) The airplane is assumed to operate in a manner typical to normal business operations. The assumed block time for
average flights is 1.5 hours. Fatigue damage per flight could be increased if a significant number of flights are shorter
in duration, thereby resulting in reduced airworthiness limitations. Example of flights not typical of normal business
operations include frequent landings due to flight training, low altitude cruise, search and rescue etc.
(i) Any operator who finds that the utilization of their airplane differ from the average conditions outlined above should
contact Textron Aviation, Inc. for guidance. Refer to the Introduction, How to Get Customer Assistance.
(j) In order to fully describe an Operator's particular usage of their airplane the following information is required:
• Stage length and block time
• Climb time and speed
• Cruise time, altitude and speed
• Descent time and speed
• Stand-off time, altitude and speed
• Number of pressurizations and differential
• Number of flap operation cycles
• Number of undercarriage operation cycles
• Number of missed approaches
• Number of touch-and-go landings (rollers)
• Taxi time (pre- and post flight)
• Typical zero fuel weight
• Typical landing weight
• Percentage of total flights flown to this mission profile
NOTE: If the airplane carries out widely differing types of operation these should be divided into groups of
similar profiles each of which require the above data.
(k) Other general information to be advised as follows:
• Airplane registration
• Airplane serial number
• Airplane series
• Total flying hours and landings (including touch-and-go landings)
• Hours and landings flown in the described flights profile(s)
• Geographical disposition of operations
(3) Overhaul Periods - Radio and Radar Equipment
(a) Subject to negotiation with the Airworthiness Authority, radio and radar equipment listed in the servicing of this
Maintenance Schedule may be maintained on an "On Condition" basis.
(4) Date Marking of Equipment
(a) Equipment which is required to be date marked after inspection or re-test to comply with this Schedule, should be re-
marked with the date at which the next inspection or test is due.
B. Routine Tolerances
(1) Each routine inspection has a period for accomplishment, that period is the tolerance window. A tolerance window is
defined as the period that an inspection may be accomplished, and does not change the next due time. The tolerance

Copyright © Textron Aviation Inc. Page 2 of 22

window for each routine inspection is specified in the Inspection Periods below. If the inspection is done within the
tolerance window, the time when the inspection is next due is not changed. These windows for doing routine inspections
apply regardless of how the operator chooses to group inspections when setting an individual inspection program.
C. Structural Inspection and Out of Phase Inspection Tolerances
Periods Tolerances
1. Items controlled by flying hours:
5000 flying hours or less 10%
More than 5000 flying hours 500 flying hours
2. Items controlled by calendar time:
1 year or less 10% or 1 calendar month, whichever is the lesser
More than 1 year but not exceeding 3 years 2 calendar months
More than 3 years 3 calendar months
3. Items controlled by landings/cycles:
5000 landings/cycles or less 10%
More than 5000 landings/cycles 500 landings/cycles
4. Items controlled by more than one limit:
Calendar, Flying Hours and/or Landings/Cycles The more restrictive limit shall be applied.
3. Composition of Schedule and Task Numbering
A. Composition of Schedule
(1) The Schedule is composed of eight inspection groups, namely:
Aircraft Flexible Maintenance
Inspection Group Section Title
Schedule Section
Mandatory Life Limitations 05-11-00 Mandatory Life Limitations
Component Requirements 05-11-01 Component Requirements
Minor Inspections 05-20-01 Pre-Flight Inspection
NOTE: 05-20-02 Post-Flight Inspection
Pre-Flight and Post Flight 05-20-03 TFE731 Engine Inspection
inspections are covered in the 05-20-04 APU Inspection
Hawker 800XP Ground Handling
Checklist P/N 140-590032-0025. 05-20-05 200 Hour Lubrication
NOTE: 05-20-06 400 Hour Lubrication
Reference is also made in the Minor 05-20-07 400 Hour Detailed Walk-Around
Inspections to Engine, APU, Thrust Inspection
Reverser and Airbrake Selector
05-20-08 Airbrake Selector Lever Baulk
Level Baulk Inspections.
Inspection
Structural Inspections 05-20-09 Structural Inspections
Out of Phase Inspections 05-20-10 Out of Phase Inspections
Lubrication 05-20-11 Lubrication
05-21-00 and Subsequent 05-21-XX
Inspection "B"
Sections
05-22-00 and Subsequent 05-22-XX
Inspection "C"
Sections

Copyright © Textron Aviation Inc. Page 3 of 22

Routine Inspections 05-23-00 and Subsequent 05-23-XX

Inspection "D"
Sections
05-24-00 and Subsequent 05-24-XX
Inspection "E"
Sections
05-25-00 and Subsequent 05-25-XX
Inspection "F"
Sections
05-26-00 Inspection "G"
05-50-01 Inspections After an Overweight or
Heavy Landing
05-50-02 Inspections After a Flight in Heavy
Turbulence
05-50-03 Inspections After a Lightning Strike
05-50-04 Inspections After Misuse of Reverse
Thrust
05-50-05 Inspections After Landing Gear
Vibration
05-50-06 Inspections After a Cold Soak Below -
40 DEG C
Special Incident Inspections
05-50-07 Inspections After Landing or Aborted
Take-OFF In Deep Water Puddles,
Slush or Snow
05-50-08 Inspections After an Emergency Stop
05-50-09 Inspections After Abnormal APU
Conditions
05-50-10 Inspections After a Flap Overspeed
05-50-11 Inspections After Exposure to Volcanic
Ash
05-50-12 Inspections for Hydraulic Contamination
of Cabin Ventilation System
B. Task Numbering
(1) Each individual task within the Minor Inspections, Routine Inspections, Structural Inspections, and Out of Phase Inspections
has its own unique task number, consisting of six digits. The first two digits relate directly to the ATA chapter number and
the last four digits relat to the task, e.g., 270025 is the 25th task in Chapter 27, Flight Controls.
(2) For recording requirements, each Minor and Routine inspection period has a unique ATA Chapter 05 code number in the
Section Title.
(3) Area inspections within the routine inspections are also given a unique code number. These are 05**** numbers and will
follow the unique number allocated to the inspection, e.g.the inspection number for Inspection B3 is 050140, therefore the
area inspection number will be 050141.
(4) Page 1 of all minor and routine inspections consists of the following:
• The relevant inspection title (e.g. Inspection "B3")
• The unique code number mentioned above (e.g., 050140)
• List of Effective Pages
• Instructional Data Block
• Completion of Inspection Block
4. Inspection Periods
NOTE: If an inspection is done within the tolerance window, the time when the inspection is next due is not
changed.

Copyright © Textron Aviation Inc. Page 4 of 22

NOTE: Minor Inspections that are divided into individual task codes so they can be used for scheduling and
tracking, can be phased similar to Routine Inspections, providing each task does not exceed the inspection
period or tolerance window, (Example: If Item J. Rear Equipment Bay inspection in the 400 Hour Detailed
Walk-Around has a task code assigned then the entire "Item J" could be scheduled and completed at the
same time as "Inspection B7 - Rear Equipment Bay and Rear Fuselage Inspection").
A. General Inspection Periods
(1) The minor inspections that follow have the corresponding applicable intervals:
• 200 Hour Lubrication - 200 flying hour interval with 50 flying hour tolerance window (191 to 240)
• 400 Hour Lubrication - 400 flying hour interval with 50 flying hour tolerance window (391 to 440)
• 400 Hour Detailed Walk-Around inspection has a 400 flying hour interval with a 50 flying hour tolerance window
(391 to 440)
• Airbrake Selector Lever Baulk inspection has a 400 flying hour interval with a 50 flying hour tolerance window (391
to 440)
(2) When an inspection group is not phased:
• Inspection group "B" has a 800 flying hour interval with a 50 flying hour tolerance window (791 to 840)
• Inspection group "C" has a 1600 flying hour interval with a 100 flying hour tolerance window (1551 to 1650)
• Inspection group "D" has a 3200 flying hour interval with a 200 flying hour tolerance window (3151 to 3350)
• Inspection group "E" has a 12 month interval with a ±1 calendar month tolerance window (11 month to 13 month)
• Inspection group "F" has a 24 month interval with a ±2 calendar month tolerance window (22 month to 26 month)
• Inspection "G" has a 48 month interval with a ±2 calendar month tolerance window (46 month to 50 month)
(3) When an inspection group is phased:
(a) Inspection group "B" is divided into 12 inspections. Refer to Table 1.
• 50 flying hours (or other period selected) are allocated for the accomplishment of each inspection within
inspection "B", as indicated in Figure 1.
NOTE: These inspections MUST be completed within the allocated flying hours.
(b) Inspection group "C" is divided into 12 inspections. Refer to Table 1
• 100 flying hours (or other period selected) are allocated for the accomplishment of each inspection within
inspection "C", as indicated in Figure 1.
NOTE: These inspections MUST be completed within the allocated flying hours.
(c) Inspection group "D" is divided into 12 inspections. Refer to Table 1
• 100 flying hours (or other period selected) are allocated for the accomplishment of each inspection within
inspection "D", as indicated in Figure 1.
NOTE: These inspections MUST be completed within the allocated flying hours.
(d) Inspection group "E" is divided into 12 inspections. Refer to Table 1
• 1 calendar month is allocated for the accomplishment of each inspection within inspection "E", as indicated in
Figure 2.
NOTE: These inspections MUST be completed within the allocated flying hours.
(e) Inspection group "F" is divided into 12 inspections. Refer to Table 1
• 2 calendar months are allocated for the accomplishment of each inspection within inspection "F", as indicated
in Figure 2.
NOTE: These inspections MUST be completed within the allocated flying hours.
(f) Routine Inspection G (48 Months) is NOT divided.
(g) No deviations or extensions for the inspections within inspection groups B, C, D, E, or F are permitted from these
allocated time periods or flying hours.
(h) When a task or inspection item in an inspection is started, the airplane MUST NOT be flown until the task or
inspection item is completed and the airplane has been approved for return to service in accordance with the
requirements of the Airworthiness Authority.

Copyright © Textron Aviation Inc. Page 5 of 22

NOTE: Assure that the task or inspection item performed is signed off in such a manner that clearly
indicates when the inspection tasks are completed.
(i)
Multiple inspections (e.g. B1 through B12) may be accomplished within the same tolerance window, however each
inspection is individually tracked.
(j) Each inspection remains current, when completed, until, at a maximum, the last day or flying hour of the next allocated
period for the identical inspection.
B. There is no Routine Inspection Group A. Instead there is a 400 Hour Detailed Walk-Around inspection.
C. The breakdown of Inspection groups "B", "C", "D", "E" and "F" and the areas dealt with in the inspections are listed below.
Table 1. Inspection Groups
Inspection Title Associated Area/Function on Airplane
B1 C1 D1 E1 F1 Functional tests 1
B2 C2 D2 E2 F2 Functional tests 2
B3 C3 D3 E3 F3 Area F1 & Lubrication
B4 C4 D4 E4 F4 Area F2 & Lubrication
B5 C5 D5 E5 F5 Area F3 (Under Floor) & Lubrication
B6 C6 D6 E6 F6 Area F3 (Above Floor) & Lubrication
B7 C7 D7 E7 F7 Area F4 & Lubrication
B8 C8 D8 E8 F8 Area T1 & Lubrication
B9 C9 D9 E9 F9 Area W1 & Lubrication
B10 C10 D10 E10 F10 Area W2 & Lubrication
B11 C11 D11 E11 F11 Area M1/M2 & Lubrication
B12 C12 D12 E12 F12 Area G & Lubrication
D. Flexible Maintenance Charts (Figure 1 and Figure 2).
(1) The charts layout the inspections in hours (Figure 1) and months (Figure 2) with 12 columns for Inspection groups "B", "C",
"D", "E" and "F". Inspection "G" only has one column. For the conventional inspection method an X would be placed in
each column at the interval for that inspection, refer to Chart 1, Figure 3 for example. This would be done for each of the
seven inspections, A through G.
(2) The flexible or progressive inspection method uses the same charts with X's placed in each column at the time selected.
The X represents that time when each inspection would be done. Chart 2, Figure 4 show one example of this method.
NOTE: The charts are designed to provide maximum flexibility such as doing any individual B through F
inspection in a packaged method while doing other inspections at one time. An example of this would
be to do Inspection groups B and C in packages and all other inspections at one time.
NOTE: The charts are provided as examples of the most commonly used inspection methods.
E. The inspections contained in the Schedule are to be completed in accordance with the following instructions.
TFE-731-5BR or TFE731-50R To be completed at periods not exceeding the appropriate engine running
...
Inspections hour times as detailed in the engine manufacturers maintenance instructions.
A.P.U. To be completed at periods not exceeding the appropriate APU running hour
...
times as detailed in the APU manufacturers maintenance instructions.
200 Hour Lubrication To be completed every 200 hours as specified in the General Inspection
...
Periods above.
400 Hour Lubrication To be completed every 400 Hours as specified in the General Inspection
...
Periods above.
400 Hour Detailed Walk-Around To be completed every 400 Hours as specified in the General Inspection
...
Inspection Periods above.
Inspection Groups B, C, D, E and F ... To be completed as specified in the General Inspection Periods above.

Copyright © Textron Aviation Inc. Page 6 of 22

Inspection "G" (48 Months) ... To be completed at the time period specified.
Structural Inspections ... To be completed at the periods specified.
Out of Phase Inspections ... To be completed at the periods specified.
Special Incident Inspections ... To be completed as and when necessary.
F. Sign Off Requirements
NOTE: The sign off requirements are based upon the method of scheduled maintenance accomplishment.
(1) When an inspection group is NOT phased:
• Each inspection must be accomplished, but only the top level form requires completion.
• No inspection sign off is required.
(2) When an inspection group is phased:
• Each inspection must be signed off as a top-level inspection. Each inspection is then tracked with the appropriate
interval.
• No overall top level sign off is required.
5. Continued Airworthiness Requirements
A. Operators should institute a system for the assessment of continuing airworthiness information. This information will originate
from the Responsible Authority of the State of Manufacture in the form of Airworthiness Directives (or documents of comparable
intent) and from the constructor/manufacturer in the form of Service Bulletins, Letters, Safety Communiques, Information Leaflets
etc. resulting from In-Service Experience.
B. Operators should add items to this Schedule to cover their special installations or equipment, and to make provision for any
regulation, national or local, in force at the time.
C. Nothing in this Schedule is to be construed as absolving persons employed in the implementation of the requirements of this
Schedule from making sure that the airplane is, at all times, maintained in an airworthy condition. Any damage or defect
affecting the safety of the airplane must be rectified before the airplane flies again.
D. Compliance with the mandatory requirements of the Responsible Authority of the country of origin must be achieved.
E. When referring to all parts within the Schedule the Operator should use only those items relevant to his own airplane and
disregard all other items.
F. Continuing Airworthiness and other Service Information must be continuously evaluated by the Operator or his contracted
maintenance organization and, where necessary, appropriate action must be taken to amend the Maintenance Schedule.
6. Inspection Criteria
WARNING: When doing any of the inspections/checks contained in this maintenance schedule, obey all of the warnings
and cautions stated in the AMM associated with the system or component under Inspection/Check.
A. At each periodic inspection the depth of inspection must:
(1) Be of a degree sufficient to make sure that the items to be inspected will remain serviceable until the next higher period for
inspection becomes due.
(2) Make sure that at the time of the inspection items are free from any defects likely to affect airworthiness. The inspections
made to assure this must comply with the minimum standards set out hereunder, having regard to the material from which
the item is made and applying the appropriate standards wherever possible.
NOTE: In general, when dismantling and access is known to be required by this Schedule, this is stated
against the item concerned.
NOTE: Due to different equipment fits between airplanes and in order to achieve a satisfactory exposure of the
area/item to be inspected, it may be necessary to displace/removed other items, (e.g. electrical cables,
piping, fittings, etc.) which are not stated in the Schedule.
NOTE: Access requirements quoted are minimum requirements and further dismantling of an item, group or
assembly may be considered essential by the Chief Inspector or a Licensed Aircraft Maintenance
Engineer in order to assure airworthiness.
NOTE: Structure is to be sufficiently clean to enable an effective inspection to be done.
B. A series of standard terms are used throughout the schedule to indicate the inspection requirements. Their interpretations are
as follows:

Copyright © Textron Aviation Inc. Page 7 of 22

(1) Area Inspection: A visual Inspection of the area using the inspection criteria as detailed in the Inspection Criteria for all
items of equipment in the area relating to the trade disciplines listed and access quoted. The depth of the area inspection
is determined by the degree of access specified for the particular inspection period and the structure rendered visible at
that time.
(2) Satisfactory Condition: A general visual inspection for signs of damage, cleanliness, security of attachment and visible
connections, locking and bonding.
(3) Inspect: A more detailed visual inspection (viewed at no more than arms length away) to survey the condition of an item,
group or assembly.
(4) Detail Inspect: An intensive visual examination of a specific structural area, system, installation or assembly to detect
damage, failure or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity
deemed appropriate by the inspector. Inspection aids such as a mirror, magnifying lenses, etc. or an approved NDT
technique may be used. A 10X Lighted Magnifier should be used to inspect all instances of suspected wire damage. All
wire related conditions should be reported using the ATA spec 2200, code 97-xx-xx format. Surface cleaning and
elaborate access procedures may be required.
(5) Check: Make a comparison of a measurement of time, pressure, temperature, resistance, dimension or quantity with a
known figure for that measurement.
(6) Test: The component to be tested may be removed from the airplane or checked in situ. All the work is to be done in
accordance with the data contained in the relevant Vendor Maintenance Manual.
(7) Functional Test: Make sure, by use of test equipment if necessary, that a complete system functions correctly.
(8) Operational Test: Make sure, by use of test equipment if necessary, that a component within a system OR part of a
system operates correctly.
(9) Detailed Walk-Around Inspection: This inspection is to be a thorough visual inspection of the airplane which does not
require removal of access panels, use of specialized tools or equipment. Lighting and cleanliness is to be adequate to
detect damage, failure or irregularity. Suspect conditions requiring additional investigation are to be tread as defined in
"Detail Inspect" (Ref. Inspection Periods in this section).
C. The inspection criteria are:
(1) Metal Parts: e.g. applicable to all metal parts, bodies or casings of units in systems and in electrical, instrument and radio
installations, metal pipes, ducting, tubes, rods, levers.
(a) Inspect for:
• Cleanliness, external signs of damage, leaks, overheating or discharge. Fluid ingress. Obstruction of drainage
or vent holes or overflow pipe orifices. Correct seating and sealing of fairings and serviceability of fasteners.
Security of attachment, fasteners, connections, locking and bonding.
(b) Freedom from:
• Distortion, dents, scores, chafing, pulled or missing fasteners, rivets, bolts, screws. Signs of cracks and wear.
Separation of bond. Failure of welds and spot welds. Deterioration of protective treatment, and signs of
corrosion.
(2) Rubber, Fabric, Fibre Glass and Plastic Parts e.g. coverings, ducting, flexible pipes, flexible mountings, seals, heater
muffs, windows, etc.:
(a) Inspect for:
• Cleanliness, cracks, cuts, chafing, kinking, twisting, crushing, contraction - sufficient free length. Deterioration.
Crazing. Loss of flexibility (other than fabric covered component), overheating. Fluid soakage.
• Security of attachment (supports, packing and electrical bonding correctly positioned, serviceable and secure)
connections and locking.
(3) Control System Components:
(a) Inspect for:
• Correct alignment - no fouling. Free movement. Distortion. Signs of bowing. Scores. Chafing. Fraying.
Kinking. Signs of wear. Flattening. Cracks. Loose rivets. Deterioration of protective treatment and signs of
corrosion. Electrical bonding correctly positioned, undamaged and secure. Attachments, end connections and
locking secure.

Copyright © Textron Aviation Inc. Page 8 of 22

NOTE: Free movement should be established at extreme ranges of travel with full trim applied.
NOTE: Full travel of the rudder circuit should be confirmed with the pedals at the full forward and full
aft adjustment positions.
(4) Electrical Motors, Alternators, Generators and Actuators:
(a) Inspect for:
• Cleanliness, obvious damage, signs of overheating, signs of corrosion and security of attachments and
connections. If protective covers are required to be removed: cleanliness, scoring, pitting, brushes free in
holders, not excessively worn and correct bedding. Adequate spring tension. Overheating. Fluid ingress.
(5) Relays, Solenoids and Contactors:
(a) Inspect for:
• Cleanliness, obvious damage, signs of overheating, signs of corrosion and security of attachments and
connections. If protective covers are required to be removed: cleanliness, pitting or burning of contacts, signs
of overheating and security of contacts exposed.
(6) Markings, notices, frequency charts, compass corrector cards, warning and caution labels, placards:
(a) Inspect for:
• Legibility and security of attachment.
NOTE: Any other inspection or work requirement not covered by the above standards is specifically
written into the Schedule.
(7) Electrical Wiring, Cables and Looms:
(a) Detail Inspect for:
• Criteria contained in AMM 125/H-20 Chapter 20 - Standard Practices - Airframe, 20-10-50, Wiring
Procedures and Repair.
(8) Structural Inspection
(a) Detail inspect lap joints, butt straps, stringers, frames, bulkheads, ribs, longerons and skins for:
• Lack of adhesion of the paint or sealant. This could indicate the presence of surface corrosion under the paint
film or sealant.
• Bubbles or eruption of the paint film or sealant. This condition could indicate local pockets of corrosion and it
is important to ascertain, beyond reasonable doubt, that any bubble or eruption found is a build up of paint or
sealant and not a build up of corrosion product. If any doubt exists the bubble or eruption should be broken, the
area cleaned up and, if satisfactory, the treatment restored.
• Signs of corrosion on the edge of any member where it joins the skin. If corrosion is found the suspect area of
the joint must be cleaned of all paint. Where corrosion is confirmed and it penetrates between the faying
surfaces of the joint, the affected area must be visually examined by removing bolts or rivets to check the
extent of corrosion and to assist in repair.
• Any signs of possible cracking or corrosion is to be stripped of paint and inspected further using dye
penetrant.
(b) Non Destructive Testing (NDT)
• Where it is considered that a visual inspection is not possible due to the nature of the structure, or an
excessive amount of dismantling would be necessary, examination by X-ray or other methods of non-
destructive testing in accordance with the approved techniques is used as the inspection medium. The
techniques are contained within the Non-destructive Testing Manual.
D. Maintenance Practices and Procedures
(1) Practices and procedures necessary to complete the requirements of this Maintenance Schedule or work resulting from its
application should be, as a minimum, to the standard recommended in:
(a) The relevant Maintenance, Overhaul and Repair Manuals.
(b) The requirements of the Airworthiness Authority.
E. All Vital Points and Control Systems

Copyright © Textron Aviation Inc. Page 9 of 22

(1) Whenever inspections are made or work is undertaken on vital points, flying or engine control systems, a detailed
investigation must be made on completion of the task to make sure that all tools, rags or any other loose articles which
could impede the free movement and safe operation of the system(s) have been removed, and that the systems and
installation in the work area are clean and unobstructed.
(2) If, as a result of the application of this Schedule, any part of either the main or any associated system is dismantled,
adjusted, repaired or renewed, that part of the system(s) which has been disturbed shall be subjected to a duplicate
inspection, with free movement, range, direction and tension checks and shall be certified in accordance with the
requirements of the Airworthiness Authority.
F. Wear Limits on All Flying Control and Engine Control Cables
(1) Whenever flying control or engine control cables are required to be inspected in accordance with this Maintenance
Schedule, the following wear limits apply:
(a) Significant wear on outer wires but obviously less than 50% of individual wire cross section and with individual wires
clearly separated can be considered as acceptable.
(b) Wear on outer wires at 50% or more, usually indicated by difficulty in distinguishing individual wires, and wear area
embracing 6 consecutive wires, raise and carry forward for repeat inspection at not more than 400 flying hour
periods.
(c) Wear on outer wires at 50% or more and not more than 3 broken wires at any wear position - change within 50 flying
hours.
(d) Wear or damage in excess of the previous paragraph - change cable.
(e) Where the possibility of failed wires bunching around pulleys etc. can occur, the cable must be changed, irrespective
of the extent of any other damage.
(f) On sleeved cables, up to 10% wear of the sleeve thickness is acceptable. To clarify a difference in terminology,
"Swaged tubes" and "Sleeved cables" are physically the same thing.
G. Fuel System Contamination Checks
(1) If, as a result of the application of this Maintenance Schedule any part of the system is dismantled, adjusted, modified,
repaired or renewed, the systems shall, after completion of the work, be tested to establish the correct operation of the
system.
(2) The following checks must be made to establish that the fuel systems are free from contamination.
(a) Fuel system water drain checks are to be performed at periods not exceeding 24 hours elapsed time.
(b) The operator must be satisfied with the quality of all fuel taken on board his airplane, specially in respect of
contamination with water, and monitor the suppliers quality performance.
H. Portable Valise Type Liferafts
(1) At the appropriate Overhaul period ten percent of all liferafts installed in fleets using a system bottle and release
mechanism are to be inflated and tested. Make sure that deployment and inflation is satisfactory.
7. Schedule Format
A. Minor and Routine Inspections
(1) The requirements of the Minor and Routine Inspections are divided into airplane areas, system and component
requirements:
(a) Area Inspections
• The area inspections require a visual inspection of the area using the inspection criteria as detailed in the
Inspection Criteria for all items of equipment in the area relating to the trade disciplines listed and access
quoted. The depth of the area inspection is determined by the degree of access specified for the particular
inspection period and the structure rendered visible at that time.
(b) System and Components Requirements
• These sub-sections give the inspection and servicing requirements of specific systems and components at
the inspection period under consideration. The requirements are laid out in ATA 2200 chapter order.
• System functional tests are given at the beginning of each Inspection and are presented in ATA 2200 chapter
order. When a requirement in this Schedule refers to an AMM sub-paragraph or specific step(s) then all
relevant warnings, cautions and preparatory procedures must be observed.

Copyright © Textron Aviation Inc. Page 10 of 22

• Overhaul periods, servicing and bench tests for non-Textron Aviation manufactured components are governed
by the maintenance manuals of the respective manufacturers. Where possible, to aid Operators with their
inspection of these components, the Aircraft Maintenance Manual is used as a reference for removal and
installation.
B. Structural Inspections
(1) The Structural Inspections are also divided into airplane areas, with each area containing the inspection requirements and
"Not exceed" periods for specific structural parts. The degree of access required is stipulated for each inspection
requirement.
C. Out of Phase Inspections
(1) The Out of Phase Inspections are presented in ATA 2200 chapter order. The "Not Exceed" period for the inspection(s) are
stated in the individual tasks.
D. Special Incident Inspections
(1) This Part contains the special inspections considered necessary if the airplane has been subjected to abnormal stresses
or climatic conditions in flights, or during landing.
E. Panel Location Charts
(1) The charts contained within the Panel Location Charts section illustrate the location of panels which may be required to be
removed or opened during airplane servicing. Refer to the applicable AMM, Chapter 06-40-00, Panel Location Charts -
Description and Operation.
F. Lubrication
(1) Details of routine lubrication and types of lubricants used are detailed in the text and illustrations contained within this
section. The AMM references of the lubricants used for general lubrication, together with a system of codes denoting
lubrication periods, are tabulated in the Introduction at the beginning of the section. The AMM references of special
purpose lubricants used for specific applications are included in the relevant text and illustrations.
G. Component Requirements
(1) Listed within this part are components or assemblies which are subject to hard-time overhaul periods, bench tests or
replacement out of phase with the airplane servicing periods. The consolidated list is given under system headings in ATA
2200 chapter order, and includes Part Nos. and the names of the manufacturers.
(2) Where the part number of a component is followed by an asterisk(s) (e.g. 42022-**) this indicates that the requirement is
applicable to all variants.
H. Mandatory Life Limitations
(1) The components and assemblies subject to Mandatory Life Limitations are now contained in the Airworthiness Limitations
Document Reference No. CJE-HPA-C-GEN-AW1667.
8. Abbreviations, Terms and Definitions
A. All significant terms and abbreviations used within the Schedule are defined below or, in the absence of formal definitions,
those quoted in the World Airlines Technical Operations Glossary are used.
AMM ... Aircraft Maintenance Manual
B/Chk ... Bench check.
CMM ... Component Maintenance Manual
DTD ... Directorate of Technical Development (UK) specification
ICAO ... International Civil Aviation Organization
ISB ... Inspection Service Bulletin
LMM ... Light Maintenance Manual
MM ... Maintenance Manual
MIL ... Military (ICAO, US) specification
NDT ... Non-destructive Test
O/H ... Overhaul

Copyright © Textron Aviation Inc. Page 11 of 22

Repl. ... Replace

SB ... Service Bulletin
9. Samples of Flexible Maintenance Schedule Charts
A. Chart 1 (Figure 3, Sheet 1 and Sheet 2).
(1) This chart shows conventional servicing when ALL of the Inspection requirements are done at one time, e.g.
• Inspection B (B1 to B12 inclusive) done at 800 Hour, 1600 Hour, 2400 Hour etc.
• Inspection C (C1 to C12 inclusive) done at 1600 Hour, 3200 Hour, 4800 Hour etc.
• Inspection D (D1 to D12 inclusive) done at 3200 Hour, 6400 Hour, 9600 Hour etc.
• Inspection E (E1 to E12 inclusive) done at 12 Months, 24 Months, 36 Months, 48 Months etc.
• Inspection F (F1 to F12 inclusive) done at 24 Months, 48 Months, etc.
B. Chart 2 (Figure 4, Sheet 1, Sheet 2, Sheet 3, and Sheet 4).
(1) This chart shows one suggested flexible method of staggering the sub-inspections.
10. Additional Requirements Introduced by Revision Action
A. Unless otherwise directed by the relevant Letter of Transmittal, or Service Bulletin action, additional requirements introduced
into the Schedule need not be added into an airplanes existing cycle of maintenance until the next period at which the
requirement becomes due.

Copyright © Textron Aviation Inc. Page 12 of 22

Figure 1 : Sheet 1 : Flexible Maintenance Charts - Hours

Copyright © Textron Aviation Inc. Page 13 of 22

Figure 1 : Sheet 2 : Flexible Maintenance Charts - Hours

Copyright © Textron Aviation Inc. Page 14 of 22

Figure 2 : Sheet 1 : Flexible Maintenance Charts - Months

Copyright © Textron Aviation Inc. Page 15 of 22

Figure 2 : Sheet 2 : Flexible Maintenance Charts - Months

Copyright © Textron Aviation Inc. Page 16 of 22

Figure 3 : Sheet 1 : Flexible Maintenance - Conventional Servicing (Hours)

Copyright © Textron Aviation Inc. Page 17 of 22

Figure 3 : Sheet 2 : Flexible Maintenance - Conventional Servicing (Hours)

Copyright © Textron Aviation Inc. Page 18 of 22

Figure 4 : Sheet 1 : Flexible Maintenance - Flexible Servicing (Hours)

Copyright © Textron Aviation Inc. Page 19 of 22

Figure 4 : Sheet 2 : Flexible Maintenance - Flexible Servicing (Hours)

Copyright © Textron Aviation Inc. Page 20 of 22

Figure 4 : Sheet 3 : Flexible Maintenance - Flexible Servicing (Hours)

Copyright © Textron Aviation Inc. Page 21 of 22

Figure 4 : Sheet 4 : Flexible Maintenance - Flexible Servicing (Hours)

Copyright © Textron Aviation Inc. Page 22 of 22

ATA TASK CODES

1. General
NOTE: Page count shown in any List of Effective Pages table is for the paper copy only. The actual page count may
differ when printed from this electronic version.
List of Effective Pages
Pages 1 thru 75
2. ATA Task Codes
ATA Task Code Description Inspection
Chapter 05 - Time Limits/Maintenance Checks
NOTE:
Chapter 05 Numbers are allocated for Inspection Numbers and Area Inspections. As these are not specific to any
airplane system the numbers have not been listed.
Chapter 05 numbers are allocated to specific tasks/inspections are listed.
Left Nose and Fuselage. 400 Hour Detailed Walk-
050772
Around Inspection
Nose Landing Gear Bay. 400 Hour Detailed Walk-
050773
Around Inspection
050774 Right Nose and Fuselage. 400 Hour Detailed Walk-
Around Inspection
Right Wing. 400 Hour Detailed Walk-
050775
Around Inspection
Right Main Landing Gear. 400 Hour Detailed Walk-
050776
Around Inspection
Right Engine and Nacelle. 400 Hour Detailed Walk-
050777
Around Inspection
Aft Fuselage - Right Side. 400 Hour Detailed Walk-
050778
Around Inspection
Empennage (Tail Section). 400 Hour Detailed Walk-
050779
Around Inspection
External Baggage Unit (750 Airplanes) - Task transferred to 050779. 400 Hour Detailed Walk-
050780
Around Inspection
Aft Fuselage - Left Side. 400 Hour Detailed Walk-
050781
Around Inspection
Rear Equipment Bay. 400 Hour Detailed Walk-
050782
Around Inspection
Left Engine and Nacelle. 400 Hour Detailed Walk-
050783
Around Inspection
Left Main Landing Gear and Center Keel. 400 Hour Detailed Walk-
050784
Around Inspection
Left Wing. 400 Hour Detailed Walk-
050785
Around Inspection
Flight Compartment. 400 Hour Detailed Walk-
050786
Around Inspection
Vestibule, Passenger Cabin and Toilet Compartment. 400 Hour Detailed Walk-
050787
Around Inspection

Copyright © Textron Aviation Inc. Page 1 of 48

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:40:26 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-10-01 (Rev A0)

Final Items. 400 Hour Detailed Walk-

050788
Around Inspection
Chapter 12 - Servicing
Do any 200 hour lubrication requirements for ALL Area's, refer to Chapter 5,
120001 200 Hour Lubrication
Lubrication.
120002 Task deleted. A1
Do any 400 hour lubrication requirements for Area F1, refer to Chapter 5,
120003 400 Hour Lubrication
Lubrication.
Do any 400 hour lubrication requirements for Area T1, refer to Chapter 5,
120004 400 Hour Lubrication
Lubrication.
120005 Task deleted. A3
120006 Task deleted. A4
Do any 400 hour lubrication requirements for Area W1/W2, refer to Chapter 5,
120007 400 Hour Lubrication
Lubrication.
120008 Task deleted. A6
120009 Task deleted (requirement transferred to 1600 Hour Inspection). B3
120010 Task deleted. B4
120011 Task deleted. B5
Do any 800 hour lubrication requirements for Area F3, refer to Chapter 5,
120012 B6
Lubrication.
Do any 800 hour lubrication requirements for Area F4, refer to Chapter 5,
120013 B7
Lubrication.
120014 Task deleted. B8
Do any 800 hour lubrication requirements for Area W1, refer to Chapter 5,
120015 B9
Lubrication.
Do any 800 hour lubrication requirements for Area W2, refer to Chapter 5,
120016 B10
Lubrication.
120017 Task deleted. B11
Do any 800 hour lubrication requirements for Area G, refer to Chapter 5,
120018 B12
Lubrication.
Do any 1600 hour lubrication requirements for Area F1, refer to Chapter 5,
120019 C3
Lubrication.
Do any 1600 hour lubrication requirements for Area F2, refer to Chapter 5,
120020 C4
Lubrication.
Do any 1600 hour lubrication requirements for Area F3, refer to Chapter 5,
120021 C5
Lubrication.
Do any 1600 hour lubrication requirements for Area F3, refer to Chapter 5,
120022 C6
Lubrication.
Do any 1600 hour lubrication requirements for Area F4, refer to Chapter 5,
120023 C7
Lubrication.
Do any 1600 hour lubrication requirements for Area T1, refer to Chapter 5,
120024 C8
Lubrication.
Do any 1600 hour lubrication requirements for Area W1, refer to Chapter 5,
120025 C9
Lubrication.

Copyright © Textron Aviation Inc. Page 2 of 48

Do any 1600 hour lubrication requirements for Area W2, refer to Chapter 5,
120026 C10
Lubrication.
Transferred to Out of Phase Inspections Task # 760004, refer to Chapter 5,
120027 C11
Lubrication.
120028 Task deleted. C12
120029 Task deleted. D3
Do any 3200 hour lubrication requirements for Area F2, refer to Chapter 5,
120030 D4
Lubrication.
120031 Task deleted. D5
120032 Task deleted. D6
120033 Task deleted. D7
120034 Task deleted. D8
120035 Task deleted. D9
120036 Task deleted. D10
120037 Task deleted. D11
120038 Task deleted. D12
120039 Task deleted. E3
120040 Task deleted. E4
120041 Task deleted. E5
120042 Task deleted. E6
120043 Task deleted. E7
120044 Task deleted. E8
120045 Task deleted. E9
120046 Task deleted. E10
120047 Task deleted. E11
120048 Task deleted. E12
Do any 24 month lubrication requirements for Area F1, refer to Chapter 5,
120049 F3
Lubrication.
Do any 24 month lubrication requirements for Area F2, refer to Chapter 5,
120050 F4
Lubrication.
120051 Task deleted. F5
120052 Task deleted. F6
120053 Task deleted. F7
120054 Task deleted. F8
120055 Task deleted. F9
120056 Task deleted. F10
120057 Task deleted. F11
120058 Task deleted. F12
120059 Task deleted (Transferred to Lubrication, 1600 Hour). G
120060 Task deleted, covered by tasks 120003, 120004 and 120007. 400 Hour Lubrication
Chapter 20 - Standard Practices - Airframe

Copyright © Textron Aviation Inc. Page 3 of 48

Control surfaces.
200001 B1
• Do a bonding check (Ref. 125/H-20, 20-10-5016).
Refuel point earthing studs (3 off).
200002 • Do a function test for bonding resistance to the local structure (Ref. B1
125/H-20, 20-10- 5016).
Radio racking, electrical-bonding.
200003 • Do a bonding check with all the equipment fitted (Ref. 125/H-20, 20-10- G
5016).
Chapter 21 - Air Conditioning
210001 Task deleted. Covered by Inspection B1 task 210003. A1
Airplanes without the digital pressurization control system Mod. 25G726A/C or
Mod. 25G726B/C:
Ram air valve and dump valve.
• Do a check/test (Ref. AMM 21-10-155, 201, select 750, 800XP,
210002 800XP/850XP Pro Line 21 or 900XP). B1
Airplanes with the digital pressurization control system Mod. 25G726A/C
or Mod. 25G726B/C:
Ram air valve and dump valve.
• Do a check/test (Ref. AMM 21-10-155, 201, select 750 or 900XP).
Environmental control system.
• Do a function test of the Pressure regulator and shut off valve (PRSOV)
(Ref. AMM 21- 10-76, 501, select 750, 800XP, 800XP/850XP Pro Line
210003 B1
21 or 900XP).
• Do a bench check of the PRSOV Overpressure switch (Ref. AMM 21-10-
78, 201, select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
Airplanes without the digital pressurization control system Mod. 25G726A/C or
Mod. 25G726B/C:
210004 Manual cabin altitude control valve. B4
• Make sure of full and free movement.
Cooling turbine exhaust duct drain. Make sure the drain is free from
210005 B7
blockages.
Every 400 Hours. Water separator.
• Inspect for satisfactory condition (Ref. AMM 21-10-95, 601, select 750,
210006 800XP/850XP Pro Line 21 or 900XP). Out of Phase
NOTE:
Operators may adjust this time based on servicing experience.
Every 400 hours.
Water separator. Inspect the following items are free from blockages and
obstructions (Ref. AMM 21-10-95, 601, select 750, 800XP/850XP Pro Line 21
or 900XP):
• Water separator water drain.
210007 Out of Phase
• Water separator water drain pipeline.
• HP line to water injector nozzle.
• Water injector nozzle.
NOTE:
Operators may adjust this time based on servicing experience.

Copyright © Textron Aviation Inc. Page 4 of 48

Airplanes without the digital pressurization control system Mod. 25G726A/C or

Mod. 25G726B/C:
Cabin pressure outflow/safety valve controller.
210008 C4
• Visually inspect and make sure that the cabin air sense port screen is
clear.

Airplanes without the digital pressurization control system Mod. 25G726A/C or

Mod. 25G726B/C:
210009 Pressurization control venturi screen. C6
• Make sure screen is clean.
Airplanes without the digital pressurization control system Mod. 25G726A/C or
Mod. 25G726B/C: Pressure regulators.
210010 G
• Clean the filter screens (Ref. AMM 21-30-55, select 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
Airplanes without the digital pressurization control system Mod. 25G726A/C or
Mod. 25G726B/C:
Outflow/safety valves.
• Clean the outflow valve poppet valve and seat (Ref. AMM 21-30-25, 701,
select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
• If required, clean exterior of the outflow valve using a cloth or sponge
soaked in cleaning fluid (Ref. AMM 21-30-25, 701, select 750, 800XP,
210011 G
800XP/850XP Pro Line 21 or 900XP).
• Check that the orifice in the cabin air filter connection is free of
obstruction.
• Check that the cabin air sense ports are free and clear of any
obstruction.
• Functionally test operation of valves (Ref. AMM 21-30-25, 501, select
750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
Air conditioning ducts. Inspect for satisfactory condition (Ref. AMM 21-10-
210012 C7
15).
Ram air duct. Inspect, as far as is possible, for cracks in the vicinity of the take-
210013 C7
off duct to the shut-off valve, and around the cut-out for the inward relief door.
Airplanes without the digital pressurization control system Mod. 25G726A/C or
210014 Mod. 25G726B/C: Cabin air filters (pressurization system). G
• Inspect.
Silencer duct and soundproofing (Ref. AMM 21-10-15).
• Inspect the silencer duct internally for deterioration of the soundproofing
210015 D7
material and of the perforated inner retaining duct.
• Inspect for internal and external corrosion.
System overheat temperature switch. Do a bench check (Ref. AMM 21-60-
210016 D7
85).
Baggage pannier heating system inlet and outlet valve (if fitted) OR
External baggage unit (EBU) inlet valve (750 airplanes ONLY).
Make sure of the correct operation under normal and 'smoke detected'
210017 conditions (Ref. AMM 21-10-205). D7
NOTE:
This test is only applicable to airplanes with a baggage pannier in place
of the ventral fuel tank OR 750 airplanes with external baggage unit.

Copyright © Textron Aviation Inc. Page 5 of 48

Altitude switch, cabin depressurization warning.

• Do a functional test (Ref. AMM 21-30-70, 201, select 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
210018 G
NOTE:
Mod. 259747C (SB 21-3136) introduces a second Altitude Warning
Switch (set to 14,000 ft.) to permit operation at high altitude airfields.
Cabin supply non-return valve.
210019 • Inspect, paying particular attention to the security of the carrier D7
arm/butterfly flap rivets (Ref. AMM 21-10-107).
Electrically actuated auxiliary heat valve.
• Do a functional test (Ref. AMM 21-60-105).
210020 C1
NOTE:
This test may be done without engine bleed air.
APU supply, auxiliary supply, ram air supply and main engine supply.
Check/non-return valves.
210021 • Remove and inspect. D7
• Make sure that the axial and radial play in the flappers is not excessive
(0.025 in. maximum for AiResearch valves).
After 50 flying hours but not more than 300 flying hours from airplane build OR
after disturbance of ducts or rubber sleeves.
Air conditioning ducts.
• Check the duct joint clamp bolts for the correct torque loading:
210022 Ref. AMM 21-10-15, 201, select 750, 800XP, 800XP/850XP Pro Line 21 or Out of Phase
900XP.
Ref. AMM 21-10-87, 201, select 750, 800XP, 800XP/850XP Pro Line 21 or
900XP.
Ref. AMM 21-10-95, 401, select 750, 800XP, 800XP/850XP Pro Line 21 or
900XP.
210023 Task deleted, covered by AMM.
Low Limit Temperature Control Valve Filter (if installed).
• Clean or replace (Ref. AMM 21-60-61, 201).
210024 NOTE: B7
This task is only applicable to airplanes with a Honeywell GTCP36-150W
APU, installed to STC ST00459NY.
PATS APU GTCP36-150W.
APU bleed air system.
• Inspect for air leaks at clamped joints and pipes.
210025 C7
• Inspect load control valve for cracks, dents, deformation or other damage
that may affect the performance of the valve.
• Remove and inspect the check valve. Repair as required.
Airplanes with the digital pressurization control system Mod. 25G726A/C or
Mod. 25G726B/C:
210026 Digital pressurization cabin air filters. C6
• Replace both of the filter element (Ref. AMM 21-31-20, 301, select 750
or 900XP).

Copyright © Textron Aviation Inc. Page 6 of 48

Airplanes with the digital pressurization control system Mod. 25G726A/C or

Mod. 25G726B/C:
Electropneumatic outflow valve (EOV).
210027 C6
• Clean each EOV poppet valve seat (Ref. AMM 21-31-10, 701, select
750 or 900XP).

Airplanes with the digital pressurization control system Mod. 25G726A/C or

Mod. 25G726B/C:
210028 Electropneumatic outflow valve (EOV) pressure limiter. D6
• Do each EOV pressure limiter test (Ref. AMM 21-31-00, 501, select 750
or 900XP).
Every 15,000 Hours, Airplanes with the digital pressurization control system
Mod. 25G726A/C or Mod. 25G726B/C:
Electropneumatic Outflow Valves.
210029 Out of Phase
• Do an inspection/check for the smooth operation of the manual
electropneumatic outflow valve (Ref. AMM 21-31-00, 601, select 750 or
900XP).
Chapter 22 - Autopilot
NOTE:
No Chapter 22 tasks at this time.
Chapter 23 - Communications
230001 Task deleted. F1
Chapter 24 - Electrical Power
Between 200 and 400 Hours.
Starter/generators.
• Remove and inspect (Ref. AMM 24-30-21, 401, select 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
• Do a brush wear check (Ref. AMM 24-30-21, 601, select 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
240001 Out of Phase
• Inspect cooling fan.
• Inspect splines for wear (Ref. AMM 24-30-21, 401, select 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
• Inspect engine drive for wear.
• Install starter/generator (Ref. AMM 24-30-21. 401, select 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
No.1 and No.2 main static inverters. Operate inverters and make sure, by
240002 B1
feel of hand, of a positive airflow output from the inverter cooling fans.
240003 Frequency wild A.C. system. Do a function test (Ref. AMM 24-22-02). D1
Busbar contactor control.
• Set the bustie switch to CLOSE.
• Trip the LH generator off-line.
• Make sure all d.c. busbars are energized.
240004 C1
• Reset the LH generator.
• Trip the RH generator off-line.
• Make sure all d.c. busbars are energized.
• Reset the RH generator.
APU generator overheat indication circuit. Function test (Ref. AMM 24-36-
240005 D1
03, Turbomach APU Installation only).

Copyright © Textron Aviation Inc. Page 7 of 48

D.C. busbar protection/voltage sensing unit. Check the trip voltage datums
240006 (Ref. AMM 24-30-142, 501, select 750, 800XP, 800XP/850XP Pro Line 21 or D6
900XP).
Ground power overvoltage sensor (if fitted). Bench check the trip voltage
240007 D7
datum (Ref. AMM 24-30-146).
240008 Task deleted. D7
D.C. generating system. Do a function test of the emergency contactor control
240009 (Ref. AMM 24-30-01, 501, select 750, 800XP, 800XP/850XP Pro Line 21 or B1
900XP).
PE, PS1 and PS2 busbar feeder cables below Panel DA.
• Inspect for discoloration due to overheating.
240010 C6
• Torque tighten the connections (Ref. AMM 24-01-00, select 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
Busbar PE, PS1 and PS2 feeder fuses. Do a functional test of the fuses:
For the UAM 100 Busbar Feeder Fuse Functional Test, ref. AMM 24-01-00, 201
240011 - Electrical Power Maintenance Practices. C7
• F31 and F32 on panel ZL.
• F13, F14, F23 and F24 on panel GA.
240012 This inspection item was combined with 240011. This item is deleted. C7
All circuit breakers. Function test for correct mechanical operation. Do two
240013 D1
manual switching cycles for this test.
Main generator control unit (GCU). Do a function test of the overvoltage
240014 D1
protection circuit (Ref. AMM 24-30-07).
APU Generator control unit (GCU). Do a function test of the overvoltage
240015 D1
protection circuit (Ref. AMM 24-36-03).
Electrical cable pressure bungs (in the forward pressure bulkhead).
240016 D3
• Inspect for correct location in their housings (Ref. AMM 24-01-00).
Earth stations *16, *17, *18 and *19.
• Inspect. Look for signs of arcing.
• Do an impedance check (Ref. AMM 24-01-00, select 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
240017 G
NOTE:
It is not necessary to do this task until the second 48 month inspection
(96 months). Do the task at every 48 month inspection from that time
onwards.
Electrical cable pressure bungs (in the read pressure bulkhead).
240018 D7
Inspect for correct location in their housings (Ref. AMM 24-01-00).
240019 Task deleted, covered by AMM. Out of Phase
240020 Task deleted, covered by AMM. Out of Phase
240021 Requirement deleted. Out of Phase
240022 Task deleted, covered by AMM. Out of Phase
240023 Requirement deleted. Out of Phase

Copyright © Textron Aviation Inc. Page 8 of 48

Every 500 APU running hours.

APU starter/generator.
• Remove (Ref. AMM 24-30-21, 401, select 750, 800XP, 800XP/850XP
Pro Line 21 or 900XP).
• Check the brush wear (Ref. AMM 24-30-21, 601, select 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
240024 • Inspect the cooling fan. Out of Phase
• Inspect the splines for wear (Ref. AMM 24-30-21, 401, select 750,
800XP, 800XP/850XP Pro Line 21 or 900XP).
• Inspect the engine drive for wear.
• Install the APU starter/generator (Ref. AMM 24-30-21, 401, select 750,
800XP, 800XP/850XP Pro Line 21 or 900XP).
Electrical cable pressure bungs (in the fuselage keel at the front spar).
240025 D5
Inspect for correct location in their housings (Ref. AMM 24-01-00).
Electrical cable pressure bungs (in the forward pressure bulkhead).
240026 D4
Inspect for correct location in their housings (Ref. AMM 24-01-00).
Main batteries.
Rebling Plastics "Quick Disconnect" battery connectors, P/N's 7007, 7013,
7016 and 7017 (if fitted):
• 750 airplanes, Check (Ref. AMM 24-30-151, 401).
240027 D7
• 800XP airplanes, Check (Ref. AMM 24-30-104, 401 or 24-30-151, 401).
• 800XP/850XP Pro Line 21 airplanes, Check (Ref. AMM 24-30-151,
401).
• 900XP airplanes, Check (Ref. AMM 24-30-151, 401).
Every 400 Hours.
Panel GG and Terminal block M.
• Do a visual inspection for deformation, displacement, discoloration and
heat distress (Ref. AMM 24-01-00, 201 select 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
NOTE:
240028 This task is applicable to series 750 airplanes HB-1 thru HB-27, 800XP, Out of Phase
800XP/850XP Pro Line 21 airplanes 258266 thru 258982 and 900XP
airplanes HA-0001 thru HA-0092 and HA-0094.
750 airplanes HB-28 and After, do not use terminal block M (Mod.
25G484B). 850XP Pro Line 21 airplanes 258983 and After, do not use
terminal block M (Mod. 25G484C). 900XP airplanes HA-0093, HA-0095
and After, do not use terminal block M (Mod. 25G484A).
Do a visual inspection for discoloration and signs of distress (Ref. AMM 24-01-
240029 00, 201 select, 750, 800XP, 800XP/850XP Pro Line 21 or 900XP). Inspect DA- E6
Panel for proper mounting of components.
Every 200 Hours.
Cabin Inverter (115 VAC) system (if fitted).
240030 Out of Phase
• Do a function test of the Cabin Inverter (115 VAC) system (Ref. MMA 24-
20-10, 201).

Copyright © Textron Aviation Inc. Page 9 of 48

Between 200 and 400 Hours.

AC Generator Pad (900XP Only):
• Remove the AC Generator (Ref. AMM 24-22-21, 401).
240031 • Inspect AC Generator QAD pad for deformation, cracks or other Out of Phase
damage.
• Install the AC Generator (Ref. AMM 24-22-21, 401).
Inspection completed at.......................... Hrs. Date.....................
Chapter 25 - Equipment & Furnishings
250001 Task deleted. A1
250002 Task deleted. A3
3rd crew members seat (if fitted).
• Make sure that the seat stowing action is satisfactory.
250003 • Make sure of the correct operation and satisfactory condition. B6
NOTE:
To be done at this inspection or at a period conforming to the
requirements of the local regulatory authority.
250004 Task deleted. E4
Emergency packs (if fitted). Inspect contents for condition and make sure
250005 E6
expiry dates are valid.
First aid kits (if fitted). Make sure expiry date is valid and make sure seal is
250006 E6
intact.
Crew Seats.
250007 • Do an operational check (Ref. CMM 25-11-24, 501 (Check 1)) or (CMM B4
25-11-27, 501 (Check 1)).
Crew Seats.
• Remove the crew seats (Ref. AMM 25-10-14, 401).
250008 • Do a detailed check (Ref. CMM 25-11-24, 501 (Check 2)) or (Ref. CMM D4
25-11-67, 501(Check 2)).
• Install the crew seats (Ref. AMM 25-10-14, 401).
Chapter 26 - Fire Protection
Airplanes with Fire Extinguisher Pressure Gauges ONLY. Fire
extinguishers, main engines.
• Check the pressure gauge. Make sure the reading is correct, refer to the
pressure/temperature chart.
260001 E1
• Do a functional test (Ref. AMM 26-20-00).
NOTE:
For airplanes without Fire Extinguisher Pressure gauges refer to
Inspection E7 task 260005.
Rear equipment bay overheat detection system. Do a functional test (Ref.
260002 AMM 26-10-00, 201, select 750, 800XP, 800XP/850XP Pro Line 21 or B1
900XP).
Portable fire extinguisher.
• Check for correct weight or if gauge is fitted, make sure the needle is in
260003 E4
the green sector.
• Inspect and look for signs of leaks or discharge.

Copyright © Textron Aviation Inc. Page 10 of 48

Portable fire extinguisher (if fitted).

• Check for correct weight or if gauge is fitted, make sure the needle is in
260004 E6
the green sector.
• Inspect and look for signs of leaks or discharge.
For airplanes without Fire Extinguisher Pressure Gauges ONLY. Fire
extinguishers, main engines.
• Remove (Ref. AMM 26-20-12).
• Inspect.
• Check weight (Ref. AMM 26-20-12).
260005 E7
• Install (Ref. AMM 26-20-12).
• Do a functional test (Ref. AMM 26-20-00).
NOTE:
For airplanes with Fire Extinguisher Pressure Gauges refer to Inspection
E1, task 260001.
260006 Requirement deleted. Covered by Inspection E1 task # 260001. E7
Fire extinguisher, APU (Solar T-40 (Turbomach ONLY)).
• Inspect.
260007 • Check pressure gauge (Ref. AMM 26-20-54). E7
• Check Hydrostatic and Cartridge due dates.
• Do a functional test (Ref. AMM 26-20-00).
Every 6 Months.
Smoke Detection System (if fitted).
• Do a function test:
260008 Out of Phase
750 airplanes (Ref. MMA 26-11-00, 501). 800XP and 800XP Pro Line 21
airplanes (Ref. MMA 26-11-00, 501). 900XP airplanes (Ref. MMA 26-11-00,
501).
Every 6 Months.
Baggage Pannier OR External Baggage Unit Smoke Detection System (if
fitted).
260009 • Do a function test (Ref. AMM 26-10-52, 201, select 750 or 800XP). Out of Phase
NOTE:
This test is only applicable to airplanes with a baggage pannier in place
of the ventral fuel tank OR 750 airplanes with an external baggage unit.
PATS APU GTCP36-150W.
APU fire extinguisher.
• Inspect.
260010 E7
• Check pressure gauge (Meggitt CMM 26-20-02).
• Check Hydrostatic and Cartridge due dates.
• Do a functional test (Ref. AMM 49-61-20, 501).
External Baggage Unit Fire Extinguisher.
• Inspect.
• Check Pressure gauge.
260011 • Check cartridge expiry date. E7
• Do a functional test (Ref. AMM 26-20-60, 201).
NOTE:
This task is ONLY applicable to 750 airplanes.
Chapter 27 - Flight Controls

Copyright © Textron Aviation Inc. Page 11 of 48

Every 400 hours.

Airbrake selector level baulk.
• Do an operational test (Ref. AMM 27-61-03, 501).
NOTE:
This task is ONLY applicable to airplanes with Mod. 25F743A or Mod.
270001 25F743C embodied and is applicable to Canadian registered airplanes Airbrake Selector Level
only. Baulk Inspection
• Mod. 25F743A (SB 27-3150) introduces an airbrake selector lever
baulk to 800XP airplanes.
• Mod. 25F743C (SB 27-3554) introduces an airbrake selector lever
baulk to 800XP Pro Line 21 airplanes.
Flap vane inner. With the flaps lowered, inspect the left outer attachment
270002 C9
bracket for cracking and for security of attachment to the flap leading edge.
270003 Flap screwjacks. Inspect screw threads for satisfactory condition. B9
Stall warning and identification system
• Do a functional test of the stall warning and identification system (Ref.
AMM 27-33-00).
270004 • Do an angle verification check (Ref. AMM 27-33-00). B2
• Do an electrical zero check (Ref. AMM 27-33-00).
NOTE:
The electrical zero check is only applicable to airplanes with Mod.
25G206A or Mod. 25G206B.
270005 Task deleted. B2
270006 Task deleted. B2
270007 Task deleted. B2
Rudder bias strut heater muffs.
270008 • Do a functional test of the rudder bias strut heater muff (Ref. AMM 27-20- B2
00).
Stall detector unit (third channel). Do a function test:
• 800XP airplanes (Ref. AMM 27-33-14).
• 800XP/850XP Pro Line 21 airplanes (Ref. AMM 27-33-14).
270009 NOTE: B2
This task is only applicable to 800XP and 800XP/850XP Pro Line 21
airplanes Pre-Mod. 25G206A.
OR
Pre-Mod. 25G206A and 25G206B.
270010 Task deleted.
Gust lock, ailerons and elevators.
• Inspect.
• Make sure that the bush in the mounting bracket is lightly lubricated and
free from burrs or scores.
270011 B4
• With the unit in the operated and locked position but without the
engagement of the claw spigots in the control column bushes, check for
positive spring pressure on the claws and for initial resistance to
movement when releasing the knurled locking ring.

Copyright © Textron Aviation Inc. Page 12 of 48

Rudder trim tab and anti-servo tab.

• Check the free movement (backlash) at the trailing edges of the tabs
(Ref. AMM 27-20- 00, 501).
• While the connecting rods are disconnected check the rear rod-end
bearings for smooth operation.
270012 B8
• Detail inspect the connecting rod attachment lugs on the tabs for cracks
using a X 10 magnifier.
NOTE:
Do not remove the protective coating unless a defect, or suspected
defect, is found.
Elevators and trim tabs.
• Check the free movement (backlash) at the trailing edges of the tabs
(Ref. AMM 27-30- 00, 501).
• While the connecting rods are disconnected check the rear rod-end
bearings for smooth operation.
270013 B8
• Detail inspect the connecting rod attachment lugs on the trim tabs for
cracks, using a X 10 magnifier.
NOTE:
Do not remove the protective coating unless a defect, or suspected
defect, is found.
Rudder and elevators primary surfaces.
270014 Make sure of full and free movement from stop to stop. B8

Aileron primary surfaces.

270015 Make sure of full and free movement from stop to stop and that all accessible B9
aileron pulleys rotate freely.
Aileron trim and servo tabs.
• Check the free movement (backlash) at the trailing edges of the tabs
(Ref. AMM 27-10- 00, 501).
• While the connecting rods are disconnected inspect the rear rod-end
bearings for smooth operation.
270016 B9
• Detail inspect the connecting rod attachment lugs on the tabs for cracks
using a X 10 magnifier.
NOTE:
Do not remove the protective finish unless a defect, or a suspected
defect is found.
Flap Screwjack and reduction gearbox.
270017 B9
Check the gearbox fluid level (Ref. AMM 27-50-141).
Flap synchronization system control cables.
270018 • Inspect for fraying, particularly in the vicinity of the pulleys. B9
• Make sure accessible pulleys rotate freely.
Flap control unit.
270019 B9
• Check the gearbox fluid level (Ref. AMM 27-50-121).
270020 Flap control unit. Check the gearbox fluid level (Ref. AMM 27-50-121). B9
Flap drive shafts.
270021 Inspect for signs of corrosion and for movement between the end fittings and the B9
shafts.
Aileron primary surfaces. Make sure of full and free movement from stop to
270022 B10
stop and that all accessible aileron pulleys rotate freely.

Copyright © Textron Aviation Inc. Page 13 of 48

Aileron servo tabs.

• Check the free movement (backlash) at the trailing edges of the tabs
(Ref. AMM 27-10-00, 501).
• While the connecting rods are disconnected inspect the rear rod-end
bearings for smooth operation.
270023 B10
• Detail inspect the connecting rod attachment lugs on the tabs for cracks
using a X 10 magnifier.
NOTE:
Do not remove the protective finish unless a defect, or a suspected
defect is found.
Flap Screwjack and reduction gearbox.
270024 B10
• Check the gearbox fluid level (Ref. AMM 27-50-141).
Flap synchronization system control cables.
270025 • Inspect for fraying, particularly in the vicinity of the pulleys. B10
• Make sure accessible pulleys rotate freely.
Flap drive shafts.
270026 Inspect for signs of corrosion and for movement between the end fittings and the B10
shafts.
270027 Flap control system. Do a function test (Ref. AMM 27-50-02, 501). B12
Airbrake and lift dump system.
270028 • Do a functional test (Ref. AMM 27-61-02, 501). B12

270029 Task deleted. C2

Elevator trim servo.
• Operate the elevator trim switch on the left, or right, control column.
270030 • As the elevator trim servo motor operates the elevator trim tabs, hold the C2
manual elevator trim wheel with sufficient force to stop the trim wheel.
• The force needed to stop the trim wheel must not be more than 15 lbs.
270031 Requirement deleted. Covered by Inspection B12 task # 270027. C3
Aileron autopilot servo control cables.
Check cable tensions are correct:
• 750 airplanes (Ref. AMM 27-00-00, 201 and 22-10-10, 401).
270032 • 800XP airplanes (Ref. AMM 27-00-00, 201 and 27-10-93, 401). C4
• 800XP/850XP Pro Line 21 airplanes (Ref. AMM 27-00-00, 201 and 22-
10-10, 401).
• 900XP airplanes (Ref. AMM 27-00-00, 201 and 22-10-10, 401).
Elevator control system balance/feel spring.
270033 C4
• Inspect.
Elevator primary control cables.
270034 C5
Check cable tensions are correct (Ref. AMM 27-30-00).
Flap control cables.
270035 C5
Check cable tensions are correct (Ref. AMM 27-50-02).
Elevator primary and elevator trim control cables. Check cable tensions
270036 C7
are correct (Ref. AMM 27-30-00).
Rudder primary and rudder trim control cables. Check cable tensions are
270037 C7
correct (Ref. AMM 27-20-00).

Copyright © Textron Aviation Inc. Page 14 of 48

Elevator autopilot servo control cables.

Check cable tensions are correct:
• 750 airplanes (Ref. AMM 22-10-30, 401).
270038 C7
• 800XP airplanes (Ref. AMM 27-30-81, 401).
• 800XP/850XP Pro Line 21 airplanes (Ref. AMM 22-10-30, 401).
• 900XP airplanes (Ref. AMM 22-10-30, 401).
Rudder autopilot servo control cables.
Check cable tensions are correct:
• 750 airplanes (Ref. AMM 22-10-20, 401).
270039 C7
• 800XP airplanes (Ref. AMM 27-20-121, 401).
• 800XP/850XP Pro Line 21 airplanes (Ref. AMM 22-10-20, 401).
• 900XP airplanes (Ref. AMM 22-10-20, 401).
Elevator autopilot trim-servo control cables. Check cable tensions are
270040 C7
correct (Ref. AMM 27-30-00).
Elevator trim cables.
• Inspect the condition of the protective coating (Ref. AMM 20-95-11, Item
No. 079) on the cables over a length of 42 ins (1070 mm) from each trim
270041 chain where the cables are exposed between the horizontal stabilizer C8
and the elevators.
• Apply protective coating (Ref. AMM 27-30-00, page block 301), if
necessary.
Aileron primary and trim control cables.Check cable tensions are correct
270042 C9
(Ref. AMM 27-10- 00).
Flap drive shaft universal joints. With grease covers removed, inspect joints
270043 C9
for wear and repack with grease (Ref. AMM 27-50-132).
Flap Bevel drive assembly.
270044 Check that the backlash between the input and output shafts, measured at the C9
input coupling flange bolts, does not exceed 0.020 in.
Flap control unit baulk release cable. Check cable tension is correct (Ref.
270045 C9
AMM 27-50-02).
Flap/airbrake baulk bobbin. Make sure bobbin setting is correct (Ref. AMM
270046 C9
27-50-02).
Flap spring drum pulley-lever.
• Disconnect rod from pulley lever (Ref. AMM 27-50-02).
• Check the pull off force required to move the lever off the spring drum
internal stops is 5.35 lb. to 7 lb., measured at the connecting rod
270047 C9
attachment point on the lever.
• Check that the lever returns to contact internal stops at or before 5 lb.
force at the connecting rod attachment.
• Reconnect control rod to pulley lever.
Flap Screwjack and reduction gearbox.
270048 Check that the backlash on the screw threads does not exceed 0.020 in (Ref. C9
AMM 27-50-141).

Copyright © Textron Aviation Inc. Page 15 of 48

Flap synchronizing system.

• Check the cable tensions are correct (Ref. AMM 27-50-02).
• With the flaps selected up, disconnect the operating link from one
transmitter gearbox only.
• Pressurize the hydraulic system.
270049 • Whilst restraining the disconnected lever arm, select the flaps down. C9
• Make sure that the flaps start to move and then the system cuts out.
• Depressurize the hydraulic system and connect the transmitter operating
link.
• Pressurize the hydraulic system and make sure that the flaps operate
correctly.
Airbrake control cables.
270050 C9
Check the cable tensions are correct (Ref. AMM 27-61-02).
Aileron primary and trim control cables. Check cable tensions are correct
270051 C10
(Ref. AMM 27-10-00).
Flap drive shaft universal joints. With grease covers removed, inspect joints
270052 C10
for wear and repack with grease (Ref. AMM 27-50-132).
Flap bevel drive assembly.
270053 Check that the backlash between the input and output shafts, measured at the C10
input coupling flange bolts, does not exceed 0.020 in.
Flap screwjack and reduction gearbox. Check that the backlash on the
270054 C10
screw threads does not exceed 0.020 in (Ref. AMM 27-50-141).
Flap synchronizing system.
• Check the cable tensions are correct (Ref. AMM 27-50-02).
• With the flaps selected up, disconnect the operating link from one
transmitter gearbox only.
• Pressurize the hydraulic system.
270055 • Whilst restraining the disconnected lever arm, select the flaps down. C10
• Make sure that the flaps start to move and then the system cuts out.
• Depressurize the hydraulic system and connect the transmitter operating
link.
• Pressurize the hydraulic system and make sure that the flaps operate
correctly.
Airbrake control cables. Check cable tensions are correct (Ref. AMM 27-61-
270056 C10
02).
Flap control forward spring strut. Check break-out load with one end
270057 disconnected and using a spring balance is 21.5 to 24.5 lb. (Ref. AMM 27-50- D4
02).
270058 Flap control input-circuit. Do a static friction check (Ref. AMM 27-50-02). D4
270059 Control cable pressure seals at rear pressure bulkhead. Inspect for wear. E7
Filter, auxiliary hydraulic system supply to flap control unit.
Replace the filter element (Ref. AMM 29-20-00, 001).
270060 D10
NOTE:
The AMM reference is for component location ONLY.

Copyright © Textron Aviation Inc. Page 16 of 48

After 200 flying hours and not more than 300 flying hours after control cable
replacement.
Control cables. Check the tensions of the:
• Aileron and aileron trim control cables (Ref. AMM 27-10-00, 501, select
750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
• Rudder and rudder trim control cables (Ref. AMM 27-20-00, 501, select
270061 750, 800XP, 800XP/850XP Pro Line 21 or 900XP). Out of Phase
• Elevator and elevator trim control cables (Ref. AMM 27-30-00, 501,
select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
• Flap control cables (Ref. AMM 27-50-02, 501, select 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
• Airbrake control cables (Ref. AMM 27-61-02, 501, select 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
270062 Transferred to Inspection B2, task # 270004. Out of Phase
Whenever the SVO-85B servo or its mating servo mount are removed and
replaced in the airplane.
270063 Out of Phase
Servomotor assembly SVO-85B (P/N 622-5027-001). Lubricate and clean as
detailed in Collins SVO-85B/C Service Information Letter SIL 1-01.
Flap vane inner. With the flaps lowered, inspect the right outer attachment
270064 C10
bracket for cracking and for security of attachment to the flap leading edge.
Flap screwjacks.
270065 B10
• Inspect screw threads for satisfactory condition.
270066 Aileron Control cable pressure seals. Inspect for wear. B9
270067 Aileron Control cable pressure seals. Inspect for wear. B10
Aileron Servomotor assembly SVO-85B (P/N 622-5027-001).
270068 • Lubricate and clean as detailed in Collins SVO-85B/C Service G
Information Letter SIL 1- 01.
Elevator Servomotor assembly SVO-85B (P/N 622-5027-001).
270069 • Lubricate and clean as detailed in Collins SVO-85B/C Service G
Information Letter SIL 1- 01.

Rudder Servomotor assembly SVO-85B (P/N 622-5027-001).

270070 • Lubricate and clean as detailed in Collins SVO-85B/C Service G
Information Letter SIL 1- 01.
Rudder Trim Jack.
270071 • Do an inspection (Ref. AMM 27-20-111, 301, select 750, 800XP, G
800XP/850XP Pro Line 21 or 900XP).
Elevator Trim Jack.
270072 • Do an inspection (Ref. AMM 27-30-51, 301, select 750, 800XP, G
800XP/850XP Pro Line 21 or 900XP).
Chapter 28 - Fuel
Fuel Transfer System, Wing tanks. Check fuel flow.
• Check for positive flow from LH and RH Wing Tank to opposite Wing
280001 Tank. B1
NOTE:
For positive flow note a 200lb increase in the fuel gauge indication.

Copyright © Textron Aviation Inc. Page 17 of 48

Fuel valve control cables. Check cable tensions are correct (Ref. AMM 28-
280002 C5
20-83).
280003 LP valves. Do a function test for internal leakage (Ref. AMM 28-20-00). D1
APU fuel inlet filter (if fitted). Inspect, clean or replace the fuel filter element: •
280004 D7
800XP airplanes (Ref. AMM 28-20-09).
280005 Suction pipe strainers. Visually inspect for satisfactory condition. C9
Water transfer system pipe suction blocks. Visually inspect for satisfactory
280006 C9
condition.
280007 Suction pipe strainers. Visually inspect for satisfactory condition. C10
Water transfer system pipe suction blocks. Visually inspect for satisfactory
280008 C10
condition.
280009 Transferred to Structural Inspections task # 570027. Out of Phase
After 200 flying hours and not more than 300 flying hours from the airplane build
or after Control Cable replacement. Control cables.
Check the tensions of the:
• LP fuel valve control cables (Ref. AMM 28-20-83, 501, select 750,
800XP, 800XP/850XP Pro Line 21 or 900XP).
280010 Out of Phase
• Crossfeed and wing transfer valve control cables (Ref. AMM 28-20-83,
501, select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
• Auxiliary fuel transfer valve control cables (Ref. AMM 28-20-83, 501,
select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP) (if ventral tank
installed).
280011 Requirement deleted. Out of Phase
280012 Requirement deleted. Out of Phase
Split into 2 tasks and transferred to Inspection C9 (280014) and Inspection C10
280013 Out of Phase
(280015).
Applicable to Intertechnique fuel pumps only. Fuel system pumps.
280014 • Part No. 2070C01 Check the brush length (14 mm minimum). C9
• Part No. 2070C11 Check the brush length (10 mm minimum).
Applicable to Intertechnique fuel pumps only. Fuel system pumps.
280015 • Part No. 2070C01 Check the brush length (14 mm minimum). C10
• Part No. 2070C11 Check the brush length (10 mm minimum).
Low Pressure Fuel Valve Support Strut Part No. 25 PF361, 25 PF361-5A
(Mod. 25G310A) and 25 PF363.
Do a visual inspection of the Low Pressure Fuel Valve Support Strut, attachment
280016 bolt and drain hole for corrosion. G
NOTE:
If corrosion is found replace the affected part.
Chapter 29 - Hydraulic Power
290001 Task deleted. A2
290002 Task deleted. A4
290003 Suction filter. Replace the element (Ref. AMM 29-10-21). B7
Main hydraulic system.
290004 • At system shutdown check the pressure dissipation time on the main B12
pressure accumulator (Ref. AMM 29-10-00, 501).

Copyright © Textron Aviation Inc. Page 18 of 48

Landing gear and flaps emergency lowering system. Do an operational

290005 B12
test (Ref. AMM 29-20-00).
Hydraulic tank pressurization system. Drain any accumulation of liquid from
290006 C7
the drain/ground air charge connection.
Flaps, airbrakes, landing gear, nosewheel steering, nose leg self-
290007 centring. Do a test of the main system with a hydraulic test rig (Ref. AMM 29- C12
10-00).
Emergency brake system leak rate. Check the rate that the pressure
290008 C12
decreases (leakage rate) in the accumulator (Ref. AMM 29-10-00).
Auxiliary reservoir low-level warning system Do a function test (Ref. AMM
29-30-00).
290009 B12
NOTE:
Do this task in conjunction with Task # 290005.
Hydraulic reservoir pressurization system. Do a functional test of the non-
290010 C12
return valve (Ref. AMM 29-10-13).
290011 Full-flow relief valve. Clean filter element (Ref. AMM 29-10-71). D7
High temperature warning system Do a test of the main hydraulic reservoir
290012 D7
high temperature warning system (Ref. AMM 29-30-00).
Chapter 30 - Ice and Rain Protection
Rotary ice detector. Do a function test (Ref. AMM 30-80-00, 501, select 750,
300001 B1
800XP, 800XP/850XP Pro Line 21 or 900XP).
Windshield electrical de-icing system. Do an operational test of the
300002 C1
windscreen overheat (Ref. AMM 30-41-00).
Airframe de-icing system pressure filter.
300003 B6
• Replace the filter element (Ref. AMM 30-10-52).
300004 Pitot head and static plate heaters. Do a function test (Ref. AMM 30-35-15). C1
Airframe de-icing pump suction-filter. Replace the filter element (Ref. AMM
300005 C6
30-10-43, select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
300006 Transferred to Navigation, task 340014. F3
Every calendar month. Applicable if the airframe de-icing system has not been
operated during the last calendar month.
300007 Airframe Ice protection Out of Phase
• Purge the airplane ice protection system (Ref. AMM 12-30-00, 301,
select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
Chapter 31 - Instruments
Flight data recorder (if fitted). Check for correct playback operation (data
dump) and for quality of the recording.
NOTE:
310001 Do the check at this inspection or at a time agreed necessary by the E1
local airworthiness authority. For FDR systems not installed under the
original Airplane Type Certificate, reference the applicable Maintenance
Manual Addenda for systems fitted by Supplemental Type Certificate
(STC).
Chapter 32 - Landing Gear

Copyright © Textron Aviation Inc. Page 19 of 48

Braking systems.
320001 • Do a test of the emergency and parking brake system operation (Ref. B12
AMM 32-40-00, 501).
Maxaret units.
320002 B12
• Do a function test (Ref. AMM 32-40-101, 501).
Nose gear leg assembly.
320003 • Make sure oil level and gas pressures are correct (Ref. AMM 32-20-12). B12
• Check the leg extension (Ref. AMM 12-32-00).
Nose gear leg lock and change-over microswitches operating
320004 B12
mechanism. Make sure of freedom of operation.
Nosewheel steering jack.
• Inspect for satisfactory condition.
320005 B12
NOTE:
Pay particular attention to scores and the cleanliness of the jack ram.
Nose gear retraction and steering system spring struts.
320006 B12
• Inspect.
320007 Nosewheel steering ON/OFF valve. Inspect. B12
320008 Nose gear drag stay assembly. Check clearances (Ref. AMM 32-20-21). B12
Nosewheel steering jack selector valve. Service: Clean and grease the
320009 selector valve spring housing and parts (Ref. AMM 32- 50-11, 301), select 750, B12
800XP, 800XP/850XP Pro Line 21 or 900XP).
Main gear leg assemblies.
320010 • Make sure oil level and gas pressures are correct (Ref. AMM 32-10-12). B12
• Check the leg extension (Ref. AMM 12-32-00).
Main landing gear side-stays.
320011 • Inspect the center joint nut for distortion (Ref. AMM 32-10-25). B12
• Check the side-stay clearances (Ref. AMM 32-10-25).
Main landing gear torque links. Examine the torque link pivots for wear (Ref.
320012 B12
AMM 32-10-12, page block 601).
Main landing gear doors.
• Inspect the hinge bracket assemblies for security and tightness of the
nuts.
• Inspect jack attachment brackets and adjacent structure for cracks.
• Inspect for signs of movement of the forward hinge brackets and bolts at
320013 B12
their attachment to the wing structure by attempting to rock the doors in
the longitudinal and transverse directions.
NOTE:
If the brackets are found to be loose, inspect the attachment bolt holes
and bolts for wear and corrosion.
Main landing gear door uplock spring struts.
• Inspect.
• Clean the sliding surfaces.
320014 B12
• Make sure of correct operation:
Check initial breakout/first movement of the spring strut occurs at 19 lb ±2 lb.
Make sure movement of the strut is free over the length of the stroke.

Copyright © Textron Aviation Inc. Page 20 of 48

Reversing valves and operating mechanisms.

• Disconnect from the side stay.
320015 • Inspect for satisfactory condition. B12
• Make sure the mechanisms are free to move correctly.
• Connect to the side stay.
Steering system cables and chains.
320016 • Make sure cable tensions are correct (Ref. AMM 32-50-00, select 750, C4
800XP, 800XP/850XP Pro Line 21 or 900XP).
Nose landing gear retraction spring strut. Check the break-out load (Ref.
320017 C12
AMM 32-20-21).
Nosewheel steering system spring strut break-out load.
• Check the break-out load (Ref. CMM 32-50-00).
320018 C12
• If the load is excessive, dismantle the spring strut, clean, lubricate and
reassemble (Ref. CMM 32-50-00).
Steering system filter element. Remove, inspect and clean filter element (Ref.
320019 D12
AMM 32-30- 22).
Filters, hydraulic supply (4 off). Clean the filter elements (Ref. AMM 32-30-
320020 D12
22).
Restrictor valves. Clean the micro filters in the pipe connections (Ref. AMM
320021 D12
32-30-01).
Brake master cylinders.
320022 • Check fluid level and replenish, as necessary (Ref. AMM 32-40-00, 301, B4
select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
Brake hoses to master cylinders.
320023 • Make sure of an adequate clearance between the hoses and the floor C4
over the full range of rudder pedal travel.
Axle/Maxaret/Modulator/Plunger Tube.
• Maxaret and modulator unit. Remove and inspect (Ref. AMM 32-40-91
and AMM 32-40-101).
• While the Maxarets and Modulator units are removed, detail inspect the
320024 internal bores of the axles. C12
• Inspect the Plunger Tube to Axle Bore for signs of corrosion.
• Reinstall Maxarets and Modulator units (Ref. AMM 32-40-91 and AMM
32-40-101).
• Do a function test (Ref. AMM 32-40-101, ADJUSTMENT/TEST).
320025 Transferred to Task # 320024. F12
320026 Task deleted. Covered by Part 7, Lubrication. G
Nose-wheel steering on/off-valve.
• Remove the plunger stop cap.
• Visually inspect the plunger and spring for corrosion, clean and lubricate
320027 G
all surface areas as required using Grease (Ref. AMM 125/H-20, 20-95-
11, Item 034).
• Install the stop cap.
8 years, then every 4 years. Main landing gear fairing strut.
320028 Structural Inspections
• Comply with instructions in NTM 32-10-103.

Copyright © Textron Aviation Inc. Page 21 of 48

Between 25 to 50 landings from build or after nose landing gear drag

320029 stay replacement. Nose landing gear drag stay. Check clearances (Ref. AMM Out of Phase
32-20-21, 601, select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
320030 Requirement deleted. Out of Phase
320031 Requirement deleted. Out of Phase
Requirement deleted, covered in Overhaul Manual Chapter's 32-20-30/501 and
320032 Out of Phase
32-20-35/501.
Main gear retraction actuator (Ref. AMM 32-30-27).
NOTE:
320033 To do this inspection, disconnect the cylinder head end of the actuator. B12
Do not disconnect the hydraulic lines.
• Detail inspect the actuator attachment lugs.
Plunger Tube/Axle Joint
• Inspect the flexible seal at the plunger tube to axle joint.
320034 B12
• Make sure the seal is not loose or cracked.
• Rectify as necessary (Ref. AMM Chapter 32, MAIN LEG ASSEMBLY).
Main Leg Assembly Retraction Lever.
320035 • Inspect for excessive movement. C12
• Inspect for signs of corrosion.
Sidestay Assembly Lock Mechanism Link.
320036 C12
• Inspect for signs of wear.
Nose leg assembly torque links. Examine the torque link pivots for wear (Ref.
320037 B12
AMM 32-20-12, 601).
NOTE:
This task is not applicable to airplanes Post Mod. 25G295 or Post SB. 32-
3779.
320038 Every month if the airplane has been exposed to runway de-icing: Out of Phase
• Lubricate the Main landing gear sidestay shims (Ref. Chapter
5,Lubrication, Monthly lubrication).
Chapter 33- Lights
330001 Task deleted. A1
330002 Task deleted. A3
Anti-Collision light system that has a strobe type device in any position.
• Clean the strobe light lenses internal and external.
• Clean the wing-tip lens covers internal and external.
• Check the strobe light flash rate (Flash rate of 60 ± 5 cycles per minute),
330003 (Ref. AMM 33- 40-12, 201). B1
NOTE:
Refer to the Component Requirements section of this manual for the
manufacturer's recommended period for replacement and strobe light
intensity test procedure.
Chapter 34- Navigation
340001 Requirement deleted. A1

Copyright © Textron Aviation Inc. Page 22 of 48

Pitot/static drain traps.

• Pre SB.34-3282 (Mod. 25F889B) or Pre Mod. 25F889A. Drain, do a
leak test (Ref. AMM 34-11-19, 501, select 750, 800XP, 800XP/850XP
Pro Line 21 or 900XP).
• Post SB.34-3282 (Mod. 25F889B) or Post Mod. 25F889A. Drain (Ref.
340002 Out of Phase
AMM 34-11-19, 501, select 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
NOTE:
Do this task in conjunction with FAR pitot/static system checks (Task
340006).
Autopilot aileron servo unit and mount.
• Inspect, particularly for cable and capstan wear, contamination, cable
spool-off angle and security of the servo unit and mount.
340003 C4
• With the autopilot disengaged operate the control system throughout the
entire range and make sure there is no unusual noise, binding, backlash
or signs of other mechanical irregularities from the servo mount.
Autopilot servo units, rudder and elevator.
• Inspect, particularly for cable and capstan wear, contamination, cable
spool-off angle and security of the servo unit and mount.
340004 C7
• With the autopilot disengaged operate the control system throughout the
entire range and make sure there is no unusual noise, binding, backlash
or signs of other mechanical irregularities from the servo mount.
Autopilot elevator trim servo unit and mount.
• Inspect, particularly for cable and capstan wear, contamination, cable
spool-off angle and security of the servo unit and mount.
340005 C7
• With the autopilot disengaged operate the control system throughout the
entire range and make sure there is no unusual noise, binding, backlash
or signs of other mechanical irregularities from the servo mount.
Pitot/static and stall warning systems.
Do the following tests (Ref. AMM 34-11-19, 501, select 750, 800XP,
800XP/850XP Pro Line 21 or 900XP):
• Pressure Test Complete Pitot System.
340006 • Suction Test Complete Static System. Out of Phase
• Pressure Test Stall Vent System (This procedure only applies to
airplanes Pre-Mod. 25G206A or 25G206B).
NOTE:
Do this task in accordance with FAR requirements.
Pitot system isolation valves.
Make sure of full and free operation.
340007 NOTE: Out of Phase
This task is not applicable to the Hawker 750 or Hawker 900XP airplanes
due to the removal of the third channel stall can. Do this task in
conjunction with FAR pitot/static system checks (Task 340006).
Mach trim system.
Do a test of the Mach trim system:
• 750 airplanes (Ref. AMM 22-20-00, 501).
340008 D1
• 800XP airplanes (Ref. AMM 34-24-00, 501).
• 800XP/850XP Pro Line 21 airplanes (Ref. AMM 22-20-00, 501)
• 900XP airplanes (Ref. AMM 22-20-00, 501).

Copyright © Textron Aviation Inc. Page 23 of 48

340009 Transferred to task 340010. G

Autotrim command isolation relay and autotrim switching relay.
NOTE:
This task is ONLY applicable to airplanes equipped with an FCC-86
340010 Flight Control Computer. D1
• Do checks as detailed, Ref. AMM 27-30-00, 501, (Autotrim command
isolation relay and autotrim switching relay checks).
This task is NOT applicable to Pro Line 21 Equipped airplanes.
Mach trim fail annunciation relays.
• Open the MACH TRIM PWR or MACH TRIM MON circuit breaker.
340011 D1
• Make sure that the MACH TRIM FAIL annunciator comes on.
• Close the MACH TRIM PWR or the MACH TRIM MON circuit breaker.
• Make sure that the MACH TRIM FAIL annunciator goes off.
Every 36 months, or at a time period agreed with the local regulatory authority.
Compass systems.
• Do a check compass swing of the compass systems at four headings 90
degrees apart.
• Compare deviations, if any are found, with the existing deviation card.
340012 Out of Phase
• If deviations are found then do a compass swing:
750 airplanes (Ref. AMM 34-20-05, 501).
800XP airplanes (Ref. Collins AMM 34-23-61, 501) (Ref. Honeywell AMM 34-
20-15, 501). 800XP Pro Line 21 airplanes (Ref. AMM 34-20-05, 501). 900XP
airplanes (Ref. AMM 34-20-05, 501).
After repaint or maintenance in the area affecting the airflow over static ports.
Static plates and Airframe
(Applicable to airplane serial numbers 258359 and after, and to airplanes that
340013 have complied with Service Bulletin 34-3110, or SB.34-3166 or SB.34-3381 Out of Phase
and are maintaining RVSM capability authorization). Comply with RVSM
requirements (Ref. AMM 34-11-29, 601, select 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP) for the area disturbed.
340014 Task deleted. F3
Chapter 35- Oxygen
Oxygen system master supply valve.
• With the oxygen system fully charged and the supply master valve closed,
exhaust system downstream of the valve until the contents gauge
350001 indicates zero. B4
• After 15 minutes has elapsed, make sure that there is no increase in the
contents gauge indication which would show leakage past the closed
valve.
Automatic shut-off valve.
350002 D2
Do a functional test (Ref. AMM 35-10-141).
350003 Task deleted. E2

Copyright © Textron Aviation Inc. Page 24 of 48

Passenger oxygen system.

• Test automatic operation of baromatic valve (Ref. AMM 35-06-00, 501).
• Test for flow from each mask by reference to operation of the visual
indicator (if fitted) when mask is pulled down to the 'full hang' position:
750 airplanes (Ref. MMA 35-06-00, 201).
800XP and 800XP/850XP Pro Line 21 airplanes (Ref. MMA 35-06-00, 201).
900XP airplanes (Ref. MMA 35-06-00, 201).
• Inspect drop-out mask units when deployed during system test: 750
airplanes (Ref. MMA 35-20-05, 301). 800XP and 800XP/850XP Pro
350004 Line 21 airplanes (Ref. MMA 35-20-05, 301). 900XP airplanes (Ref. E2
MMA 35-20-05, 301).
NOTE:
If the passenger masks PN. 289-601* do not meet the requirements of the
annual inspection refer to the vendor CMM 35-22-26 for Visual, Overhaul
and Repair procedures.
• Stow drop-out mask units:
750 airplanes (Ref. MMA 35-20-05, 301). 800XP and 800XP/850XP Pro Line
21 airplanes (Ref. MMA 35-20-05, 301). 900XP airplanes (Ref. MMA 35-20-05,
301).
Baromatic control valve.
• With passenger supply isolation valve closed, exercise control valve
350005 E2
mechanism by operating the emergency/reset knob several times.
• Leave the knob at the reset position.
350006 Crew masks, smoke set mask (if fitted) and hoses. Inspect. E4
Portable breathing equipment.
• Inspect: 800XP airplanes (Ref. AMM 35-35-10).
350007 E4
OR
• Check the expiry dates.
Oxygen cylinders.
350008 • Inspect cylinder mount clamps for security (Ref. AMM 35-10-14, 401, C7
select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
Chapter 38- Water/Waste
Water systems.
• Inspect the toilet and galley water systems.
• Make sure the flow of water is correct through the normal and overflow
drains and that there are no leaks. If you find signs of fluid leakage:
• Inspect the aileron-cable fuselage pressure-seals and the adjacent
structure in the areas to the rear of frame 16. Do this to make sure the
fluid leakage has drained correctly.
• Make sure the drain holes and drain valves are free from blockages and
380001 function correctly. Do this from the inside and the outside of the fuselage. B6
• Remove all fluid remaining in the area.
• Clean the areas where leakage has occurred.
• Lubricate the aileron cables if necessary (Ref. AMM 12-20-25).
• Replenish the toilet and galley water systems, if required: 800XP
airplanes (Ref. AMM 12-38-00 or MMA Chapter 38 as applicable).
800XP/850XP Pro Line 21 airplanes (Ref. AMM 12-38-00 or MMA
Chapter 38 as applicable). 750 airplanes (Ref. MMA Chapter 38).
900XP airplanes (Ref. MMA Chapter 38).

Copyright © Textron Aviation Inc. Page 25 of 48

Chapter 49- Airborne Auxiliary Power

NOTE:
Also refer to inspection 050020 for APU servicing information.
Perform in conjunction with Task 490003.
PATS APU GTCP36-150W.
490001 • Visually inspect exhaust for cracks or deformation. Out of Phase
• Visually inspect for loose or frayed wires.
• Inspect for signs of corrosion.
Every 750 APU running hours.
PATS GTCP36-150W APU.
490002 Igniter plug (Ref. CMM 49-40-33): Out of Phase
• Remove, clean, inspect and install.

NOTE:
Choose one of the following options. Do either Oil and Filter change at
every 12 months or 1000 flying hours OR do a S.O.A.P. check at 750 APU
running hours/12 months.
CAUTION:
Do not mix options.
Option 1.
Every 12 months or 1000 flying hours (whichever comes first).
PATS GTCP36-150W APU.
Oil and filter change, and magnetic drain plug inspection. Lubricating oil system:
• Drain and refill (refer to servicing).
NOTE:
490003 Routine SOAP inspection is not required. Out of Phase
Oil Filter Element:
• Remove, inspect and replace as necessary (Ref. CMM 49-90-47).
Magnetic Drain Plug:
• Remove, clean, inspect and install magnetic element of drain plug (Ref.
CMM 49-90-46).
Option 2.
750 APU running hours or 12 months (whichever comes first). Oil and Filter
Element:
• Do a S.O.A.P. check (in accordance with Honeywell procedures).
Magnetic Drain Plug:
• Remove, clean, inspect and install magnetic element of drain plug (Ref.
CMM 49-90-46).
Every 1000 APU running hours.
PATS GTCP36-150W APU.
490004 Fuel filter element: Out of Phase
• Remove and replace (Ref. CMM 49-30-52).
Every 4500 APU running hours.
PATS GTCP36-150W APU.
490005 Fuel Nozzle Assemblies: Out of Phase
Do a fuel flow rate check (Ref. CMM 49-20-00, Page Block 601, paragraph 5,
Fuel Nozzle Assembly Flow Rate Check).

Copyright © Textron Aviation Inc. Page 26 of 48

Every 4500 APU running hours.

PATS GTCP36-150W APU.
Hot Section Inspection.
Do a detailed Hot Section Inspection on the components listed (Ref. CMM 49-
20-00, Page Block 601, paragraph (4), Detailed Hot Section Inspection):
• Turbine Rotor.
• Deswirl Deflector.
490006 • Turbine Nozzle. Out of Phase
• Airflow Deflector.
• Turbine Housing Assembly.
• Combustion Chamber.
• Labyrinth Seal.
• Turbine Wheel Deflector.
• Retainer Halves.
• Containment Ring.
Every 4500 APU running hours.
PATS GTCP36-150W APU.
Compressor Rotor:
490007 • Visually check compressor rotor for damage by observation through the Out of Phase
compressor screen openings.
NOTE:
No damage allowed.
Chapter 51- Structures
Every 5000 landings or 12 years, whichever occurs first.
510001 Nose landing gear bay sidewalls. Access: Refer to NTM Technique. Structural Inspections
• Comply with instructions in NTM 53-10-111.
5000 flights then every 1000 flights.
Front pressure bulkhead. Access: Sound-proofing blankets removed.
• Detail inspect the upper sidewall beams and the rudder pedal clearance
510002 pressings for cracks (Ref. SRM 53-10-11, Front Pressure Bulkhead Pre Structural Inspections
Mod. 253090C or Front Pressure Bulkhead Mod. 253090C).
• Pay special attention to the area in the vicinity of the joint with the canopy
center post.
12 years, then every 4 years.
Flight compartment skin and window structure above windshields. Access:
510003 Refer to NTM Technique. Structural Inspections
• Comply with instructions in NTM 53-10-105A.
Every 20,000 flights.
Upper canopy rail at intersection with the canopy posts. Access: Trim and
510004 insulation removed. Structural Inspections
• Detail inspect.
15 to 18 years, then every 8 years.
Center fuselage structure below the floor, nose landing gear bay to Frame 13
and Frames 16 to 19. Access: Refer to relevant NTM Techniques.
• Comply with instructions in:
510005 Structural Inspections
• NTM 53-10-108.
• NTM 53-10-107.
• NTM 53-10-108B.
• NTM 53-10-109.

Copyright © Textron Aviation Inc. Page 27 of 48

Between 15 to 18 years and then every 8 years.

Structure below escape hatch, Frames 13 to 14. Access: Escape hatch
removed, leaded vinyl sleeve peeled back from lower corners of the escape
510006 hatch surround to expose the apertures in the surround. Structural Inspections
• Detail inspect Frames 13 and 14, as far as is possible, for signs of
corrosion using a borescope probe.
Between 15 to 18 years and then every 8 years.
Center fuselage structure below the floor, frames 8 to 17. Access: Refer to NTM
510007 Technique. Structural Inspections
• Comply with instructions in NTM 53-10-106A.
Between 15 to 18 years and then every 8 years.
Center fuselage structure below the floor, Frames 13 to 16. Access: Refer to
NTM Technique.
• Comply with instructions in NTM 53-10-108A.
510008 NOTE: Structural Inspections
In certain instances it may be necessary to lower the wing or separate
the wing from the fuselage to insert the film packs. In order to determine
the conditions of individual airplanes a test may be done by attempting
to pass a strip of vinyl carrier, to the dimensions given in the relevant
NTM, between the fuselage lower skin and the wing top surface.
8 years and then every 4 years.
Entry door surround. Access: Panel F66A, F66B, F66C removed.
510009 • Detail inspect the structure at the lower edge of the surround for signs of Structural Inspections
corrosion using a borescope probe inserted through the lightening holes
in the intercostal.
Between the 15 th and 18th year of aircraft operation and then every 8
years.
Center fuselage structure, above the floor. Access: Refer to relevant NTM
Techniques.
Access: Refer to relevant NTM Techniques.
NOTE:
The most economical and practical time to do this inspection is when
the quick trim is removed for refurbishing or other reasons.
NOTE:
Airplanes without the digital pressurization control system Mod.
25G726A/C or Mod. 25G726B/C. When installing local furnishings, make
sure a minimum clearance of 1.0 inch between the motor of the fan
510010 operated venturi and local furnishings is kept. Structural Inspections
• Peel back the sound dampening material sufficiently to visually inspect
the skin in the vicinity of the fasteners and other attachments. It is not
necessary to remove the sound dampening material.
• Inspect the skin, as far as is possible, for cracks, signs of corrosion and
deterioration of the protective treatment.
• Comply with instructions in:
• NTM 53-10-101.
• NTM 53-10-102.
• NTM 53-10-103A.
• NTM 53-10-104.
• NTM 53-10-106.

Copyright © Textron Aviation Inc. Page 28 of 48

Chapter 52- Doors

520001 Task deleted. A3
Baggage pannier loading door/upper hatch warning system (if fitted) OR
External baggage unit (EBU) (750 airplanes ONLY).
• Test for correct operation (Ref. AMM 52-30-05).
520002 C1
NOTE:
This test is only applicable to airplanes with a baggage pannier in place
of the ventral fuel tank OR 750 airplanes with external baggage unit.
Baggage pannier door (if fitted) OR External baggage unit (EBU) (750 airplanes
ONLY). Inspect: (Ref. AMM 52-30-05):
• The door seal for damage, distortion and maintained shape profile.
• Seal for adhesion to the door lip.
520003 • Seal to door surround interface for potential leakage. C3
• Door surround surface for damage which would prevent good sealing.
NOTE:
This test is only applicable to airplanes with a baggage pannier in place
of the ventral fuel tank OR 750 airplanes with external baggage unit.
Main entry door "not locked" warning microswitches .
• Energize the dc busbars (Ref. AMM 12-24-00, select 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
• With the main entry door open, operate the "door not closed"
microswitch.
• Make sure the "ENT DOOR UNLOCKED" annunciator on the Master
520004 warning System panel remains on. C6
NOTE:
If the annunciator goes off, then investigate the 'door lock 'microswitch
for seizure in the operated position.
• Release the "door not closed" microswitch.
• De-energize the dc busbars.
Escape hatch release mechanism.
520005 B6
Check the operating load using the external push button (Ref. AMM 52-20-00).
Escape hatch seals.
520006 Inspect for total seal contact with airframe structure to prevent ingress of B6
rainwater when the cabin is unpressurized.
Entry door.
• Inspect seal for deterioration and damage.
520007 C6
• Check internal handle operating loads (Ref. AMM 52-11-00, select 750,
800XP, 800XP/850XP Pro Line 21 or 900XP).
12 years then every 8 years.
Main entry door.
520008 Access: Refer to NTM Technique. Structural Inspections
• Comply with instructions in NTM 52-80-102.
Between 15 to 18 years, then every 8 years.
Escape hatch.
520009 • Access: Trim removed. Structural Inspections
Detail inspect the structure internally and externally for cracks, signs of corrosion
and the deterioration of the protective treatment.

Copyright © Textron Aviation Inc. Page 29 of 48

Main Entry Door - Folding Handrail (if fitted).

Inspect:
• 800XP and 800XP/850XP Pro Line 21 airplanes (Ref. MMA 52-15-00,
520010 C6
601).
• 750 airplanes (Ref. MMA 52-15-00, 601).
• 900XP airplanes (Ref. MMA 52-15-00, 601).
External Baggage Unit (EBU) loading Door (750 Airplanes).
520011 • Do a detailed visual inspection of the baggage door latch and pin B7
assemblies.
Chapter 53- Fuselage
8 years, then every 4 years.
Skin exterior under the dorsal intake, forward of Frame 19. Access: Dorsal
intake removed.
530001 Structural Inspections
• Detail inspect for cracks, signs of corrosion and deterioration of the
protective treatment.
• Detail inspect for chafing rivets.
8 years, then every 4 years.
Fuselage skin under wing-to-fuselage fairings. Access: Panels F124 and F224
530002 removed. Structural Inspections
• Inspect visible areas of skin for cracks and signs of corrosion using
flashlight, mirror and borescope probes.
This task is NOT APPLICABLE to the Hawker 750 airplane or 750 airplanes
with the Ventral baggage pannier installed in place of the Ventral fuel tank.
Between 15 to 18 years, then every 8 years.
Fuselage skin covered by the ventral fuel tank. Access:
530003 Ventral fuel tank removed. Structural Inspections
• Detail inspect especially for signs of corrosion and deterioration of
protective treatments.
• Detail inspect attachment points and links.
This task is NOT APPLICABLE to the Hawker 750 airplane or 750 airplanes
with the Ventral baggage pannier installed in place of the Ventral fuel tank.
Between 15 to 18 years, then every 8 years.
Ventral fuel tank and attachments.
Access: Ventral fuel tank and tank access panels removed 800XP (Ref. AMM
28-10-15), 800XP/850XP Pro Line 21 (Ref. AMM 28-10-15) and 900XP (Ref.
AMM 28-10-15).
• Detail inspect the tank internal structure, skin, access panels, bolts and
fasteners, fuel system components and pipelines.
530004 • Pay particular attention to the security of the nylon vent pipes and the Structural Inspections
integrity of the sealant fillets at the pipe joints.
• Inspect the rubber drain non-return valve in the vent system balance pipe
for deterioration and splitting.
• Detail inspect attachment points and links.
• Detail inspect the fuel seal block assembly (P/N: 25-8PT341-1A) at the
ventral tank diaphragm for missing sealer, voids and corrosion.
NOTE:
If missing sealer, voids or corrosion are found, remove the fuel seal
block assembly for further detailed inspection.

Copyright © Textron Aviation Inc. Page 30 of 48

Between 15 to 18 years, then every 8 years.

Fuselage skin covered by the ventral baggage pannier or EBU (750 airplanes)
(if fitted). Access: Ventral baggage pannier removed or EBU (750 airplanes) (if
fitted) removed.
• Detail inspect, specially for signs of corrosion and signs of deterioration
530005 Structural Inspections
of the protective treatments.
• Detail inspect attachment points and links.
NOTE:
This task is only applicable to airplanes with a baggage pannier in place
of the ventral fuel tank OR 750 airplanes with external baggage unit.
Between 15 to 18 years, then every 8 years.
Ventral baggage pannier (if fitted) or EBU (750 airplanes) (if fitted) internal
structure.
Access: Ventral baggage pannier (if fitted) or EBU (750 airplanes) (if fitted)
removed. All doors open and access panels removed..
530006 Structural Inspections
• Detail inspect the pannier internal structure.
• Detail inspect attachment points and links.
NOTE:
This task is only applicable to airplanes with a baggage pannier in place
of the ventral fuel tank OR 750 airplanes with external baggage unit.
12 years and then every 8 years.
Wing to fuselage attachment links, brackets and bolts. Access: Panels F124,
F224 and W501 removed.
530007 Structural Inspections
• Detail inspect links, brackets and bolts for cracks, signs of corrosion,
fretting and wear (Ref. AMM 53-40-01, select 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
530008 Transferred to AMM Chapter 32. Structural Inspections
27,000 flights and then every 4500 flights.
Fuselage lap joints.
530009 Access: Refer to NTM Technique. Structural Inspections
• Comply with instructions in NTM 53-10-104.
Whenever the wings are separated from the fuselage. Access: Wings
separated from the fuselage.
• Detail inspect the skin of the fuselage in the area that is covered by the
530010 wing structure. Structural Inspections
• Detail inspect the wing attachment brackets and the frame build-up at
frames 13 and 16.
• Detail inspect the drag spigot bearing.
• Inspect the drag spigot housing.

Copyright © Textron Aviation Inc. Page 31 of 48

Every 4 years.
Front face of rear pressure bulkhead (Frame 19).
• Inspect left-hand side of bulkhead with the soundproofing blankets
removed.
NOTE:
Airplanes without the digital pressurization control system Mod.
530011 25G726A/C or Mod. 25G726B/C. When installing local furnishings, Structural Inspections
make sure there is a minimum clearance of 1.0 inch between the
motor of the fan operated venturi and the local furnishings.
• Look for signs of corrosion at the boundary angle to Frame 19 joints.
NOTE:
If you find any defects, extend the inspection to include the right-
hand side of the bulkhead.
Every 8 years.
Front face of rear pressure bulkhead (Frame 19).
• Inspect right hand side of bulkhead with soundproofing blanket removed.
NOTE:
530012 Airplanes without the digital pressurization control system Mod. Structural Inspections
25G726A/C or Mod. 25G726B/C. When installing local furnishings, make
sure a minimum clearance of 1.0 inch between the motor of the fan
operated venturi and local furnishings is kept.
• Look for signs of corrosion at the boundary angle to frame 19 joints.
Every 10,000 flying hours.
Pylon engine main mounting attachment fittings. Access: Refer to NTM
530013 Technique. Structural Inspections
• Comply with instructions in NTM 53-10-110.
Every 20,000 flying hours.
530014 Rear engine mount fittings. Access: Refer to NTM Technique. Structural Inspections
• Comply with instructions in NTM 53-10-110A.
30,000 flying hours.
530015 Vertical stabilizer root attachment to fuselage. Access: Refer to NTM Technique. Structural Inspections
• Comply with instructions in NTM 55-30-104.
Every 10,000 flying hours.
Engine beam. Access: Engines and engine main mounting attachment fittings
removed (Ref. AMM 71-20-00, 401, select, 750 800XP, 800XP/850XP Pro
Line 21 or 900XP).
NOTE:
The pylon firewall below the engine front mount assembly and the inside
530016 of the engine pick-up mount bracket can be visually inspected from Structural Inspections
inside the pylon access panels. The ends of the engine beam with all the
doublers and angles can be inspected from inside the rear equipment
bay area.
• Detail inspect the multi-layer ends of the beam forming pick-ups for
damage, cracks and signs of corrosion using X 10 magnification.

Copyright © Textron Aviation Inc. Page 32 of 48

Whenever the brackets are removed from the engine.

This task is only required when the engine has accomplished a Major Periodic
Inspection. Refer to the relevant Honeywell Light Maintenance Manual: 750,
800XP and 800XP Pro Line 21 - TFE731-5BR-1H Series engine. 900XP -
530017 TFE731-50R-1H Series engine. Structural Inspections
Forward engine mounting brackets, Part No. 3071071-3. Access: Engine
cowlings M1L, M2R, M3L and M4R removed.
• Remove the mounting brackets.
• Inspect for cracks using a magnetic particle inspection (LMM 72-00-06).
4800 flying hours, then every 2400 flying hours.
530018 Structural Inspections
Fuselage skin adjacent to cabin window cutouts. Detail inspect skin.
PATS APU GTCP36-150W. Every 12 months.
NOTE:
If any of the following inspections show an abnormal indication or
requires the replacement of structural parts, do Tasks 530022 and
530023.
Detail inspect the following items accessible without removal from the rear
equipment bay, for cracks or failures:
• All APU support structure external to the fire enclosure.
530019 Structural Inspections
• Remove the oil filler door and all access covers in the bottom enclosure
and inspect all the APU structure internal to the fire enclosure.
• Inspect the main engine crossbeam and frame 21 in the areas
immediately adjacent to the APU attachment fittings.
• Inspect the five pairs of isolator mounts for deterioration of the silicone
rubber. Visually check on the exterior of the fuselage and make sure that
the APU exhaust duct is centered in the exhaust shroud duct, and that the
exhaust shroud duct is centered in the skin cutout for the APU exhaust.

530020 Task deleted (covered by task 530019). Structural Inspections

PATS APU GTCP36-150W. Every 3000 APU running hours.
APU Support Structure:
• Detail inspect all mounting parts for cracks or damage.
530021 Structural Inspections
• Detail inspect all fuselage attachments point for cracks or damage.
NOTE:
Repair as required.
TS APU GTCP36-150W. Every 4500 APU running hours.
NOTE:
Do this task in conjunction with the removal of the APU for the Hot
Section inspection (Out of Phase Task # 490006).
530022 Structural Inspections
• Remove and detail inspect the items listed in Table 1 (Located after
Area F4 inspections).
NOTE:
Replace all parts with the evidence of any damage.

Copyright © Textron Aviation Inc. Page 33 of 48

PATS APU GTCP36-150W. Every 4500 APU running hours.

NOTE:
Do this task in conjunction with the removal of the APU for the Hot
Section inspection (Out of Phase Task # 490006).
• Detail inspect the fuselage structure for cracks, particularly the support
530023 bracket attachment holes in the upper cap of the main engine cross Structural Inspections
beam and at the top and left side of the fuselage at frame 21.
NOTE:
The attachment brackets secured to the airframe will have to be removed
so that a detailed inspection of the holes drilled in the airframe for the
APU fitting can be done.
PATS APU GTCP36-150W. Every 22,500 APU running hours.
APU support hardware listed in Table 2 (Located after Area F4 inspections).
• Do a fluorescent penetrant inspection (FPI) (Ref. NTM 125, General
Techniques, Part C Liquid Penetrant).
OR
530024 Structural Inspections
• Replace.
NOTE:
FPI using MIL-1-25135C, Group 6A penetrant. Reject all linear
indications. Do this task in conjunction with the removal of the APU for
the Hot Section inspection (Out of Phase Task # 490006).
PATS APU GTCP36-150W. Every 10,000 flights.
Exhaust and inlet doubler frames and stringers.
• Detail inspect internally and externally for minute cracking conditions or
530025 Structural Inspections
other defects particularly near the exhaust.
NOTE:
Repair as required.
Between the 15 th and 18th year of aircraft operation and then every 8
years.
530026 External Baggage Unit (EBU) (750 airplanes ONLY) forward and aft attachment Structural Inspections
fittings:
• Do a detailed visual inspection.
Fuselage Skin.
530027 G
• Do a visual inspection.
Chapter 55- Stabilizers
Every 4 years.
Elevators and Tabs:
• Remove elevator (Ref. AMM 27-30-22, 401, select, 750, 800XP,
800XP/850XP Pro Line, 900XP).
• Detail inspect.
550001 • Inspect the bearings for smooth operation and replace as required. Structural Inspections
• Detail inspect the hinge brackets for security and cracks with a X 10
magnifier. Look for signs of corrosion.
• Install elevator (Ref. AMM 27-30-22, 401, select 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
Inspection completed at..................... Hrs. Date..........................

Copyright © Textron Aviation Inc. Page 34 of 48

Every 4 years.
Elevator trim tabs, connecting rods:
• Inspect the rod end bearings for smooth operation and replace as
required.
• Apply a coat of silicone lubricant to both exterior surfaces of the bearing
550002 Structural Inspections
at each connecting rod end (Ref. AMM 27-30-00, 301, select 750,
800XP, 800XP/850XP Pro Line 21 or 900XP).
NOTE:
The silicone lubricant is applied to give the rod end bearing protection
against corrosion.
8 years, then every 4 years.
Elevators.
Access: Refer to relevant NTM Technique.
550003 Structural Inspections
• Comply with instructions in NTM 55-20-101 and NTM 55-20-102.
• If corrosion is found extend the X-Ray coverage until a complete rib bay
is found to be free from corrosion.
Every 4 years.
Rudder and Tab:
• Remove (Ref. AMM 27-20-23, 301, select 750, 800XP, 800XP/850XP
Pro Line 21 or 900XP).
550004 • Detail inspect. Structural Inspections
• Inspect the bearings for smooth operation a replace as required.
• Install (Ref. AMM 27-20-23, 301, select 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP).

Every 4 years.
Connecting rods, rudder trim tab and anti-servo tab:
550005 Structural Inspections
• Inspect the rod end bearings for smooth operation and replace as
required.
8 years, then every 4 years.
Rudder.
550006 Access: Refer to NTM Technique. Structural Inspections
• Comply with instructions in NTM 55-40-101.
Every 8 years.
Rudder hinge brackets and attachments.
550007 Access: Rudder and rudder hinge bracket cover plates removed. Structural Inspections
• Detail inspect the rudder hinge brackets, using a X 10 magnifier.
Horizontal stabilizer to vertical stabilizer rear attachment fitting.
• Inspect for signs of corrosion, paying special attention to the condition of
550008 the outboard flanges and webs. F8
NOTE:
For corrosion limits refer to Beechcraft Corporation.

Copyright © Textron Aviation Inc. Page 35 of 48

Every 8 years.
Horizontal stabilizer.
Access: Leading edges removed. Elevators removed. Shroud panels T21R,
T22L, T23R, T24L, T25R, T26L and T45 removed. Fairing panels T4L, T4R, T5,
T6L, T7R, T8L, T9R and T13 removed.
• Detail inspect the front face of the front spar for cracks and signs of
corrosion.
• Detail inspect the rear face of the rear spar for cracks and signs of
550009 corrosion. Structural Inspections
• Detail inspect the vertical stabilizer to horizontal stabilizer attachment
fittings.
• Detail inspect the elevator hinge brackets.
• Apply Corrosion Preventive Compound (Ref. AMM 55-13-00, 301, select
800XP or 800XP/850XP Pro Line 21).
NOTE:
Application of Corrosion Preventive Compound is ONLY applicable to
the series 800XP and 800XP/850XP Pro Line 21 airplanes.
Between 15 to 18 years, then every 8 years.
Vertical stabilizer.
Access: Leading edge panels, upper vertical stabilizer and rudder removed.
• Detail inspect the structure rendered visible.
• Detail inspect the rudder hinge brackets for security, cracks and signs of
corrosion.
550010 • Comply with instructions in: Structural Inspections
• NTM 55-30-101.
• NTM 55-30-102.
• NTM 55-30-103.
• With the leading edge removed detail inspect the internal structure of the
vertical stabilizer for cracks and signs of corrosion using a borescope
probe through the access holes in the front spar and through the root rib.
16 years, then every 8 years (see NOTE).
Horizontal stabilizer to vertical stabilizer attachments. Horizontal stabilizer
removed.
NOTE:
Airplanes which have had the horizontal stabilizer removed at or
subsequent to the 12 year inspection can be considered to have
550011 satisfied the initial inspection requirement. Structural Inspections
• DETAIL INSPECT THE ATTACHMENT LUGS FOR CRACKS,
SIGNS OF CORROSION AND ELONGATION OF THE
ATTACHMENT BOLT HOLES.
• INSPECT THE BOLTS FOR SIGNS OF WEAR OR CORROSION.
• REPLACE ANY WORN BOLTS. IF HOLES ARE ELONGATED
REPLACE BOLTS, SEE SRM 55-10-41.

Copyright © Textron Aviation Inc. Page 36 of 48

24 years and then every 8 years.

Horizontal stabilizer.
Access: Refer to relevant NTM Techniques.
NOTE:
For convenience and improved access it is recommended that this
550012 inspection is done when the horizontal stabilizer is removed for the Structural Inspections
inspection of the attachment lugs (Task No. 550011).
• Comply with instructions given in one of the methods below:
• Fokker Bond Test, NTM 55-10-104A.
• Schlumberger Sonatest NTM 55-10-104B.
• Staveley Sonic Bondmaster NTM 55-10-104C.
Between 15 to 18 years, then every 8 years.
Horizontal stabilizer.
Access: Refer to relevant NTM Techniques.
• Comply with instructions in:
550013 Structural Inspections
• NTM 55-10-101.
• NTM 55-10-102.
• NTM 55-10-103.
• NTM 55-10-105.
15,000 flights and then at every X-Ray inspection of the horizontal
stabilizer internal structure (Task No.550013).
550014 Horizontal stabilizer top skin "T" fitting and joint strap at the center line of the Structural Inspections
stabilizer. Access: Upper vertical stabilizer removed.
• Detail inspect for cracks and signs of corrosion.

Copyright © Textron Aviation Inc. Page 37 of 48

Every 2 years.
Elevators:
• Remove and inspect mass balance weight side plates, look for signs of
corrosion (Ref. AMM 27-30-91, 601, select 750, 800XP, 800XP/850XP
Pro Line 21 or 900XP).
• Remove and inspect mass balance weights, spigots and installation,
look for signs of corrosion (Ref. AMM 27-30-91, 601, select 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
NOTE:
Remove all corrosion found from the spigots to a maximum depth of
0.03 in. and paint with epoxy primer (Ref. AMM 125/H-20, 20-95-401, Item
No. 474).
NOTE:
If excessive corrosion is found contact: Repair Design Office Beechcraft
Corporation 9709 East Central P.O. Box 85 Wichita, KS 67201-0085,
550015 Structural Inspections
U.S.A
• Assemble the spigots and mass balance weights (Ref. AMM 27-30-91,
601, select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
• Apply corrosion preventive compound LPS 3 (Ref. AMM 125/H-20, 20-
95-11, Item No. 089) or ACF 50 (AMM 125/H-20, 20-95-11, Item No.
090) (Ref. AMM 27-30-91, 601, select 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP).
• Install the side plate assembly (Ref. AMM 27-30-91, 601, select 750,
800XP, 800XP/850XP Pro Line 21 or 900XP).
NOTE:
The balance of the elevator must be checked and if necessary adjusted
only when a repair has been done or a paint finish changed.
CAUTION:
Make sure that the mass balance weights are installed on the same side
that they were removed from.
Chapter 56- Windows
560001 Task deleted. A1
560002 Task deleted. A2
560003 Task deleted. A3
Windows dry-air system filter (if fitted).
560004 • Inspect the filter element (Ref. AMM 56-00-00, select 750, 800XP, C6
800XP/850XP Pro Line 21 or 900XP).
Passenger cabin windows.
• Satisfactory condition of seals and no signs of moisture ingress.
• If you find moisture, renew Silica Gel crystals and verify seal integrity
560005 B3
(AMM 56-00-00).
NOTE:
Pre Mod. 25G360A ONLY.
Windshield panel 'C' Silica Gel container.
560006 • Inspect Silica Gel crystals for discoloration. B4
• Renew as necessary.

Copyright © Textron Aviation Inc. Page 38 of 48

Screen heat circuit breakers.

• Do a visual inspection for heat distress, discoloration and deformation
560007 F6
(Ref. AMM 30-41-001, 501 select 750, 800XP, 800XP/850XP, Pro Line
21 or 900XP).
Chapter 57- Wings
Flap hinge fittings.
Inspect.
NOTE:
Inspect the bolt head on the bottom skin of the flap (in the area of the
570001 inboard hinge) adjacent to flap screw jack carriage grease fitting for B9
damage caused by chafing. If damage is found, replace the bolt.
NOTE:
For details of the repair kit refer to Beechcraft Corporation Technical
Support (1.800.429.5372 OR 316.676.3140).
Flap hinge fittings.
Inspect.
NOTE:
Inspect the bolt head on the bottom skin of the flap (in the area of the
570002 inboard hinge) adjacent to flap screw jack carriage grease fitting for B10
damage caused by chafing. If damage is found, replace the bolt.
NOTE:
For details of the repair kit refer to Beechcraft Corporation Technical
Support (1.800.429.5372 OR 316.676.3140).
The internal structure of the wing in the area of Ribs 0 to 4.
• Detail inspect.
• Look for signs microbiological contamination and corrosion.
NOTE:
If corrosion or microbiological contamination is found:
• PROGRESSIVELY EXTEND THE DETAIL INSPECTION, BY
570003 VISUAL MEANS OR X-RAY TECHNIQUE, FORWARD OF THE F9
CENTRE SPAR AND OUTBOARD OF RIB 4 UNTIL A CLEAN BAY
RIB IS FOUND.
• REMOVE THE VENTRAL FUEL TANK (IF FITTED) AND DETAIL
INSPECT INTERNALLY.
• DO THE SHOCK PREVENTATIVE PROCEDURE (REF. AMM 28-10-
00, PAGE BLOCK 701).
Applicable to Mod. 259071A airplanes only.
Flap skin protection panels (if fitted).
Remove panels and inspect the flap skin for corrosion and deterioration of the
570004 protective treatment. F9
NOTE:
Mod. 259071A introduces protective skins on the flap inboard underside
for rough runway protection.

Copyright © Textron Aviation Inc. Page 39 of 48

The internal structure of the wing in the area of Ribs 0 to 4.

• Detail inspect.
• Look for signs microbiological contamination and corrosion.
NOTE:
If corrosion or microbiological contamination is found:
570005 • PROGRESSIVELY EXTEND THE DETAIL INSPECTION, BY VISUAL F10
MEANS OR X-RAY TECHNIQUE, FORWARD OF THE CENTRE SPAR
AND OUTBOARD OF RIB 4 UNTIL A CLEAN BAY RIB IS FOUND.
• REMOVE THE VENTRAL FUEL TANK (IF FITTED) AND DETAIL
INSPECT INTERNALLY.
• DO THE SHOCK PREVENTATIVE PROCEDURE (REF. AMM 28-10-
00, PAGE BLOCK 701).
Applicable to Mod. 259071A aircraft only.
Flap skin protection panels (if fitted).
Remove panels and inspect the flap skin for corrosion and deterioration of the
570006 protective treatment. F10
NOTE:
Mod. 259071A introduces protective skins on the flap inboard underside
for rough runway protection.
8 years, then every 4 years.
Wing bottom skins and stringers between the front and rear spars, Rib 0 to Rib
1 and between the center spar and rear spar from Rib 1 to Rib 4.
Access: Refer to NTM Technique.
• Comply with instructions in NTM 57-30-101.
• Detail inspect the bottom stringers in the vicinity of the wing skin restraint
ties with the aid of a flashlight and mirrors.
NOTE:
570007 If corrosion is found while doing NTM 57-30-101, extend the X-Ray Structural Inspections
coverage (NTM 57- 30-102) until a complete rib bay is found to be free
from corrosion.
NOTE:
If the quality of the radiographs is impaired by the presence of pockets
of fuel it would indicate that the internal fuel drain paths are blocked.
Operators are advised to remedy this condition at the first convenient
opportunity.

8 years, then every 4 years.

Main Landing Gear and sidestay attachment fittings. Access: Panels W324,
W424 removed.
570008 • Detail inspect the landing gear pick-up fittings, specially the sidestay Structural Inspections
pick-up, for cracks, signs of corrosion and signs of movement.
• Make sure the drain holes are unobstructed.
• Check the tightness of all securing bolts.
4800 flying hours, then every 1200 flying hours.
Wing bottom skin (LH and RH) adjacent to flap outboard hinge at Rib 8. Access:
570009 Hinge fairings, panels W314 and W414, removed. Structural Inspections
• Detail inspect for cracks and signs of corrosion.

Copyright © Textron Aviation Inc. Page 40 of 48

Every 4800 flying hours or 8 years, whichever is the sooner.

Wing front spar, forward face.
Access: Wing leading edges removed.
• Detail inspect for cracks, signs of corrosion and distortion, specially
between Ribs 1 and 3.
570010 Structural Inspections
• Inspect leading edges for cracks, signs of corrosion, damage and
integrity of the bolt holes.
NOTE:
When replacing the leading edges the profiles must be maintained (see
SRM 57-41-00).
4800 flying hours or 8 years, whichever is the sooner, then every 2400
flying hours or 4 years.
Wing rear spar, rear face.
570011 Access: Ailerons, aileron shrouds, flaps and airbrakes removed. Structural Inspections
• Inspect for cracks, signs of corrosion, distortion and damage.
• Inspect control surface hinge brackets on the rear spar for wear, cracks,
signs of corrosion and security.
4800 flying hours or 8 years, whichever is the sooner, then every 2400
flying hours or 4 years.
Airbrakes.
570012 Access: Airbrakes removed. Structural Inspections
• Detail inspect.
• Inspect the hinges for security.
Every 2400 flying hours or 4 years, whichever is the sooner.
Ailerons:
Remove (Ref. AMM 27-10-31, 401, select 750, 800XP, 800XP/850XP Pro Line
21 or 900XP).
570013 • Detail inspect. Structural Inspections
• Inspect the bearings for satisfactory condition and make sure there is
adequate lubrication (Ref. AMM 125/H-20, 20-09-22, 201).
• Install (Ref. AMM 27-10-31, 401, select 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP).

Every 2400 flying hours or 4 years, whichever is the sooner. Connecting

rods, aileron trim and servo tabs.
• Lubricate or replace the front and rear rod end bearings, as required
(Ref. AMM 125/H- 20, 20-09-22, 201).
• Apply a coat of silicone lubricant to both exterior surfaces of the bearing
570014 Structural Inspections
at each trim tab connecting rod end (Ref. AMM 27-10-00, 501, select,
750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
NOTE:
The silicone lubricant is applied to give the rod end bearing protection
against corrosion.
4800 flying hours or 8 years, whichever is the sooner, then every 2400
flying hours or 4 years.
Ailerons:
570015 Access: Refer to NTM Technique. Structural Inspections
• Detail inspect the hinge brackets with a X 10 magnifier.
• Comply with instructions in NTM 57-50-107.

Copyright © Textron Aviation Inc. Page 41 of 48

4800 flying hours or 8 years, whichever is the sooner, then every 2400
flying hours or 4 years.
Flaps and flap vanes.
Access: Refer to relevant NTM Technique.
• Inspect hinge brackets for security, freedom from cracks and signs of
570016 corrosion. Structural Inspections
• Inspect bearings for satisfactory condition and adequate lubrication.
• Comply with instructions in NTM 57-50-105 and NTM 57-50-106.
NOTE:
If corrosion is found during the X-Ray inspection, extend the X-Ray
inspection coverage until a complete rib bay is found free of corrosion.
24,000 flying hours and then every 4800 flying hours.
Wing bottom skin at attachment to front spar, between Ribs 1 and 7. Access: As
570017 visible. Structural Inspections
• Detail inspect for cracks and signs of corrosion.
24,000 flying hours and then every 9600 flying hours.
570018 Wing bottom skin centerline joint strap. Access: Keel skid removed. Structural Inspections
• Detail inspect for cracks and signs of corrosion.
24,000 flying hours and then every 9600 flying hours.
Upper surface of the wing bottom skin at the attachment to the centerline joint
adjacent to Rib 0. Access: Refer to NTM Technique.
• Comply with instructions in NTM 57-30-104.
570019 OR Structural Inspections
24,000 flying hours and then every 7200 flying hours.
• With the sealant removed to expose the skin surface, detail inspect for
cracks at the bolt line.
24,000 flying hours and then every 12,000 flying hours.
Wing bottom skin centerline butt strap and center section beams (24 positions).
570020 Access: Refer to NTM Technique. Structural Inspections
• Comply with instructions in NTM 57-00-102.

Whenever the wings are separated from the fuselage.

Wing top skin in the area that is covered by the fuselage structure and main
attachment brackets. Access: Wings separated from the fuselage.
570021 • Detail inspect the skin, stiffeners and main attachment brackets for Structural Inspections
cracks, signs of corrosion, security of rivets and damage.
• Inspect the drag spigot for wear.
• Inspect the spigot location plate for security of attachment.
Every 4800 flying hours.
Rear spar, rear face between Rib 1 LH and Rib 1 RH.
570022 Access: Main landing gear doors and panels W325, W425, W507 and W508 Structural Inspections
removed.
• Detail inspect the rear face of the rear spar.

Copyright © Textron Aviation Inc. Page 42 of 48

Every 4 years.
NOTE:
Applicable to airplanes without BC Winglets.
Aileron horn balance weight.
570023 Access: Aileron horn balance weight cover removed. Structural Inspections
• Detail inspect the horn balance weight for signs of corrosion.
• If signs of corrosion are found, then do an X-Ray inspection of the area.
• Comply with instructions in NTM 57-50-107.
12,000 flying hours, then every 7200 flying hours.
570024 Wing bottom skin at attachment to Rib 1 LH and RH. Access: As visible. Structural Inspections
• Detail inspect the skin where it is bolted to Rib 1 LH and RH.
Every 4800 flying hours.
Wing bottom skin at attachment to the rear spar, between Rib 1 LH and Rib 1
RH.
570025 Access: Main landing gear doors open and keel skid fairing in the area of the Structural Inspections
main landing gear doors removed.
• Detail inspect the skin where it is bolted to the rear spar, between Rib 1
LH and Rib 1 RH.
Every 4 years.
Wing leading edges.
570026 Access: TKS panels removed (also any material that might interfere with visual Structural Inspections
inspection). Inspect, specifically rebate area for cracks and signs of corrosion
(Ref. SRM 57-41-12, 201).

Copyright © Textron Aviation Inc. Page 43 of 48

Every 4800 flying hours or 8 years, whichever is the sooner.

Wing internal structure forward of the center spar including the front and center
spars from Ribs 0 to 4, and between and including the front and rear spars from
Rib 4 to the wing tip.
Access: Wing leading edges W102, W120, W130, W202, W220,W230
removed. Front spar access panels W301, W302, W303, W304, W305, W401,
W402, W403, W404, W405 removed.
Rear spar access panels W115, W116, W117, W215, W216, W217 removed.
NOTE:
Rear spar access panels W114 and W214 need not be removed for this
inspection unless required for other work in the area.
Top skin panels W106, W108, W112, W119, W206, W208, W212, W219
removed.
Bottom skin panels W306, W308, W309, W310, W312, W313, W329, W330,
570027 W406, W408, W409, W410, W412, W413, W429, W430 removed. Structural Inspections
• Detail inspect the internal structure, as visible.
• Inspect for signs of corrosion and microbiological contamination.
• Detail inspect the bottom stringers in the vicinity of the wing skin restraint
ties with the aid of a flashlight and mirrors.
NOTE:
If corrosion or contamination is found, clean and repair in accordance
with the Structural Repair Manual. Do the shock preventative treatment
(Ref. AMM 28-10-00, 701, select 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
Fuel system non-return valves in inner and outer wings.
• Remove and inspect (Ref. AMM 28-20-32, 401, select 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
• Pay particular attention to the condition of the valve and valve seat.
4800 flying hours or 8 years, whichever is the sooner, then every 4
years.
NOTE:
Applicable to airplanes without BC Winglets.
570028 Aileron at outboard hinge casting. Structural Inspections
• Do the "Aileron Horn" Inspection/Check: 750 (Ref. AMM 27-10-31, 601),
800XP (Ref. AMM 27-10-31, 601) and
800XP Pro Line 21 (Ref. AMM 27-10-31, 601).
Applicable to Airplanes with BC Winglets. Every 300 hours.
Wing Outer, Upper and Lower Skins.
• Visually inspect between Ribs 14 and 16 around the fasteners for
570029 cracking in the skins. Out of Phase
NOTE:
Pay particular attention to those fasteners installed between the front
and rear spars.
Applicable to Airplanes with BC Winglets.
Rib 16 and spar fitting where the winglet is attached to the wing.
Access: Remove winglet (SRM 57-30-12, 201)
570030 NOTE: F9
It is recommended to re-apply the corrosion preventive treatment every 2
years.
Refer to SRM 5710-19, 201 and inspect for signs of corrosion. If corrosion is
found, and beyond limits, contact Repair Design Office or replace the rib.

Copyright © Textron Aviation Inc. Page 44 of 48

Applicable to Airplanes with BC Winglets.

Rib16 and spar fitting where the winglet is attached to the wing.
Access: Remove winglet (SRM 57-30-12, 201)
NOTE:
570031 It is recommended to re-apply the corrosion preventive treatment every 2 F9
years.
Refer to SRM 57-10-19, 201 Refer to SRM 57-10-19, 201 and inspect for signs
of corrosion. If corrosion is found, and beyond limits, contact Repair Design or
replace the rib.and inspect for signs of corrosion. If corrosion is found, and
beyond limits, contact Repair Design or replace the rib.
Chapter 70- Standard Practices Engine
NOTE:
No Chapter 70 tasks at this time.
Chapter 71- Power Plant - General
NOTE:
No Chapter 71 tasks at this time.
Chapter 72- Engine
720001 Task deleted - covered by Out of Phase task 240001. A6
Whenever an engine is removed for a Major Periodic Inspection.
720002 Aft cowling, inner fan duct and exhaust duct. Out of Phase
Inspect with the aft cowling removed.
Whenever an engine is removed for a Major Periodic Inspection.
Exhaust nozzle/exhaust pipe V clamp.
720003 Out of Phase
Detail inspect, particularly for cracks in the weld lines of the trunnion nut support
tubes, using a X 10 magnifier.
Chapter 73 - Engine - Fuel & Control
PT2 pipelines to fuel computers.
730001 B7
Drain any accumulations of water from the drain points.
Chapter 74 - Engine Ignition
NOTE:
No Chapter 74 tasks at this time.
Chapter 75 - Engine Air
NOTE:
This task is only applicable to Hawker 900XP airplanes.
Engine Bleed System.
750001 B11
• Inspect the bleed air port low pressure (LP) venturi gasket for signs of
deterioration, deep discoloration, cracks or missing pieces of gasket
and replace as necessary.

Chapter 76 - Engine Controls

Throttle lever controls.
• Correct operation of the gust lock operated thrust lever baulk. (Ref. AMM
760001 B4
27-72-00, 501, select 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
Engine power control cables.
760002 C5
• Check cable tensions are correct (Ref. AMM 76-10-00).

Copyright © Textron Aviation Inc. Page 45 of 48

After 200 flying hours and not more than 300 flying hours after control cable
replacement.
Control cables.
760003 Check the tensions of the: Out of Phase
• Power control cables (Ref. AMM 76-10-00, 501, select 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
Do any lubrication requirement for Area M1/M2, refer to Part 7 -
760004 Out of Phase
LUBRICATION.Lubrication.
Chapter 77 - Engine Indicating
NOTE:
No Chapter 77 tasks at this time.
Chapter 78 - Engine Exhaust
Link arm assemblies (8 off).
• Remove the link arms (Ref. AMM 78-31-10).
• Inspect the attachment bolts (16 off), particularly for signs of corrosion
and/or seizing.
780001 • Replace any bolts that show signs of corrosion and/or seizing. B11
• Lubricate the bolt shafts and threads before installation, using a dry film
lubricant to specification MIL-PRF-907, C5-A (non-aerosol) Item 084
(Ref. AMM 20-95-11).
• Install the link arms (Ref. AMM 78-31-10).
Reverser door seals.
• Inspect for correct seating (Ref. AMM 78-31-20).
780002 B11
• Inspect for cracks and wear.
• Make sure the material is pliable.
Thrust reverser stow/deploy microswitches.
780003 • Test microswitches coded CWA or CXA (Ref. AMM 78-34-20, 201, C4
select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
Pylon skin panels.
780004 C11
• Remove the panels, inspect the fasteners and attachments.
Door link rods and pivot brackets.
780005 C11
• Detail inspect (Ref. AMM 78-31-10, 601).
Thrust reverser lever baulk mechanism.
• Deploy each thrust reverser in turn.
• Make sure that the baulk release lever of the reverser system which is
780006 D4
not deployed stays down and does not show any tendency to lift when the
solenoid of the deployed system is energized.
• Return both thrust reverser to the stowed position.
780007 Task deleted. B1
780008 Task deleted. A1

Copyright © Textron Aviation Inc. Page 46 of 48

Thrust Reversers.
• Inspect the afterbody and make sure it is correctly attached.
• Inspect the doors for corrosion and wear.
780009 • Detail inspect the doors for cracks. B11
• Inspect the fan flaps for signs of fatigue and make sure they are correctly
attached and stow completely.
• Detail inspect the fan flaps for cracks.
Thrust Reversers.
• Inspect the hydraulic lines for signs of leakage.
780010 B7
• Inspect the wire harness for any chaffing in the area of the hydraulic
control valve.
Exhaust nozzle.
780011 B11
• Detail inspect for cracks.
Hydraulic Lines.
• Make sure the hydraulic lines are correctly attached.
780012 B11
• Inspect for leaks.
• Inspect the sleeving material for signs of chafing.
Wire harness.
• Make sure the wire harness in the thrust reverser and afterbody is
780013 B11
correctly attached.
• Inspect for signs of chafing.
Fan duct.
• Inspect for signs of corrosion and fatigue.
780014 B11
• Detail inspect for cracks.
• Inspect the contour and general condition of the fan duct fairings.
Latch box springs.
780015 • Inspect for signs of fatigue. B11
• Detail inspect for cracks.
Latch monitoring switches.
780016 B11
• Do an operational test (Ref. AMM 78-33-50, ADJUSTMENT/TEST).
Latches and latch receptacles.
780017 B11
• Inspect for wear (78-31-35, INSPECTION/CHECK).
Primary (Ref. AMM 78-32-40) and Latch (Ref. AMM 78-32-50) hydraulic
actuators.
780018 B11
• Inspect for leaks, corrosion or wear.
• Detail inspect for cracks.
Throttle Retard hydraulic actuators (Ref. AMM 78-32-30).
• Inspect for leaks, corrosion or wear.
780019 B11
• Detail inspect for cracks.
• Detail inspect the actuator housing at the bearing on the Throttle Retard.
Fan Flap hydraulic actuators (Ref. AMM 78-32-60).
• Inspect for leaks, corrosion or wear.
780020 B11
• Detail inspect for cracks.
• Detail inspect the actuator housing at the bearing on the Fan Flap.

Copyright © Textron Aviation Inc. Page 47 of 48

Pylon Plug.
780021 • Make sure the pylon plug fairings M17L and M18R are correctly installed B11
and make a continuous surface with the pylon.

NOTE:
This task is NOT APPLICABLE to Series 750 and 900XP Airplanes.
Door link rods (Part No. 5453003-7 link rods only) .
780022 C11
• Do a thickness check, Link rod - corrosion removal limits). 800XP
airplanes (Ref. AMM 78-31-10, 601). 800XP/850XP Pro Line 21
airplanes (Ref. AMM 78-31-10, 601).
Bonding Straps - 900XP Airplanes.
NOTE:
The Bonding Straps run from the after-body bolt circle to an attachment
point inside the pylon.
780023 Door link rods (Part No. 5453003-7 link rods only) . C11
• Check for corrosion, arcing, wear or fretting.
• Make sure the end connections are tight to the mounting attachment
points.

Chapter 79 - Engine Oil

NOTE:
No Chapter 79 tasks at this time.
Chapter 80 - Engine Starting
NOTE:
No Chapter 80 tasks at this time.

Copyright © Textron Aviation Inc. Page 48 of 48

MANDATORY LIFE LIMITATIONS

1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

For the Mandatory Life Limitations for this aircraft refer to the Airworthiness Limitations Document, Reference CJE-HPA-C-GEN-
AW1667.

Copyright © Textron Aviation Inc. Page 1 of 1

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:40:28 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-11-01 (Rev A0)

COMPONENT REQUIREMENTS
1. General
List of Effective Pages
Pages 1 thru 8, Issued Sep.16

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.

Component Part No. Manufacturer Period Test Repl O/H

Air Conditioning
Non-return valve AWE124-51 AWE124- Hymatic Engineering Redditch, 12,000 hrs *
main air supply to 51A AWE124-51-2 UK
cabin
Switches, bleed air 156D** Kidde Graviner 4 - 5 years *
over temperature 53183* 4 - 5 years *
Communications
NOTE:
Overhaul periods for communications equipment are subject to negotiation between individual operators and their
Regulatory Authority, unless listed below. For the manufacturers recommended overhaul periods for communication
equipment, refer to the relevant CMM.
Cockpit voice 93-A100-30 Fairchild Industrial Products 8000 hours *
recorder, model
A100A
Underwater locator 266-E0305-00 Fairchild Industrial Products 2 years *
beacon
Underwater locator 266-E0305-00 Fairchild Industrial Products 6 years *
beacon
Underwater locator DK100DK120 Dukane Corporation 2 years *
beacon
Underwater locator DK100DK120 Dukane Corporation 6 years *
beacon
NOTE:
Underwater Locator Beacons can be installed on Cockpit Voice Recorders and Flight Data Recorders.
Underwater locator ULB Part No. 15957 Fairchild Industrial Products 2 years *
beacon - battery
NOTE:
For the ULB Part No. 266-E0305-00 the ULB has to be returned to the manufacturers for the battery to be replaced. For
the earlier type ULB Part No.15957 the replacement batteries can be obtained from the manufacturers.
Battery kit, fitted to B362-06192 RJE International Inc. and 6 years *
Underwater Locator Datasonics Inc.)
Beacon ELP-362D.
Emergency locator As installed NOTE:
transmitter Service/Replace in accordance with the
manufacturer's servicing instructions.

Copyright © Textron Aviation Inc. Page 1 of 6

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:40:29 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-11-01 (Rev A0)

Emergency locator As installed

transmitter battery
pack

Electrical Power
Contactor, inverter LDA200-B18C Lucas Aerospace Ltd., 5000 hrs *
supply Electrical Division
Contactor, bustie LDA150A-8C Lucas Aerospace Ltd., 5000 hrs *
Electrical Division
Contactor, ground LDG150Y4 Lucas Aerospace Ltd., 6000 hrs *
supply Electrical Division
Starter/generator, 23080-005 Lucas Aerospace Power 1000 hrs *
main engines Equipment Corporation, 777
Lena Drive, Ohio, USA
Starter/generator, 23080-064 Lucas Aerospace Power 1000 hrs *
main engines Equipment Corporation, 777
Lena Drive, Ohio, USA
Starter/generator, 140-380026-1 Lucas Aerospace Power 1000 hrs *
main engines Equipment Corporation, 777
Lena Drive, Ohio, USA
Starter/generator, 23080-005 23080-064 Lucas Aerospace Power 1000 APU running *
auxiliary power unit Equipment Corporation, 777 hrs
Lena Drive, Ohio, USA
Frequency wild A.C. BA02801-1 Lucas Aerospace Ltd., 3000 hrs or 8 years *
generator Electrical Division
Main aircraft As installed NOTE:
batteries Service/Replace in accordance with the
manufacturer's instructions.
Aircraft emergency As installed NOTE:
batteries Service/Replace in accordance with the
manufacturer's instructions.
Internal Avionics As installed NOTE:
batteries Service/Replace in accordance with the
Avionics manufacturer's instructions.
Equipment/Furnishings
Life jackets 102MK2BA RFD Inflatables Ltd. 2 years 4 years 1 * **
(manufactured year
before March 1980)
NOTE:
The overhaul period of 4 years is subject to a satisfactory examination of one pack after 2 years. From 9 years onwards
ALL packs must be overhauled every year.
Life jackets 102MK2BA RFD Inflatables Ltd. 2 years 5 years 1 * **
(manufactured after year
March 1980)
NOTE:
The overhaul period of 5 years is valid from the date of manufacture up to 20 years subject to a satisfactory
examination of one pack every 2 years. After 20 years the overhaul period changes to every year.
Fire Protection

Copyright © Textron Aviation Inc. Page 2 of 6

Fire extinguisher, 33200002 33200002- HTL Industries Inc. 10 years from date *
main engine 3 33200009 of filling
33200009-3

Fire extinguisher, 30402104 HTL Industries Inc. 4 - 5 years from date *

APU of filling
Fire extinguisher, 4190-* Meggitt/Whittaker/Systron 4 - 5 years from date *
APU Donner of filling
Fire extinguisher, 30300106-1 HTL Industries Inc. 4 - 5 years from date *
External baggage of filling
unit (EBU)
APU fire warning 17343* Fenwell 4 - 5 years *
switches
APU fire warning 160275-1 Sundstrand 4 - 5 years *
switch
APU generator 67100* Fenwall 4 - 5 years *
overheat switch
Overheat detection 150D01* Graviner (Colnbrook) Ltd. 4 - 5 years *
switches
Overheat detection 53182*17343* Fenwall 4 - 5 years *
switches
Flight Controls
Flap control unit, CHA614-001/2 Lucas Aerospace Ltd., 6000 landings *
Type 614 Mk 2 Actuation Division
Receiver unit, flap CHA617-104 Lucas Aerospace Ltd., 4500 landings *
synchronizing Actuation Division
system, Type 617
Mk. 4
Flight Controls (Cont.)
Flap screw jacks 25-8CW159* 25- Textron Aviation Inc. 4000 landings *
and reduction 8CW161*
gearboxes
Air brake jacks AIR46520* AIR46521* AP Precision Hydraulics 3000 hrs *
Fuel
Fuel pump, Type 2070C01 2070C11 Intertechnique S.A. 4000 hrs *
20700-01
Hydraulic Power
Full flow relief valve AIR45394 AP Precision Hydraulics 4500 flts *
Pressure AIR45474 AP Precision Hydraulics 5000 flts *
maintaining valve
Pressure switch TP42001 Thermal Control Company Ltd. 5000 hrs *
emergency brakes
LP warning
Instruments
Fatigue meter (if M1946 Negretti and Zambra 30,000 counts or 2 *
fitted) years from
installation

Copyright © Textron Aviation Inc. Page 3 of 6

Landing Gear
NOTE:
The calendar start time for the BC manufactured Landing Gear components may be based on the date of release for
service following aircraft completion, up to a maximum of three months from the date of original aircraft certification.
Main lega ssembly 25-8UM1-* Textron Aviation Inc. 5000 landings OR *
259W02333-* 25- 12 years, whichever
8UM523-* comes first.
Main leg assembly 140-810044-* Beechcraft Corporation 5000 landings OR *
12 years, whichever
comes first.
Side stay assembly 25-8UM3-* Textron Aviation Inc. 5000 landings OR *
12 years, whichever
comes first.
Landing Gear (Cont.)
Side stay assembly 140-810043-* Beechcraft Corporation 5000 landings OR *
12 years, whichever
comes first.
Nose leg assembly 25-9UN1-* Textron Aviation Inc. 5000 landings OR *
12 years, whichever
comes first.
Nose landing gear 25-8UN3-* Beechcraft Corporation 5000 landings OR *
drag stay assembly. 12 years, whichever
comes first.
Reversing valve AIR48542 AIR48543 AP Precision Hydraulics 5000 landings OR *
12 years, whichever
comes first.
Sequence valve AIR48540* AP Precision Hydraulics 5000 landings OR *
12 years, which ever
comes first.
Main gear jack AIR48502* AIR48503* AP Precision Hydraulics 5000 landings *
Nose gear jack AIR45404* AP Precision Hydraulics 5000 landings *
Main gear door AIR48484 AIR48485 AP Precision Hydraulics 5000 landings *
jacks
Maxaret unit AC65216 AC65218 Dunlop Limited, Aviation 3000 landings *
Division
Pressure switch TP42000 Thermal Control Company Ltd. 5000 hrs *
emergency brakes
system
Lights

Copyright © Textron Aviation Inc. Page 4 of 6

NOTE:
Accomplish replacement/hardtime restoration as required by this section using any one of the following methods:
• Operators may replace the strobe flash tube or strobe light flash tube assembly in accordance with Honeywell
Grimes Component Instructions.
• OR send the strobe light assembly to Honeywell Grimes for hardtime restoration or overhaul.
NOTE:
If the strobe light replacement/hardtime restoration is not accomplished, the strobe light must be intensity tested once
the initial replacement/hardtime hours are met and then every 400 ± 50 hours thereafter, or until the strobe light no
longer meets the requirements of intensity or flash rate, in which case comply with the previous NOTE.
NOTE:
Use Devore Flash Gun Model 4400D or equivalent American Aerospace Model ST-4000 for testing strobe light flash
intensity.

Strobe light Pre Mod.253262A31- Honeywell Grimes 1500 hrs. * * *

assembly - Wings 2059-11 (100 effective
30-0538-7/-8 candle power)
Strobe light Mod. 253262A31- Honeywell Grimes 2000 hrs. * * *
assembly - Wings 3078-19 (100 effective
30-1617-1/-2 candle power)
Strobe light - Wings 01-0770935-01 01- Whelen 2000 hrs. * * *
0770935-02
(Alternate)
(100 effective candle
power)
Strobe light Pre Mod 253262A31- Honeywell Grimes 1500 hrs. * * *
assembly - Tail 30- 1840-1 (100 effective
0531-1 candle power)
Strobe light Mod. 253262A31- Honeywell Grimes 1500 hrs. * * *
assembly - Tail 30- 3172-43 (100 effective
0876-1 candle power)
Strobe light 31-1748-1 (100 Honeywell Grimes 1500 hrs. * * *
assembly - Tail 30- effective candle power)
0516-1
Lights (Cont.)
Escape Hatch 2821003 132848-11 SRB Technologies (Canada) 6 years from date of *
Betalight "Exit" sign Inc. manufacture.
NOTE:
Escape hatch Beta lights that have exceeded the replacement period have 24 months to comply with the vendor
recommendations.
Navigation
NOTE:
Overhaul periods for navigation systems transmitters and receivers are to be subject to negotiation between individual
operators and their regulatory authority.
Elevator trim servo 622-3260-001 Rockwell International, Collins 3500 hrs. *
motor General Aviation Division.
Oxygen
Oxygen cylinder WKA37447 The Walter Kidde Co. 4 - 5 years *

Copyright © Textron Aviation Inc. Page 5 of 6

Oxygen cylinder, ZP650 Puritan-Zep Aero systems. 4 - 5 years *

portable
Crew masks MC10-** EROS, France. 6 years *
Crew masks MF10-** EROS, France. 6 years *
Passenger Masks C351-2000* B/E Aerospace/Puritan Bennet. 6 years *
Passenger Masks 289-601* Scott Refer to the vendor CMM 35-22-26 for the installed
unit.
Passenger Masks As applicable to the As applicable to the installed Refer to the vendor MM for the installed unit.
installed unit. unit.
Crew masks As applicable to the As applicable to the installed Refer to the vendor MM for the installed unit.
installed unit. unit.
Auxiliary Power Unit
APU As applicable to the As applicable to the installed Refer to the vendor MM, for the installed unit.
installed unit. unit.

Copyright © Textron Aviation Inc. Page 6 of 6

PRE FLIGHT INSPECTION - 050001

1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the Introduction section at the
front of this schedule.

Completion of Inspection
Aircraft registration: Engine Serial No:
Aircraft total airframe hours: Engine total running hours:
Date of completion of inspection:
Checked by: License # :

All Areas. Access: As visible.

Aircraft Registration: Total Airframe Hours: Mechanic Inspector
For the Pre-Flight Inspection procedures refer to the Hawker
800XP Ground Handling Checklist, P/N 140-590032-0025.

Copyright © Textron Aviation Inc. Page 1 of 1

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Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-20-02 (Rev A0)

POST FLIGHT INSPECTION - 050005

1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the Introduction section at the
front of this schedule.

Completion of Inspection
Aircraft registration: Engine Serial No:
Aircraft total airframe hours: Engine total running hours:
Date of completion of inspection:
Checked by: License # :

All Areas. Access: As visible.

Aircraft Registration: Total Airframe Hours: Mechanic Inspector
For the Post-Flight Inspection procedures refer to the Hawker
800XP Ground Handling Checklist, P/N 140-590032-0025.

Copyright © Textron Aviation Inc. Page 1 of 1

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:40:31 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-20-03 (Rev A0)

TFE731 ENGINE INSPECTIONS - 050010

1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Sep.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the Introduction section at the
front of this schedule.

Completion of Inspection
Aircraft registration: Engine Serial No:
Aircraft total airframe hours: Engine total running hours:
Date of completion of inspection:
Checked by: License # :

All Areas. Access: As visible.

Aircraft Registration: Total Airframe Hours: Mechanic Inspector
Engine General
Refer to the Honeywell Light Maintenance Manual for ALL routine
and Out of Phase inspection requirements for the TFE731-5BR-
1H or the TFE731-50R-1H engines, as applicable.

Copyright © Textron Aviation Inc. Page 1 of 1

APU INSPECTION - 050020

1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the Introduction section at the
front of this schedule.

Area F4: Rear equipment bay and rear fuselage. Access: Rear equipment bay door open.
Aircraft Registration: Total Airframe Hours: Mechanic Inspector
Auxiliary Power Unit
050181 For ALL Routine and Out of Phase servicing
requirements for the Sundstrand APU, refer to SB-T-
62T-49-77 and the Turbomach APU Maintenance
Manual. For Routine and Out of Phase servicing
requirements for the PATS APU Installation (STC #
ST00459NY), refer to this AFMS.

Copyright © Textron Aviation Inc. Page 1 of 1

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:40:32 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-20-05 (Rev A0)

200 HOUR LUBRICATION - 050030

1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

General Lubrication
Aircraft Registration: Total Airframe Hours. Mechanic Inspector
Lubrication - ALL Area's
120001 Do any 200 hour lubrication requirements for ALL
Area's, refer to Chapter 5, Lubrication.

Copyright © Textron Aviation Inc. Page 1 of 1

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:40:33 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-20-06 (Rev A0)

400 HOUR LUBRICATION - 050770

1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

General Lubrication
Aircraft Registration: Total Airframe Hours. Mechanic Inspector
Lubrication - ALL Area's
120060 Task deleted, covered by tasks 120003, 120004
and 120007.
120003 Do any 400 hour lubrication requirements for Area
F1, refer to Chapter 5, Lubrication.
120004 Do any 400 hour lubrication requirements for Area
T1, refer to Chapter 5, Lubrication.
120005 Task deleted.
120007 Do any 400 hour lubrication requirements for Area
W1/W2, refer to Chapter 5, Lubrication.

Copyright © Textron Aviation Inc. Page 1 of 1

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:40:34 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-20-07 (Rev A0)

400 HOUR DETAILED WALK-AROUND INSPECTION - 050771

1. Inspection
List of Effective Pages
Pages 1 thru 16, Issued Mar.16

Instructional Data
NOTE:
Refer to the Hawker 750/800XP/850XP/900XP Ground Handling Checklist for information concerning area locations.
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

A. Preparation
Check Comments
1 Flaps and airbrakes in "Lift Dump" (Area E and N).
2 Release Accumulator Hydraulic Pressure (Area K) (Ref. 12-29-00, 301
in the applicable maintenance manual 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP).
3 Electrical power "OFF" (ALL areas except P) (Ref. 24-01-00, 201 in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line
21 or 900XP).
4 Nose landing gear doors open (Area C) (Ref. 32-20-42, 301 in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line
21 or 900XP).
NOTE:
When releasing doors ensure the doors open a small amount and
then can be completely opened with minimal resistance.
5 Main landing gear doors open (Area F and M) (Ref. 32-10-01, 201 in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line
21 or 900XP).
6 Control locks removed (Area O).
7 Nose and main landing gear pins installed (Areas C, F and M) (Ref. 10-
00-00, 201 in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).

B. Left Nose and Fuselage

050772 Check Comments
1 Make sure the stall detector vane moves freely through the full range of
travel. Vane movement must be smooth and damped. Check vane
condition.
2 Check pitot tube condition, and sense port and drain holes are clear.

Copyright © Textron Aviation Inc. Page 1 of 10

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:40:35 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-20-07 (Rev A0)

3 Check static plate and static ports for condition; free from dents,
corrosion, contaminants and obstructions.

4 Check O.A.T. sensor probe for condition.

5 Check ice detector for condition and rotor movement.
6 Check external fuselage and flight compartment windows for damage.
Check windscreen weather seal for condition.
7 Check nose skin forward of static plate, free from dents, paint bubbles
and sealant bulges.
8 Make sure the avionics access panel (if fitted) is correctly seated and
secure (Ref. AMM 34-11-29, 601, in the applicable maintenance
manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
9 Check radome for condition and security.
10 Check condition of nose taxi light lens and bulbs (Left and Right).

C. Nose Landing Gear and Bay

050773 Check Comments
1 Check overall condition of NLG bay.
2 Make sure there is no visible damage to doors, nose gear assembly or
wheels.
3 Check the nose gear bay to make sure there is no fluid leakage greater
than the AMM tolerance.
4 Check condition of nose gear door bond straps.
5 Check condition of wiring and hoses.
6 Check the auxiliary hydraulic system reservoir for correct fluid level (Ref.
AMM 12-29-00, 301, in the applicable maintenance manual 750,
800XP, 800XP/850XP Pro Line 21 or 900XP).
7 Close nose landing gear doors and check that manual release is secure
(Ref. AMM 32-20-42, 301, in the applicable maintenance manual 750,
800XP, 800XP/850XP Pro Line 21 or 900XP).
8 Visually check the strut for normal condition and leakage (Ref. AMM 12-
32-00, 301, in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
9 Check tires for condition and pressure (Ref. AMM 12-32-00, 301, in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line
21 or 900XP).
10 Check the left and right door operating strut bearings for freedom of
movement by twisting the strut using finger pressure only. If the bearings
cannot be rotated replace as required.

D. Right Nose and Fuselage

050774 Check Comments
1 Check pitot tube condition, and sense port and drain holes are clear.
2 Make sure the stall detector vane moves freely through the full range of
travel. Vane movement must be smooth and damped. Check condition
of vane.

Copyright © Textron Aviation Inc. Page 2 of 10

3 Make sure the avionics access panel (if fitted) is correctly seated and
secure (Ref. AMM 34-11-29. 601, in the applicable maintenance
manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).

4 Check nose skin, forward of static plate, free from dents, paint bubbles
and sealant bulges.
5 Check static plate and static ports for condition; free from dents,
corrosion, contaminants and obstructions.
6 Check external fuselage and flight compartment windows for damage.
Check windscreen weather seal for condition.
7 Check antennas are secure and undamaged.
8 Airplanes without the digital pressurization control system Mod.
25G726A/C or Mod. 25G726B/C:
Make sure Cabin venturi outlet is clear.
9 Check external fuselage and windows for damage.
10 Check overwing emergency exit closed and flush with fuselage.
11 Check condition of overwing fillet fairing seal.
12 Check S.A.T. sensor for condition.

E. Right Wing
050775 Check Comments
1 Check condition of wing ice light and lens.
2 Make sure all water has been drained from the center fuel tank and
lock sump (Ref. AMM 12-28-00, 301, in the applicable maintenance
manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
3 Check the condition of the external upper surface structure of the wing
to make sure it is clean and undamaged (no fuel leaks).
4 Check the condition of the external lower surface structure of the wing
to make sure it is clean and undamaged (no fuel leaks).
5 Check stall strip and vortilon, for damage and condition.
6 Check landing and taxi lights for condition of lens and bulbs.
7 Check wing leading edge and TKS panel for damage and sealant for
condition.
8 Check vortex generators for dents and straightness and overwing fuel
cap for security.
9 Make sure the stall warning system vent (if fitted) is clear, free of
foreign objects and fuel leaks.
10 Make sure the NACA vent is clear.
11 Check vent surge tank is drained and locked.
12 Check condition of strobe and navigation lights and lens.
13 Check condition of wing tip.
14 Check condition of wing tip static wick.
15 Check condition of aileron and aileron trim tab.
16 Check condition of aileron and trim tab bond straps.
17 Check condition of aileron and trim tab static wicks.

Copyright © Textron Aviation Inc. Page 3 of 10

18 Make sure there are no foreign objects in the aileron shrouds.

19 Make sure the aileron and trim tab move freely through the full range
of travel.
20 Check condition of flap and air brakes. Make sure that there is no
damage to upper and lower surfaces.
21 Check flap for damaged or missing static wick.
22 Check condition of flap and air brake bond straps.
23 Check Flap bay overall condition and for hydraulic leaks.

F. Right Main Landing Gear

050776 Check Comments
1 Visually check the strut for normal condition and leakage (Ref. AMM 12-
32-00, 301, in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
2 Check tires for condition and pressure (Ref. AMM 12-32-00,301, in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line
21 or 900XP).
3 Check the main wheel tie bolt nuts for evidence of loosening.
4 Check the extension of the brake wear indicators (Ref. AMM 32-40-114,
601, in the applicable maintenance manual 750, 800XP, 800XP/850XP
Pro Line 21 or 900XP).
5 Make sure there is no visible damage to the main landing gear fairing
and doors.
6 Check condition of gear door bond straps.
7 Check the main gear and inside the main gear bay to make sure there is
no fluid leakage or damage.
8 Check condition of wiring and hoses.

G. Right Engine and Nacelle

050777 Check Comments
1 Make sure the starter generator cooling intake and outlet is
unobstructed.
2 Check the engine intake for damage and foreign objects.
3 Make sure there is no damage to the fan blades when viewed
through the engine intake.
4 Check P2T2 sensor clean, undamaged and secure.
5 Check general condition of cowling and latches for damage.
Vents and drain holes should be clear.
6 Check engine oil tank quantity and engine oil filter bypass pin
(Ref. Honeywell Light Maintenance Manual).
7 Check that the engine drain mast is clear and there are no signs
of fluid leaks.
8 Make sure there are no visible fluid leaks or foreign objects in
the engine exhaust (includingT/R's and afterbody).
9 Make sure there is no damage to the turbine blades when
viewed through the exhaust.

Copyright © Textron Aviation Inc. Page 4 of 10

10 Check exhaust duct blister sealant coating for condition.

H. Aft Fuselage - Right Side

050778 Check Comments
1 Check upper external fuselage (above engine pylon) for
condition and damage.
2 Check the APU exhaust is unobstructed/undamaged.
3 Check dorsal air intake is clear.
4 Check lower external fuselage (below engine pylon) for
condition and damage.
5 Check condition of pressure refueling cap and make sure it is
secure. Make sure the pressure refueling door is closed and
secured.
6 Make sure the ground power unit access door is secure.
7 Make sure the oxygen charging port access panel is secure.
8 Make sure that ventral tank OR EBU (if fitted) fairing is installed
and secure.

I. Empennage (Tail Section)

050779 Check Comments
1 Check condition of tailcone and make sure it is secured and
locked and the vents are unobstructed.
2 Check condition of tailcone strobe and navigation light lenses
and bulbs.
3 Check condition of the bullet fairing.
4 Check overall condition and for no visible damage to the vertical
stabilizer, rudder and trim tab.
5 Check overall condition and for no visible damage to the
horizontal stabilizer, elevator and trim tab.
6 Check condition of the upper anti-collision light.
7 Check condition of rudder, rudder trim tab, elevator and elevator
trim tab bond straps.
8 Check control surfaces for freedom of movement.
9 Check condition of static wicks; present and undamaged.
10 External Baggage Unit (750 airplanes only):
• Do a detailed visual inspection of the exposed internal
and external structure.

J. External Baggage Unit (750 Airplanes)

050780 Check Comments
1 Task moved to 050779.

K. Aft Fuselage - Left Side

050781 Check Comments
1 Check ventral tank (if fitted) fairing installed and secure.

Copyright © Textron Aviation Inc. Page 5 of 10

2 Check ventral tank (if fitted) filler cap for security and make sure the ventral
tank access door is closed and secure.
3 Check lower external fuselage (below engine pylon) for condition and
damage.
4 Make sure the fire extinguisher pressure relief indication disc for each
engine is intact and the APU fire extinguisher pressure relief indication disc
is intact.
NOTE:
Applicable to Sundstrand APU.
5 Check drain lines for signs of leakage.
6 Check upper external fuselage (above engine pylon) for condition and
damage.
7 Check the APU intake is unobstructed/undamaged.

L. Rear Equipment Bay

050782 Check Comments
1 Open door and check condition of door.
2 Check general condition of rear equipment bay.
3 Check all (T/R, MAIN and EMERG.) hydraulic accumulator pre-charge
pressures with hydraulic system pressure depleted.
4 Check the main hydraulic reservoir contents (dependant on accumulator
pressure) and make sure there are no leaks (Ref. AMM 12-29-00, 301, in
the applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line
21 or 900XP).
5 Make sure the hydraulic system pressure filter differential pressure
indicator button is not protruding (Ref. AMM 29-10-61, 001,in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21
or 900XP).
6 Make sure there are no sign of fluid leakage.
7 Check computer connections are secure.
8 Check APU general condition, no leaks and APU fire extinguisher
pressure.
NOTE:
Applicable to PATS APU.
9 Check stick pusher assembly, general condition/no leaks.
10 Check elevator elliptical unit for free movement and condition.
11 Make sure that the rear equipment bay light is off and door is closed and
latched securely.

M. Left Engine and Nacelle

050783 Check Comments
1 Make sure there are no visible fluid leaks or foreign objects in the engine
exhaust (including T/R's and afterbody).
2 Make sure there is no damage to the turbine blades when viewed through
the exhaust.
3 Check exhaust duct blister sealant coating for condition.

Copyright © Textron Aviation Inc. Page 6 of 10

4 Check that the engine drain mast is clear and there are no signs of fluid
leaks.
5 Check general condition of cowling and latches for damage. Vents and
drain holes should be clear.
6 Check engine oil tank quantity and engine oil filter bypass pin (Ref.
Honeywell Light Maintenance Manual).
7 Make sure the starter generator cooling intake and outlet is unobstructed.
8 Check the engine intake for damage and foreign objects.
9 Make sure there is no damage to the fan blades when viewed through the
engine intake.
10 Check P2T2 sensor is clean, undamaged and secure.

N. Left Main Landing Gear and Center Keel

050784 Check Comments
1 Visually check the strut for normal condition and leakage (Ref. AMM 12-32-
00, 301, in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
2 Check tires for condition and pressure (Ref. AMM 12-32-00, 301, in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21
or 900XP).
3 Check the main wheel tie bolt nuts for evidence of loosening.
4 Check the extension of the brake wear indicators (Ref. AMM 32-40-114,
601, in the applicable maintenance manual 750, 800XP, 800XP/850XP
Pro Line 21 or 900XP).
5 Make sure there is no visible damage to the main landing gear fairing and
doors.
6 Check condition of gear door bond straps.
7 Check the main gear and inside the main gear bay to make sure there is no
fluid leakage or damage.
8 Check condition of wiring and hoses.
9 Check condition of the anti-collision light lens and bulb, located on the
center keel.
10 Check all antennas attached to the keel are secure and undamaged.
11 Make sure that all water has been drained from the ventral fuel tank (if fitted)
sump and it is locked (Ref. AMM 12-28-00, 301, in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).

O. Left Wing
050785 Check Comments
1 Check condition of flap and air brake bond straps.
2 Check flap for damaged or missing static wick.
3 Check Flap bay overall condition and for hydraulic leaks.
4 Check condition of flap and air brakes. Make sure that there is no damage
to upper and lower surfaces.
5 Make sure the aileron and trim tab move freely through the full range of
travel.

Copyright © Textron Aviation Inc. Page 7 of 10

6 Make sure there are no foreign objects in the aileron shrouds.

7 Check condition of aileron and trim tab static wicks.
8 Check condition of aileron and trim tab bond straps.
9 Check condition of aileron and aileron trim tab.
10 Check condition of wing tip static wick.
11 Check condition of wing tip.
12 Check condition of strobe and navigation lights and lens.
13 Check vent surge tank is drained and locked.
14 Make sure the NACA vent is clear.
15 Make sure the stall warning system vent (if fitted) is clear, free of foreign
objects and fuel leaks.
16 Check vortex generators for dents and straightness and overwing fuel cap
for security.
17 Check wing leading edge and TKS panel for damage and sealant for
condition.
18 Check the condition of the external upper surface structure of the wing to
make sure it is clean and undamaged (no fuel leaks).
19 Check the condition of the external lower surface structure of the wing to
make sure it is clean and undamaged (no fuel leaks).
20 Check stall strip and vortilon, for damage and condition.
21 Check landing and taxi lights for condition of lens and bulbs.
22 Check condition of wing ice light and lens.
23 Check condition of over-wing fillet fairing and seal.
24 Make sure all water has been drained from the center section fuel tank
sump and it is locked (Ref. AMM 12-28-00, 301, in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
25 Check condition of main entry door seal/frame, fuselage and passenger
windows.

P. Flight Compartment
050786 Check Comments
1 Check condition of seat, seat belts and shoulder harnesses.
2 Check seat adjustment for proper operation.
3 Check flight compartment windows for condition.
4 Make sure all flashlights function correctly.
5 Make sure the auxiliary hydraulic system handpump handle/rudder gust
lock is properly stowed.

Copyright © Textron Aviation Inc. Page 8 of 10

6 Airplanes without the digital pressurization control system Mod.

25G726A/C or Mod. 25G726B/C:
Check operation of the Dump Valve. Make sure the dump valve lever is
set to SHUT (Ref. AMM 21-10-155, 201, in the applicable maintenance
manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
Airplanes with the digital pressurization control system Mod. 25G726A/C
or Mod. 25G726B/C:
Check operation of the Vent Valve. Make sure the vent valve lever is set to
SHUT (Ref. AMM 21-10-155, 201, in the applicable maintenance manual
750, 900XP).

7 Make sure there is full and free movement of the aileron, elevator and
rudder primary controls and all three trim controls.
8 With the landing gear ground locks installed, make sure that the
emergency dump valve is properly exercised by operating the auxiliary
hydraulic handle several times. Investigate any undue stiffness in
operation.
WARNING:
On completion of the check, make sure the selector handle is reset
to the fully in position.
9 Check overall status of the flight compartment.
10 Check the airframe anti-icing system tank contents (Ref. AMM 12-30-00,
301, in the applicable maintenance manual 750, 800XP, 800XP/850XP
Pro Line 21 or 900XP).

Q. Vestibule, Passenger Cabin and Toilet Compartment

050787 Check Comments
1 Make sure all emergency equipment is on board and properly stowed.
2 Check the portable breathing equipment for condition and date (if
installed):
800XP airplanes (Ref. AMM 35-35-10) or (Ref. AMM 35-35-15).
OR
750, 800XP/850XP Pro Line 21 and 900XP (Ref. AMM 35-35-15, in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21
or 900XP.).
3 Make sure the emergency exit door is secure.
4 Make sure all passenger seat safety belts (and settee safety harnesses
(if installed)) operate correctly and are secure. Check latch security and
wear. Check seat belt attachment hook and safety clip for distortion and
security.
5 Check cabin windows for condition.
6 Check for signs of water leakage from the lavatory and toilet areas.
7 Check lavatory seat and seat belt (if installed) for condition.
8 Check aft avionics equipment for condition and security.
9 Check the condition of the Galley waste container (Ref. MMA 25-30-20,
601).

Copyright © Textron Aviation Inc. Page 9 of 10

10 Airplanes with the digital pressurization control system Mod. 25G762A/C

or Mod. 25G762B/C:
Check the cleanliness of the two cabin pressurization system air filters
(Ref. AMM 21-31-20, 301, in the applicable maintenance manual 750 or
900XP).). If necessary, replace the air filter(s).

11 Check the condition of the lavatory waste container, with particular

attention to the correct fit, sealing and latching of the container access
door (Ref. MMA 25-30-20, 601, in the applicable maintenance manual
750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
NOTE:
The lavatory waste container inspection satisfies FAA AD 74-08-09
R3 repetitive requirements.

R. Final Items
050788 Check Comments
1 Energize the airplane 28 vdc busbars (Ref. AMM 24-01-00, 201, in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line
21 or 900XP).
2 Check operation of all external lights and beacons (Ref. AMM/MMA
Chapter 33, as applicable).
3 Check the operation of the auxiliary heating valve. (Ref. AMM 21-60-
105, 201, in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP). Functional test steps (2) and (4).
4 Make sure the oxygen system contents are adequate (Ref. AMM 12-35-
00, 301, in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
5 Check operation of all emergency lights (Ref. AMM/MMA Chapter 33, as
applicable).
6 Check operation of cockpit lighting (Ref. AMM/MMA Chapter 33, as
applicable).
7 Check operation of cabin interior lights (Refer to AMM/MMA Chapter 33,
as applicable).
8 Make sure that all access doors and servicing panels are secure.
9 De-energize the airplane 28 vdc busbars.
10 Make sure ALL areas are clean and clear of tools and miscellaneous
items of equipment.

Copyright © Textron Aviation Inc. Page 10 of 10

AIRBRAKE SELECTOR LEVER BAULK INSPECTION - 270001

1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Sep.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.

Functional Test
Aircraft Registration: Total Airframe Hours: Mechanic Inspector
Flight Controls
270001 Every 400 hours.
Airbrake selector lever baulk. Do an operational test (AMM 27-61-03, 501
in the applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line
21 or 900XP).
NOTE:
SB 27-3554, Rev.4, introduces an airbrake selector lever baulk to 900XP
airplanes.
NOTE:
This task is ONLY applicable to airplanes with Mod.25F743A or
25F743C embodied and is applicable to Canadian registered airplanes
only.
NOTE:
Mod.25F743A (SB 27-3150) introduces an airbrake selector lever baulk
to 800XP airplanes.
NOTE:
Mod.25F743C (SB 27-3554) introduces an airbrake selector lever baulk
to 800XP - Pro Line 21 airplanes.
NOTE:
SB 27-3554, Rev.3, introduces an airbrake selector lever baulk to 850XP
airplanes.

Copyright © Textron Aviation Inc. Page 1 of 1

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:40:36 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-20-09 (Rev A0)

STRUCTURAL INSPECTIONS
1. Inspection
List of Effective Pages
Pages 1 thru 32, Issued Sep.15

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.

Area F1: External fuselage, nose cone, tail cone, wing-to-fuselage fairings.
Aircraft Registration: Mechanic Inspector
530001 8 years, then every 4 years.
Skin exterior under the dorsal intake, forward of Frame 19.
Access: Dorsal intake removed.
• Detail inspect for cracks, signs of corrosion and deterioration of the
protective treatment.
• Detail inspect for chafing rivets.
Inspection completed at..................... Hrs. Date..........................
530002 8 years, then every 4 years.
Fuselage skin under wing-to-fuselage fairings.
Access: Panels F124 and F224 removed.
• Inspect visible areas of skin for cracks and signs of corrosion using
flashlight, mirror and borescope probes.
Inspection completed at.......................... Hrs. Date......................
NOTE:
It is recommended that the following two tasks are done at the same time.
530003 This task is NOT APPLICABLE to the Hawker 750 airplane or airplanes with the
Ventral baggage pannier installed in place of the Ventral fuel tank.
Between 15 to 18 years, then every 8 years.
Fuselage skin covered by the ventral fuel tank.
Access: Ventral fuel tank removed.
• Detail inspect especially for signs of corrosion and deterioration of the
protective treatments.
• Detail inspect attachment points and links.
Inspection completed at..................... Hrs. Date..........................

Copyright © Textron Aviation Inc. Page 1 of 18

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:40:37 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-20-09 (Rev A0)

530004 This task is NOT APPLICABLE to the Hawker 750 airplane or airplanes with the
Ventral baggage pannier installed in place of the Ventral fuel tank.
Between 15 to 18 years, then every 8 years.
Ventral fuel tank and attachments.
Access: Ventral fuel tank and tank access panels removed 800XP (Ref. AMM
28-10-15), 800XP/850XP Pro Line 21 (Ref. AMM 28-10-15) and 900XP (Ref.
AMM 28-10-15).
• Detail inspect the tank internal structure, skin, access panels, bolts and
fasteners, fuel system components and pipelines.
• Pay particular attention to the security of the nylon vent pipes and the
integrity of the sealant fillets at the pipe joints.
• Inspect the rubber drain non-return valve in the vent system balance pipe
for deterioration and splitting.
• Detail inspect attachment points and links.
• Detail inspect the fuel seal block assembly (P/N: 25-8PT341-1A) at the
ventral tank diaphragm for missing sealer, voids and corrosion.
NOTE:
If missing sealer, voids or corrosion are found, remove the fuel
seal block assembly for further detailed inspection.
Inspection completed at......................... Hrs. Date......................
NOTE:
It is recommended that the following three tasks are done at the same time.
530005 Between 15 to 18 years, then every 8 years.
Fuselage skin covered by the ventral baggage pannier or EBU (750 airplanes)
(if fitted).
Access: Ventral baggage pannier removed or EBU (750 airplanes) (if fitted)
removed.
• Detail inspect, especially for signs of corrosion and deterioration of the
protective treatments.
• Detail inspect attachment points and links.
NOTE:
This task is only applicable to airplanes with a baggage pannier in place
of the ventral fuel tank or 750 airplanes with external baggage unit.
Inspection completed at...................... Hrs. Date.........................
530006 Between 15 to 18 years, then every 8 years.
Ventral baggage pannier (if fitted) or EBU (750 airplanes) (if fitted) internal
structure.
Access: Ventral baggage pannier (if fitted) or EBU (750 airplanes) (if fitted)
removed. All doors open and access panels removed.
• Detail inspect the pannier (or EBU as applicable) internal structure.
• Detail inspect attachment points and links.
NOTE:
This task is only applicable to airplanes with a baggage pannier in place
of the ventral fuel tank OR 750 airplanes with external baggage unit.
Inspection completed at...................... Hrs. Date.........................
530026 Between the 15 th and 18th year of aircraft operation and then every 8
years.
External Baggage Unit (EBU) (750 airplanes ONLY) forward and aft attachment
fittings:
• Do a detailed visual inspection.

Copyright © Textron Aviation Inc. Page 2 of 18

520008 12 years then every 8 years.

Main entry door.
Access: Refer to NTM Technique.
• Comply with instructions in NTM 52-80-102.
Inspection completed at.......................... Hrs. Date.....................
530007 12 years and then every 8 years.
Wing to fuselage attachment links, brackets and bolts.
Access: removed.
• Detail inspect links, brackets and bolts for cracks, signs of corrosion,
fretting and wear (Ref. AMM 53-40-01, 201 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
Inspection completed at .........................Hrs. Date........................
530008 Transferred to AMM Chapter 32.
530009 Panels F124, F224, W501 27,000 flights and then every 4500 flights.
Fuselage lap joints.
Access: Refer to NTM Technique.
• Comply with instructions in NTM-125, 53-10-104.
Inspection completed at.................... Flts. Date.......................
530010 Whenever the wings are separated from the fuselage.
Access: Wings separated from the fuselage.
• Detail inspect the skin of the fuselage in the area that is covered by the
wing structure.
• Detail inspect the wing attachment brackets and the frame build-up at
frames 13 and 16.
• Detail inspect the drag spigot bearing.
• Inspect the drag spigot housing.
Inspection completed at...................... Hrs. Date.........................
530018 4800 flying hours, then every 2400 flying hours.
Fuselage skin adjacent to cabin window cutouts.
• Detail inspect skin.
Inspection completed at...................... Hrs. Date.........................

Area F2: Flight compartment

Aircraft Registration: Mechanic Inspector
510001 Every 5000 landings or 12 years, whichever occurs first.
Nose landing gear bay sidewalls.
Access: Refer to NTM Technique.
• Comply with instructions in NTM-125, 53-10-111.
Inspection completed at........................ Landings. Date......................
510002 5000 flights then every 1000 flights.
Front pressure bulkhead.
Access: Sound-proofing blankets removed.
• Detail inspect the upper sidewall beams and the rudder pedal clearance
pressings for cracks (Ref. SRM 53-10-11, Front Pressure Bulkhead Pre-
Mod. 253090C and Front Pressure Bulkhead Mod. 253090C).
• Pay special attention to the area in the vicinity of the joint with the canopy
center post.
Inspection completed at......................... Flts. Date......................

Copyright © Textron Aviation Inc. Page 3 of 18

510003 12 years, then every 4 years.

Flight compartment skin and window structure above windshields.
Access: Refer to NTM Technique.
• Comply with instructions in NTM-125, 53-10-105A.
Inspection completed at.................... Flts/Hrs. Date....................
510004 Every 20,000 flights.
Upper canopy rail at intersection with the canopy posts.
Access: Trim and insulation removed.
• Detail inspect.
Inspection completed at........................ Flts. Date.......................

Area F3: Vestibule, passenger cabin and toilet compartment.

Aircraft Registration: Mechanic Inspector
510005 Between 15 to 18 years, then every 8 years.
Center fuselage structure below the floor, nose landing gear bay to Frame 13
and Frames 16 to 19.
Access: Refer to relevant NTM Techniques.
Comply with instructions in:
• NTM-125, 53-10-108.
• NTM-125, 53-10-107.
• NTM-125, 53-10-108B.
• NTM-125, 53-10-109.
Inspection completed at....................... Hrs. Date........................
510006 Between 15 to 18 years and then every 8 years.
Structure below escape hatch, Frames 13 to 14.
Access: Escape hatch removed, leaded vinyl sleeve peeled back from lower
corners of the escape hatch surround to expose the apertures in the surround.
• Detail inspect Frames 13 and 14, as far as is possible, for signs of
corrosion using a borescope probe.
Inspection completed at........................ Hrs. Date.......................
520009 Between 15 to 18 years, then every 8 years.
Escape hatch.
Access: Trim removed.
• Detail inspect the structure internally and externally for cracks, signs of
corrosion and the deterioration of the protective treatment.
Inspection completed at...................... Flts./Hrs. Date.................

Copyright © Textron Aviation Inc. Page 4 of 18

510007 Between 15 to 18 years and then every 8 years.

Center fuselage structure below the floor, frames 8 to 17.
Access: Refer to NTM Technique.
• Comply with instructions in NTM-125, 53-10-106A.
Inspection completed at........................ Hrs. Date.......................
510008 Between 15 to 18 years and then every 8 years.
Center fuselage structure below the floor, Frames 13 to 16.
Access: Refer to NTM Technique.
• Comply with instructions in NTM-125, 53-10-108A.
NOTE:
In certain instances it may be necessary to lower the wing or separate
the wing from the fuselage to insert the film packs. In order to
determine the conditions of individual airplanes a test may be done by
attempting to pass a strip of vinyl carrier, to the dimensions given in the
relevant NTM, between the fuselage lower skin and the wing top
surface.
Inspection completed at........................ Hrs. Date.......................
510009 8 years and then every 4 years.
Entry door surround.
Access: Panel F66A, F66B, F66C removed.
• Detail inspect the structure at the lower edge of the surround for signs
of corrosion using a borescope probe inserted through the lightening
holes in the intercostal.
Inspection completed at....................... Hrs. Date........................
510010 Between the 15th and 18th year of aircraft operation and then every 8
years.
Center fuselage structure, above the floor.
Access: Refer to relevant NTM Techniques.
NOTE:
The most economical and practical time to do this inspection is when
the quick trim is removed for refurbishing or other reasons.
NOTE:
Airplanes without the digital pressurization control system Mod.
25G726A/C or Mod. 25G726B/C.
When installing local furnishings, make sure a minimum clearance of
1.0 inch between the motor of the fan operated venturi and local
furnishings is kept.
• Peel back the sound dampening material sufficiently to visually inspect
the skin in the vicinity of the fasteners and other attachments. It is not
necessary to remove the sound dampening material.
• Inspect the skin, as far as is possible, for cracks, signs of corrosion and
deterioration of the protective treatment.
• Comply with instructions in:
• NTM-125, 53-10-101.
• NTM-125, 53-10-102.
• NTM-125, 53-10-103A.
• NTM-125, 53-10-104.
• NTM-125, 53-10-106.
Inspection completed at......................... Hrs. Date.....................

Copyright © Textron Aviation Inc. Page 5 of 18

530011 Every 4 years.

Front face of rear pressure bulkhead (Frame 19).
• Inspect left-hand side of bulkhead with the soundproofing blankets
removed.
NOTE:
Airplanes without the digital pressurization control system Mod.
25G726A/C or Mod. 25G726B/C.
When installing local furnishings, make sure there is a minimum
clearance of 1.0 inch between the motor of the fan operated venturi and
the local furnishings.
• Look for signs of corrosion at the boundary angle to Frame 19 joints.
NOTE:
If you find any defects, extend the inspection to include the right-hand
side of the bulkhead.
Inspection completed at......................... Hrs. Date......................

530012 Every 8 years.

Front face of rear pressure bulkhead (Frame 19).
• Inspect right hand side of bulkhead with soundproofing blanket
removed.
NOTE:
Airplanes without the digital pressurization control system Mod.
25G726A/C or Mod. 25G726B/C.
When installing local furnishings, make sure a minimum
clearance of 1.0 inch between the motor of the fan operated
venturi and local furnishings is kept.
• Look for signs of corrosion at the boundary angle to frame 19 joints.
Inspection completed at.......................... Hrs. Date......................

Area F4: Rear fuselage.

Aircraft Registration: Mechanic Inspector
530013 Every 10,000 flying hours.
Pylon engine main mounting attachment fittings.
Access: Refer to NTM Technique.
• Comply with instructions in NTM-125, 53-10-110.
Inspection completed at...................... Flts. Date.........................
530014 Every 20,000 flying hours.
Rear engine mount fittings.
Access: Refer to NTM Technique.
• Comply with instructions in NTM-125, 53-10-110A.
Inspection completed at...................... Flts. Date.........................
530015 Every 30,000 flying hours.
Vertical stabilizer root attachment to fuselage.
Access: Refer to NTM Technique.
• Comply with instructions in NTM-125, 55-30-104.
Inspection completed at........................ Flts. Date......................

Copyright © Textron Aviation Inc. Page 6 of 18

530016 Every 10,000 flying hours.

Engine beam.
Access: Engines and engine main mounting attachment fittings removed (Ref.
AMM 71-20-00, 401, in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
NOTE:
The pylon firewall below the engine front mount assembly and the inside
of the engine pick-up mount bracket can be visually inspected from
inside the pylon access panels. The ends of the engine beam with all the
doublers and angles can be inspected from inside the rear equipment
bay area.
• Detail inspect the multi-layer ends of the beam forming pick-ups for
damage, cracks and signs of corrosion using X 10 magnification.
Inspection completed at...................... Flts. Date.........................
530019 PATS APU GTCP36-150W.
Every 12 months.
NOTE:
If any of the following inspections show an abnormal indication or
requires the replacement of structural parts, do Tasks 530022 and
530023.
Detail inspect the following items accessible without removal from the rear
equipment bay, for cracks or failures:
• All APU support structure external to the fire enclosure.
• Remove the oil filler door and all access covers in the bottom enclosure
and inspect all the APU structure internal to the fire enclosure.
• Inspect the main engine crossbeam and frame 21 in the areas
immediately adjacent to the APU attachment fittings.
• Inspect the five pairs of isolator mounts for deterioration of the silicone
rubber.
Visually check on the exterior of the fuselage and make sure that the APU
exhaust duct is centered in the exhaust shroud duct, and that the exhaust shroud
duct is centered in the skin cutout for the APU exhaust.
Inspection completed at..................... Hrs. Date..........................
530020 Task deleted (covered by task 530019).
530021 PATS APU GTCP36-150W.
Every 3000 APU running hours.
APU Support Structure:
• Detail inspect all mounting parts for cracks or damage.
• Detail inspect all fuselage attachments point for cracks or damage.
NOTE:
Repair as required.
Inspection completed at..................... Hrs. Date..........................

Copyright © Textron Aviation Inc. Page 7 of 18

530022 PATS APU GTCP36-150W.

Every 4500 APU running hours.
NOTE:
Do this task in conjunction with the removal of the APU for the Hot
Section inspection (Out of Phase Task # 490006).
• Remove and detail inspect the items listed in Table 1 (Located after
Area F4 inspections).
NOTE:
Replace all parts with the evidence of any damage.
Inspection completed at..................... Hrs. Date..........................
530023 PATS APU GTCP36-150W.
Every 4500 APU running hours.
NOTE:
Do this task in conjunction with the removal of the APU for the Hot
Section inspection (Out of Phase Task # 490006).
• Detail inspect the fuselage structure for cracks, particularly the support
bracket attachment holes in the upper cap of the main engine cross
beam and at the top and left side of the fuselage at frame 21.
NOTE:
The attachment brackets secured to the airframe will have to be removed
so that a detailed inspection of the holes drilled in the airframe for the
APU fitting can be done.
Inspection completed at..................... Hrs. Date..........................

530024 PATS APU GTCP36-150W.

Every 22,500 APU running hours.
APU support hardware listed in Table 2 (Located after Area F4 inspections)
• Do a fluorescent penetrant inspection (FPI) (Ref. NTM 125, General
Techniques, Part C Liquid Penetrant)
OR
• Replace.
NOTE:
FPI using MIL-1-25135C, Group 6A penetrant. Reject all linear
indications.
NOTE:
Do this task in conjunction with the removal of the APU for the Hot
Section inspection (Out of Phase Task # 490006).
Inspection completed at..................... Hrs. Date..........................
530025 PATS APU GTCP36-150W.
Every 10,000 flights.
Exhaust and inlet doubler frames and stringers.
• Detail inspect internally and externally for minute cracking conditions or
other defects particularly near the exhaust.
NOTE:
Repair as required.
Inspection completed at..................... Hrs. Date..........................
Table 1. Table 1(PATS APU GTCP36-150W - Items to be inspected in task # 530022)
Part Number Item Quantity
2380054-5 Mount Bracket 2

Copyright © Textron Aviation Inc. Page 8 of 18

2380054-7 Mount Bracket 2

2380138-1 Side Brace Bracket 1

238043-401 or 238043-411 Cradle Mount Assembly 1
2380062-19 Mount Adapter Assembly 2
2380055-403 or 2380055-413 Attach Bracket 3
2380137-401 or 2380137-411 Engine Mount Assembly 1
2350066-1 Special Bolt 5
2380058-5 or 2380058-15 Engine Beam Anchor Bracket 2
2380056-403 or 2380056-413 Mount Tube Assembly 1
2380056-405 or 2380056-415 Mount Tube Assembly 1
2380056-409 or 2380056-419 Mount Tube Assembly 1
2380136-1 or 2380136-11 Eye Bolt 3
2380148-1 Bracket 4
MS27039-1-17 Screw 8
NAS1351-4H12P Cap Screw 16
NAS6203-10 Bolt 8
NAS6203-26 Bolt 2
NAS6203-27 Bolt 1
NAS6203-31 Bolt 1
NAS6206-19 Bolt 2
NAS6206-31 Bolt 1
AN5-13 Bolt 2
Table 2. Table 2(PATS APU GTCP36-150W - Items to be inspected in task # 530024)
Part Number Item Quantity
2380143-401 or 2380143-411 Cradle Mount Assembly 1
2380062-19 Mount Adapter Assembly 2
NAS1351-4H10P Cap Screw 8
NAS1351-4H12P Cap Screw 16

Area T1: Horizontal and vertical stabilizers, to include elevators and rudder.
Aircraft Registration: Mechanic Inspector

Copyright © Textron Aviation Inc. Page 9 of 18

550001 Every 4 years.

Elevators and Tabs:
• Remove elevator (Ref. AMM 27-30-22, 401, in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
• Detail inspect.
• Inspect the bearings for smooth operation and replace as required.
• Detail inspect the hinge brackets for security and cracks with a X
10 magnifier. Look for signs of corrosion.
• Install elevator (Ref. AMM 27-30-22, 401, in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
Inspection completed at..................... Hrs. Date..........................

550002 Every 4 years.

Elevator trim tabs, connecting rods:
• Inspect the rod end bearings for smooth operation and replace as
required.
• Apply a coat of silicone lubricant to both exterior surfaces of the
bearing at each connecting rod end (Ref. AMM 27-30-00, 301, in
the applicable maintenance manual 750, 800XP, 800XP/850XP
Pro Line 21 or 900XP).
NOTE:
The silicone lubricant is applied to give the rod end bearing
protection against corrosion.
Inspection completed at..................... Hrs. Date..........................
550003 8 years, then every 4 years.
Elevators.
Access: Refer to relevant NTM Technique.
• Comply with instructions in NTM-125, 55-20-101 and NTM-125, 55-
20-102.
• If corrosion is found extend the X-Ray coverage until a complete rib
bay is found to be free from corrosion.
Inspection completed at....................... Hrs. Date..................
550004 Every 4 years.
Rudder and Tab:
• Remove (Ref. AMM 27-20-23, 401, in the applicable maintenance
manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
• Detail inspect.
• Inspect the bearings for smooth operation and replace as required.
• Install (Ref. AMM 27-20-23, 401, in the applicable maintenance
manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
Inspection completed at..................... Hrs. Date..........................
550005 Every 4 years.
Connecting rods, rudder trim tab and anti-servo tab:
• Inspect the rod end bearings for smooth operation and replace as
required.
Inspection completed at..................... Hrs. Date..........................

Copyright © Textron Aviation Inc. Page 10 of 18

550006 8 years, then every 4 years.

Rudder.
Access: Refer to NTM Technique.
• Comply with instructions in NTM-125, 55-40-101.
Inspection completed at...................... Hrs. Date..................
550007 Every 8 years.
Rudder hinge brackets and attachments.
Access: Rudder and rudder hinge bracket cover plates removed.
• Detail inspect the rudder hinge brackets, using a X 10 magnifier.
Inspection completed at ......................... Hrs. Date ......................
550008 Transferred to Inspection F8.
550009 Every 8 years.
Horizontal stabilizer.
Access: Leading edges removed. Elevators removed. Shroud panels
T21R, T22L, T23R, T24L, T25R, T26L and T45 removed. Fairing panels
T4L, T4R, T5, T6L, T7R, T8L, T9R and T13 removed.
• Detail inspect the front face of the front spar for cracks and signs of
corrosion.
• Detail inspect the rear face of the rear spar for cracks and signs of
corrosion.
• Detail inspect the vertical stabilizer to horizontal stabilizer
attachment fittings.
• Detail inspect the elevator hinge brackets.
• Apply Corrosion Preventive Compound (Ref. AMM 55-13-00, 301
in the applicable maintenance manual 800XP or 800XP/850XP
Pro Line 21).
NOTE:
Application of Corrosion Preventive Compound is ONLY
applicable to the series 800XP and 800XP/850XP Pro Line 21
airplanes.
Inspection completed at........................ Hrs. Date.......................
550010 Between 15 to 18 years, then every 8 years.
Vertical stabilizer.
Access: Leading edge panels, upper vertical stabilizer and rudder
removed.
• Detail inspect the structure rendered visible.
• Detail inspect the rudder hinge brackets for security, cracks and
signs of corrosion.
• Comply with instructions in:
• NTM-125, 55-30-101
• NTM-125, 55-30-102
• NTM-125, 55-30-103.
• With the leading edge removed detail inspect the internal structure
of the vertical stabilizer for cracks and signs of corrosion using a
borescope probe through the access holes in the front spar and
through the root rib.
Inspection completed at........................ Hrs. Date................

Copyright © Textron Aviation Inc. Page 11 of 18

550011 16 years, then every 8 years (see NOTE).

Horizontal stabilizer to vertical stabilizer attachments.
Access: Horizontal stabilizer removed.
NOTE:
Airplanes which have had the horizontal stabilizer removed at or
subsequent to the 12 year inspection can be considered to have
satisfied the initial inspection requirement.
• Detail inspect the attachment lugs for cracks, signs of corrosion
and elongation of the attachment bolt holes.
• Inspect the bolts for signs of wear or corrosion.
• Replace any worn bolts. If holes are elongated replace bolts, see
SRM 55-10-41.
Inspection completed at.........................Hrs. Date....................
550012 24 years and then every 8 years.
Horizontal stabilizer.
Access: Refer to relevant NTM Techniques.
NOTE:
For convenience and improved access it is recommended that this
inspection is done when the horizontal stabilizer is removed for the
inspection of the attachment lugs (Task No. 550011).
• Comply with instructions given in one of the methods below:
• Fokker Bond Test NTM-125, 55-10-104A.
• Schlumberger Sonatest NTM-125, 55-10-104B
• Staveley Sonic Bondmaster NTM-125, 55-10-104C.
Inspection completed at......................... Hrs. Date......................

550013 Between 15 to 18 years, then every 8 years.

Horizontal stabilizer.
Access: Refer to relevant NTM Techniques.
• Comply with instructions in:
• NTM-125, 55-10-101
• NTM-125, 55-10-102
• NTM-125, 55-10-103
• NTM-125, 55-10-105.
Inspection completed at........................ Hrs. Date...............
550014 15,000 flights and then at every X-Ray inspection of the horizontal
stabilizer internal structure (Task No.550013).
Horizontal stabilizer top skin 'T' fitting and joint strap at the center line of the
stabilizer.
Access: Upper vertical stabilizer removed.
• Detail inspect for cracks and signs of corrosion.
Inspection completed at........................ Flts. Date......................

Copyright © Textron Aviation Inc. Page 12 of 18

550015 Every 2 years.

Elevators:
• Remove and inspect mass balance weight side plates, look for
signs of corrosion (Ref. AMM 27-30-91, 601, in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
• Remove and inspect mass balance weights, spigots and
installation, look for signs of corrosion (Ref. AMM 27-30-91, 601, in
the applicable maintenance manual 750, 800XP, 800XP/850XP
Pro Line 21 or 900XP).
NOTE:
Remove all corrosion found from the spigots to a maximum depth
of 0.03 in. and paint with epoxy primer (Ref. AMM 125/H-20, 20-95-
401, Item No. 474).
NOTE:
If excessive corrosion is found contact:Repair Design Office
Textron Aviation Inc 9709 East Central P.O. Box 85 Wichita, KS
67201-0085, U.S.A
• Assemble the spigots and mass balance weights (Ref. AMM 27-
30-91, 601, in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
• Apply corrosion preventive compound LPS 3 (AMM 125/H-20, 20-
95-11, Item No. 089) or ACF 50 (Ref. AMM 125/H-20, 20-95-11,
Item No. 090) (Ref. AMM 27-30-91, 601, in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
• Install the side plate assembly (Ref. AMM 27-30-91, 601, in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP).
NOTE:
The balance of the elevator must be checked and if
necessary adjusted only when a repair has been done or a
paint finish changed.
CAUTION:
Make sure that the mass balance weights are installed on the same
side that they were removed from.
Inspection completed at..................... Hrs. Date..........................

Area W1, W2: Wings, LH and RH.

Aircraft Registration: Mechanic Inspector
320028 8 years, then every 4 years.
Main landing gear fairing strut.
• Comply with instructions in NTM 32-10-103.
Inspection completed at......................... Hrs. Date......................

Copyright © Textron Aviation Inc. Page 13 of 18

570007 8 years, then every 4 years.

Wing bottom skins and stringers between the front and rear spars, Rib 0 to
Rib 1 and between the center spar and rear spar from Rib 1 to Rib 4.
Access: Refer to NTM Technique.
• Comply with instructions in NTM-125, 57-50-107 .
• Detail inspect the bottom stringers in the vicinity of the wing skin
restraint ties with the aid of a flashlight and mirrors.
NOTE:
If corrosion is found while doing NTM-125, 57-50-107 extend the X-
Ray coverage until a complete rib bay is found to be free from
corrosion.
NOTE:
If the quality of the radiographs is impaired by the presence of
pockets of fuel it would indicate that the internal fuel drain paths are
blocked. Operators are advised to remedy this condition at the first
convenient opportunity.
Inspection completed at..................... Hrs. Date.........................

570008 8 years, then every 4 years.

Main Landing Gear and sidestay attachment fittings.
Access: Panels W324, W424 removed.
• Detail inspect the landing gear pick-up fittings, specially the sidestay
pick-up, for cracks, signs of corrosion and signs of movement.
• Make sure the drain holes are unobstructed.
• Check the tightness of all securing bolts.
Inspection completed at.................... Hrs. Date............................
570009 4800 flying hours, then every 1200 flying hours.
Wing bottom skin (LH and RH) adjacent to flap outboard hinge at Rib 8.
Access: Hinge fairings, panels W314 and W414, removed.
• Detail inspect for cracks and signs of corrosion.
Inspection completed at....................... Hrs. Date........................
570010 Every 4800 flying hours or 8 years, whichever is the sooner.
Wing front spar, forward face.
Access: Wing leading edges removed.
• Detail inspect for cracks, signs of corrosion and distortion, specially
between Ribs 1 and 3.
• Inspect leading edges for cracks, signs of corrosion, damage and
integrity of the bolt holes.
NOTE:
When replacing the leading edges the profiles must be maintained
(see SRM 57-41-00).
Inspection completed at.................... Hrs. Date...........................
570011 4800 flying hours or 8 years, whichever is the sooner, then every
2400 flying hours or 4 years.
Wing rear spar, rear face.
Access: Ailerons, aileron shrouds, flaps and airbrakes removed.
• Inspect for cracks, signs of corrosion, distortion and damage.
• Inspect control surface hinge brackets on the rear spar for wear,
cracks, signs of corrosion and security.
Inspection completed at....................... Hrs. Date.......................

Copyright © Textron Aviation Inc. Page 14 of 18

570012 4800 flying hours or 8 years, whichever is the sooner, then every
2400 flying hours or 4 years.
Airbrakes.
Access: Airbrakes removed.
• Detail inspect.
• Inspect the hinges for security.
Inspection completed at......................... Hrs. Date.....................
570013 Every 2400 flying hours or 4 years, whichever is the sooner.
Ailerons:
• Remove (Ref. AMM 27-10-31, 401, in the applicable maintenance
manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
• Detail inspect.
• Inspect the bearings for satisfactory condition and make sure there
is adequate lubrication (Ref. AMM 125/H-20, 20-09-22, 201).
• Install (Ref. AMM 27-10-31, 401, in the applicable maintenance
manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
Inspection completed at......................... Hrs. Date......................
570014 Every 2400 flying hours or 4 years, whichever is the sooner.
Connecting rods, aileron trim and servo tabs:
• Lubricate or replace the front and rear rod end bearings, as required
(Ref. AMM 125/H-20, 20-09-22, 201).
• Apply a coat of silicone lubricant to both exterior surfaces of the
bearing at each trim tab connecting rod end (Ref. AMM 27-10-00,
501, in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
NOTE:
The silicone lubricant is applied to give the rod end bearing
protection against corrosion.
Inspection completed at......................... Hrs. Date......................
570015 4800 flying hours or 8 years, whichever is the sooner, then every
2400 flying hours or 4 years.
Ailerons.
Access: Refer to NTM Technique.
• Detail inspect the hinge brackets with a X 10 magnifier.
• Comply with instructions in NTM-125, 57-50-107.
Inspection completed at....................... Hrs. Date........................
570016 4800 flying hours or 8 years, whichever is the sooner, then every
2400 flying hours or 4 years.
Flaps and flap vanes.
Access: Refer to relevant NTM Technique.
• Inspect hinge brackets for security, freedom from cracks and signs
of corrosion.
• Inspect bearings for satisfactory condition and adequate lubrication.
• Comply with instructions in NTM-125, 57-50-107 and NTM-125, 57-
50-107.
NOTE:
If corrosion is found during the X-Ray inspection, extend the X-Ray
inspection coverage until a complete rib bay is found free of
corrosion.
Inspection completed at....................... Hrs. Date.......................

Copyright © Textron Aviation Inc. Page 15 of 18

570017 24,000 flying hours and then every 4800 flying hours.
Wing bottom skin at attachment to front spar, between Ribs 1 and 7.
Access: As visible.
• Detail inspect for cracks and signs of corrosion.
Inspection completed at....................... Hrs. Date.................
570018 24,000 flying hours and then every 9600 flying hours.
Wing bottom skin centerline joint strap.
Access: Keel skid removed.
• Detail inspect for cracks and signs of corrosion.
Inspection completed at...................... Hrs. Date.........................
570019 24,000 flying hours and then every 9600 flying hours.
Upper surface of the wing bottom skin at the attachment to the centerline
joint adjacent to Rib 0.
Access: Refer to NTM Technique.
• Comply with instructions in NTM-125, 57-50-107.
OR
24,000 flying hours and then every 7200 flying hours.
• With the sealant removed to expose the skin surface, detail inspect
for cracks at the bolt line.
Inspection completed at....................... Hrs./Flts. Date........................
570020 24,000 flying hours and then every 12,000 flying hours.
Wing bottom skin centerline butt strap and center section beams (24
positions).
Access: Refer to NTM Technique.
• Comply with instructions in NTM-125, 57-50-107.
Inspection completed at........................ Hrs. Date.......................
570021 Whenever the wings are separated from the fuselage.
Wing top skin in the area that is covered by the fuselage structure and main
attachment brackets.
Access: Wings separated from the fuselage.
• Detail inspect the skin, stiffeners and main attachment brackets for
cracks, signs of corrosion, security of rivets and damage.
• Inspect the drag spigot for wear.
• Inspect the spigot location plate for security of attachment.
Inspection completed at....................... Hrs. Date........................
570022 Every 4800 flying hours.
Rear spar, rear face between Rib 1 LH and Rib 1 RH.
Access: Main landing gear doors and panels W325, W425, W507 and
W508 removed.
• Detail inspect the rear face of the rear spar.
Inspection completed at....................... Hrs. Date........................

Copyright © Textron Aviation Inc. Page 16 of 18

570023 Every 4 years.

NOTE:
Applicable to airplanes without BC Winglets.
Aileron horn balance weight.
Access: Aileron horn balance weight cover removed.
• Detail inspect the horn balance weight for signs of corrosion.
• If signs of corrosion are found, then do an X-Ray inspection of the
area
• Comply with instructions in NTM-125, 57-50-107.
Inspection completed at....................... Hrs. Date........................
570028 4800 flying hours or 8 years, whichever is the sooner, then every 4
years.
NOTE:
Applicable to airplanes without BC Winglets.
Aileron at outboard hinge casting.
• Do the "Aileron Horn" Inspection/Check:750 (Ref. AMM 27-10-31,
601), 800XP (Ref. AMM 27-10-31, 601) and 800XP Pro Line 21
(Ref. AMM 27-10-31, 601).
Inspection completed at....................... Hrs. Date........................
570024 12,000 flying hours, then every 7200 flying hours.
Wing bottom skin at attachment to Rib 1 LH and RH.
Access: As visible.
• Detail inspect the skin where it is bolted to Rib 1 LH and RH.
Inspection completed at....................... Hrs. Date........................
570025 Every 4800 flying hours.
Wing bottom skin at attachment to the rear spar, between Rib 1 LH and Rib
1 RH.
Access: Main landing gear doors open and keel skid fairing in the area of
the main landing gear doors removed.
• Detail inspect the skin where it is bolted to the rear spar, between
Rib 1 LH and Rib 1 RH.
Inspection completed at....................... Hrs. Date........................
570026 Every 4 years.
Wing leading edges.
Access: TKS panels removed (also any material that might interfere with
visual inspection).
Inspect, specifically rebate area for cracks and signs of corrosion (Ref.
SRM 57-41-12, 201).
Inspection completed at........................ Hrs. Date........................

Copyright © Textron Aviation Inc. Page 17 of 18

570027 Every 4800 flying hours or 8 years, whichever is the sooner.

Area M1, M2: Engine installation and pylon, LH and RH.

Aircraft Registration: Mechanic Inspector
530017 Whenever the brackets are removed from the engine.
NOTE:
This task is only required when the engine has accomplished a Major
Periodic Inspection. Refer to the relevant Honeywell Light
Maintenance Manual:
750, 800XP and 800XP Pro Line 21 - TFE731-5BR-1H Series engine.
900XP - TFE731-50R-1H Series engine.
Forward engine mounting brackets, Part No. 3071071-3.
Access: Engine cowlings M1L, M2R, M3L and M4R removed.
• Remove the mounting brackets.
• Inspect for cracks using a magnetic particle inspection (LMM 72-00-
06).
Inspection completed at....................... Hrs. Date........................

Copyright © Textron Aviation Inc. Page 18 of 18

OUT OF PHASE INSPECTIONS

List of Effective Pages
Pages 1 thru 14, Issued Sep.16

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the Introduction section at the front
of this schedule.
Aircraft Registration: Mechanic Inspector
Air Conditioning
210006 Every 400 Hours.
Water separator.
• Inspect for satisfactory condition (Ref. AMM 21-10-95,
601, in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
NOTE:
Operators may adjust this time based on servicing
experience.
210007 Every 400 Hours.
Water separator .
Inspect the following items are free from blockages and
obstructions (Ref. AMM 21-10-95, 601, in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
• Water separator water drain.
• Water separator water drain pipeline.
• HP line to water injector nozzle.
• Water injector nozzle.
NOTE:
Operators may adjust this time based on servicing
experience.
210022 After 50 flying hours but not more than 300 flying hours from
airplane build OR after disturbance of ducts or rubber sleeves.
Air conditioning ducts:
• Check the duct joint clamp bolts for the correct torque
loading:
(Ref. AMM 21-10-15, 201, in the applicable maintenance
manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
(Ref. AMM 21-10-87, 201, in the applicable maintenance
manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
(Ref. AMM 21-10-95, 401, in the applicable maintenance
manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
Inspection completed at.......................... Hrs. Date.....................
210023 Task deleted, covered by AMM.
Air Conditioning (Cont)

Copyright © Textron Aviation Inc. Page 1 of 9

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:40:38 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-20-10 (Rev A0)

210029 Every 15,000 Hours, Airplanes with the digital pressurization

control system Mod. 25G726A/C or Mod. 25G726B/C:
Electropneumatic Outflow Valves:
• Do an inspection/check for the smooth operation of the
manual electropneumatic outflow valve (Ref. AMM 21-31-
10, 601, in applicable maintenance manual 750 or
900XP.)
Inspection completed at.......................... Hrs. Date.....................
Electrical Power
240001 Between 200 and 400 Hours.
Starter/generators:
• Remove and inspect (Ref. AMM 24-30-21, 401, in the
applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
• Do a brush wear check (Ref. AMM 24-30-21, 601, in the
applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
• Inspect cooling fan.
• Inspect splines for wear (Ref. AMM 24-30-21, 401, in the
applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
• Inspect engine drive for wear.
• Install starter/generator (Ref. AMM 24-30-21, 401, in the
applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
Inspection completed at.......................... Hrs. Date.....................
240019 Task deleted, covered by AMM.
240020 Task deleted, covered by AMM.
240021 Requirement deleted.
240022 Task deleted, covered by AMM.
240023 Requirement deleted.
240024 Every 500 APU running hours.
APU starter/generator:
• Remove (Ref. AMM 24-30-21, 401, in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line
21 or 900XP).
Check the brush wear (Ref. AMM 24-30-21, 601, in the
applicable maintenance manual 750, 800XP, 800XP/850XP
Pro Line 21 or 900XP).
Electrical Power (Cont).
240024 (Cont.) • Inspect the cooling fan.
• Inspect the splines for wear (Ref. AMM 24-30-21, 401, in
the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
• Inspect the engine drive for wear.
• Install the APU starter/generator (Ref. AMM 24-30-21, 401,
in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
Inspection completed at.......................... Hrs. Date......................

Copyright © Textron Aviation Inc. Page 2 of 9

240028 Every 400 Hours.

Panel GG and terminal block M.
• Do a visual inspection for deformation, displacement,
discoloration and heat distress (Ref. AMM 24-01-00, 201
in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
NOTE:
This task is applicable to series 750 airplanes HB-1
thru HB-27, 800XP, 800XP/850XP Pro Line 21
airplanes 258266 thru 258982 and 900XP airplanes
HA-0001 thru HA-0092 and HA-0094.
750 airplanes HB-28 and After, do not use terminal
block M (Mod. 25G484B).
850XP Pro Line 21 airplanes 258983 and After, do not
use terminal block M (Mod. 25G484C).
900XP airplanes HA-0093, HA-0095 and After, do not
use terminal block M (Mod. 25G484A).
• Check the terminal lugs and attaching hardware for correct
torque loading (Ref. AMM 24-01-00, 201)
Inspection completed at...........................Hrs. Date......................
240030 Every 200 Hours.
Cabin Inverter (115 VAC) system (if fitted).
• Do a function test of the Cabin Inverter (115 VAC) system
(Ref. MMA 24-20-10, 201).
Electrical Power (Cont)
240031 Between 200 and 400 Hours.
AC Generator Pad (900XP Only):
• Remove the AC Generator (Ref. AMM 24-22-21, 401).
• Inspect AC Generator QAD pad for deformation, cracks or
other damage.
• Install the AC Generator (Ref. AMM 24-22-21, 401).
Inspection completed at.......................... Hrs. Date.....................
Fire Protection
260008 Every 6 months.
Smoke Detection System (if fitted):
• Do a function test:
750 airplanes (Ref. MMA 26-11-00, 501).
800XP and 800XP Pro Line 21 airplanes (Ref. MMA 26-
11-00, 501).
900XP airplanes (Ref. MMA 26-11-00, 501).
Inspection completed at.......................... Hrs. Date......................

Copyright © Textron Aviation Inc. Page 3 of 9

260009 Every 6 months.

Baggage Pannier OR External Baggage Unit Smoke
Detection System (if fitted):
• Do a function test (Ref. AMM 26-10-52, 201, in the
applicable maintenance manual 750, or 800XP).
NOTE:
This test is only applicable to airplanes with a baggage
pannier in place of the ventral fuel tank OR 750 airplanes
with an external baggage unit.
Inspection completed at.......................... Hrs. Date......................
Flight Control
270001 Refer to Chapter 5, Pre-Flight Inspection, Post-Flight Inspection,
TFE731 Engine Inspection, APU Inspection, 200 Hour
Lubrication, 400 Hour Lubrication, 400 Hour Detailed Walk-
Around Inspection and Airbrake Selector Lever Baulk Inspection.
270061 After 200 flying hours and not more than 300 flying hours from the
airplane build or after control cable replacement.
Control cables. Check the tensions of the:
• Aileron and aileron trim control cables (Ref. AMM 27-10-
00, 501, in the applicable maintenance manual 750,
800XP, 800XP/850XP Pro Line 21 or 900XP).
• Rudder and rudder trim control cables (Ref. AMM 27-20-
00, 501, in the applicable maintenance manual 750,
800XP, 800XP/850XP Pro Line 21 or 900XP).
• Elevator and elevator trim control cables (Ref. AMM 27-30-
00, 501, in the applicable maintenance manual 750,
800XP, 800XP/850XP Pro Line 21 or 900XP).
• Flap control cables (Ref. AMM 27-50-02, 501, in the
applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
• Airbrake control cables (Ref. AMM 27-61-02, 501, in the
applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
Inspection completed at.......................... Hrs. Date.....................
270062 Transferred to Inspection B2, task # 270004.
270063 Whenever the SVO-85B servo or its mating servo mount are
removed and replaced in the airplane.
Servomotor assembly SVO-85B (P/N 622-5027-001).
Lubricate and clean as detailed in Collins SVO-85B/C Service
Information Letter SIL 1-01.
Inspection completed at.......................... Hrs. Date......................
Fuel
280009 Transferred to Structural Inspections task # 570027.
Fuel (Cont)

Copyright © Textron Aviation Inc. Page 4 of 9

280010 After 200 flying hours and not more than 300 flying hours from the
airplane build or after control cable replacement.
Control cables. Check the tensions of the:
• LP fuel valve control cables (Ref. AMM 28-20-83, in the
applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
• Crossfeed and wing transfer valve control cables (Ref.
AMM 28-20-83, in the applicable maintenance manual
750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
• Auxiliary fuel transfer valve control cables (Ref. AMM 28-
20-83, in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).(if ventral tank
installed).
Inspection completed at.......................... Hrs. Date......................
280011 Requirement deleted.
280012 Requirement deleted.
280013 Split into 2 tasks and transferred to Inspection C9 (280014) and
Inspection C10 (280015).
Ice and Rain Protection
300007 Every calendar month.
Applicable if the airframe de-icing system has not been operated
during the last calendar month.
• Airframe Ice protection - purge the airplane ice protection
system (Ref. AMM 12-30-00, 301, in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line
21 or 900XP).
Inspection completed at.......................... Hrs. Date.....................
Landing Gear
320029 Between 25 to 50 landings from build or after nose landing gear
drag stay replacement.
Nose landing gear drag stay. Check clearances (Ref. AMM 32-
20-21, 601, in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
Inspection completed at.......................... Hrs. Date.....................
320030 Requirement deleted.
Landing Gear (Cont).
320031 Requirement deleted.
320032 Requirement deleted, covered in Overhaul Manual Chapters 32-
20-30/501 and 32-20-35/501.
320038 NOTE:
This task is not applicable to airplanes Post Mod. 25G295 or
Post SB. 32-3779.
Every month if the airplane has been exposed to runway de-icing:
• Lubricate the Main landing gear sidestay shims (Refer to
Chapter 5, Lubrication, Monthly lubrication).
Inspection completed at.......................... Hrs. Date.....................
Navigation

Copyright © Textron Aviation Inc. Page 5 of 9

340002 Pitot/static drain traps.

• Pre-SB.34-3282 (Mod. 25F889B) or Pre-Mod. 25F889A.
Drain, do a leak test (Ref. AMM 34-11-19, 501, in the
applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
• Post SB.34-3282 (Mod. 25F889B) or Post Mod.
25F889A. Drain (Ref. AMM 34-11-19, 501, in the
applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
NOTE:
Do this task in conjunction with FAR pitot/static
system checks (Task 340006).
Inspection completed at.......................... Hrs. Date......................
Navigation (Cont).
340006 Pitot/static and stall warning systems. Do the following tests
(Ref. AMM 34-11-19, 501, in the applicable maintenance manual
750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
• Pressure Test Complete Pitot System.
• Suction Test Complete Static System.
• Pressure Test Stall Vent System (This procedure only
applies to airplanes Pre-Mod. 25G206A or 25G206B).
NOTE:
Do this task in accordance with FAR requirements.
Inspection completed at.......................... Hrs. Date......................
340007 Pitot system isolation valves.Make sure of full and free
operation.
NOTE:
This task is not applicable to the Hawker 750 or Hawker
900XP airplanes due to the removal of the third channel stall
can.
Do this task in conjunction with FAR pitot/static system
checks (Task 340006).
Inspection completed at.......................... Hrs. Date......................
Navigation (Cont).
340012 Every 36 months, or at a time period agreed with the local
regulatory authority.
Compass systems:
• Do a check compass swing of the compass systems at
four headings 90 degrees apart.
• Compare deviations, if any are found, with the existing
deviation card.
• If deviations are found then do a compass swing:
750 airplanes (Ref. AMM 34-20-05, 501).
800XP airplanes (Collins AMM 34-23-61, 501) (Honeywell
AMM 34-20-15, 501).
800XP Pro Line 21 airplanes (Ref. AMM 34-20-05, 501).
900XP airplanes (Ref. AMM 34-20-05, 501).
Inspection completed at.......................... Hrs. Date......................

Copyright © Textron Aviation Inc. Page 6 of 9

340013 After repaint or maintenance in the area affecting the airflow over
static ports.
Static plates and Airframe (Applicable to airplane serial
numbers 258359 and after, and to airplanes that have complied
with Service Bulletin 34-3110, or SB.34-3166 or SB.34-3381 and
are maintaining RVSM capability authorization).
Comply with RVSM requirements (Ref. AMM 34-11-29, 601, in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP) for the area disturbed.
Inspection completed at.......................... Hrs. Date......................
Auxiliary Power Unit
General • For ALL out of phase servicing and inspection
requirements, for the Sundstrand APU, refer to the
Sundstrand Power Systems SB-T-62T-49-77 and the
Turbomach APU MM.
Auxiliary Power Unit (Cont).
490001 Perform in conjunction with Task 490003.
PATS APU GTCP36-150W.
• Visually inspect exhaust for cracks or deformation.
• Visually inspect for loose or frayed wires.
• Inspect for signs of corrosion.
Inspection completed at.......................... Hrs. Date......................
490002 Every 750 APU running hours.
PATS GTCP36-150W APU.
Igniter plug (Ref. CMM 49-40-33):
• Remove, clean, inspect and install.
Inspection completed at.......................... Hrs. Date......................
490003 NOTE:
Choose one of the following options. Do either Oil and Filter
change at every 12 months or 1000 flying hours OR do a
S.O.A.P. check at 750 APU running hours/12 months.
CAUTION:
Do not mix options.
Option 1.
Every 12 months or 1000 flying hours (whichever comes first).
PATS GTCP36-150W APU.
Oil and filter change, and magnetic drain plug inspection.
Lubricating oil system:
• Drain and refill (refer to servicing).
NOTE:
Routine SOAP inspection is not required.
Oil Filter Element:
• Remove, inspect and replace as necessary (CMM 49-90-
47).
Auxiliary Power Unit (Cont).

Copyright © Textron Aviation Inc. Page 7 of 9

490003 (Cont.) Magnetic Drain Plug:

• Remove, clean, inspect and install magnetic element of
drain plug (CMM 49-90-46).
Option 2.
750 APU running hours or 12 months (whichever comes first).
Oil and Filter Element:
• Do a S.O.A.P. check (in accordance with Honeywell
procedures).
Magnetic Drain Plug:
• Remove, clean, inspect and install magnetic element of
drain plug (CMM 49-90-46).
Inspection completed at.......................... Hrs. Date......................
490004 Every 1000 APU running hours.
PATS GTCP36-150W APU.
Fuel filter element:
• Remove and replace (CMM 49-30-52).
Inspection completed at.......................... Hrs. Date......................
490005 Every 4500 APU running hours.
PATS GTCP36-150W APU.
Fuel Nozzle Assemblies:
Do a fuel flow rate check (CMM 49-20-00, Page Block 601,
paragraph 5, Fuel Nozzle Assembly Flow Rate Check).
Inspection completed at.......................... Hrs. Date......................
490006 Every 4500 APU running hours.
PATS GTCP36-150W APU.
Hot Section Inspection.
Do a detailed Hot Section Inspection on the components listed
(CMM 49-20-00, Page Block 601, paragraph (4), Detailed Hot
Section Inspection):
• Turbine Rotor
• Deswirl Deflector
• Turbine Nozzle
Auxiliary Power Unit (Cont).
490006 (Cont.) • Airflow Deflector
• Turbine Housing Assembly
• Combustion Chamber
• Labyrinth Seal
• Turbine Wheel Deflector
• Retainer Halves
• Containment Ring
Inspection completed at.......................... Hrs. Date......................

Copyright © Textron Aviation Inc. Page 8 of 9

490007 Every 4500 APU running hours.

PATS GTCP36-150W APU.
Compressor Rotor:
• Visually check compressor rotor for damage by
observation through the compressor screen openings.
NOTE:
No damage allowed.
Inspection completed at.......................... Hrs. Date......................
Chapter 57 - Wings
570029 Applicable to airplanes with BC Winglets.
Every 300 hours.
Wing Outer, Upper and Lower Skins:
• Visually inspect between Ribs 14 and 16 around the
fasteners for cracking in the skins.
NOTE:
Pay particular attention to those fasteners installed between
the front and rear spars.
Inspection completed at.......................... Hrs. Date......................
Engine - General
720002 Whenever an engine is removed for a Major Periodic Inspection.
Aft cowling, inner fan duct and exhaust duct. Inspect with the
aft cowling removed.
Inspection completed at.......................... Hrs. Date......................
720003 Whenever an engine is removed for a Major Periodic Inspection.
Exhaust nozzle/exhaust pipe V clamp. Detail inspect,
particularly for cracks in the weld lines of the trunnion nut support
tubes, using a X 10 magnifier.
Inspection completed at.......................... Hrs. Date......................
Engine - Controls
760003 After 200 flying hours and not more than 300 flying hours from the
airplane build or after control cable replacement.
Control cables. Check the tensions of the:
• Power control cables (Ref. AMM 76-10-00, 501, in the
applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
Inspection completed at.......................... Hrs. Date......................
760004 Do any lubrication requirement for Area M1/M2, refer to Chapter
5, Lubrication.

Copyright © Textron Aviation Inc. Page 9 of 9

LUBRICATION

1. List of Effective Pages

Pages 1 thru 23, Issued Sep.16

Instructional Data
The illustrations in this part of the schedule indicate the points that require periodic lubrication and the method of lubrication. Grease
application is by grease gun except where indicated by a hand symbol. Oil application is indicated by an oil can symbol.
Unless otherwise indicated on the illustrations the lubricants are:-
Grease (Chapter 20 STANDARD PRACTICES - AIRFRAME, Ref. 125/H-20, 20-95-11, Item No. 078)
Oil (Chapter 20 STANDARD PRACTICES - AIRFRAME, Ref. 125/H-20, 20-95-101, Item No. 126)
The number within the balloon at each lubrication point on the illustration indicates the recommended interval between applications
of the lubricant, as detailed in Table 1.
The requirements identified in Figure 1 through Figure 4 should be done as well as and in conjunction with the items listed in the
"Lubrication Requirements" table.
Table 1. Lubrication Periods
1 Every 200 flying hours.
2 Every 400 flying hours.
3 Every 800 flying hours/Inspection B.
4 Every 1600 flying hours/Inspection C.
5 Every 3200 flying hours/Inspection D.
6 Every 12 months elapsed time/Inspection E.
7 Every 24 months elapsed time/Inspection F.
8 Every 48 months elapsed time/Inspection G.
Table 2. Lubrication Requirements
Monthly
Item Lubricant
Area G (Main Landing Gear and bay, Nose Landing Gear and bay).
NOTE:
If the airplane has been exposed to runway de-icing do this lubrication at monthly intervals.
Main landing gear sidestay shims (Ref. Figure 2 (Sheet 1and Corrosion Preventative Lubricant, AMM 20-95-11, Item 092.
Sheet 2, detail A)) Post Mod. 253549A or Pre SB. 32-3779
(Mod. 25G295A).

200 Hour
Item Lubricant
Area G (Main Landing Gear and bay, Nose Landing Gear and bay).
Nose landing gear steering and retraction mechanism (Ref. Oil, AMM 20-95-101, Item No. 126.
Figure 1, Sheet 1). Grease, AMM 20-95-11,Item 078.
Nose landing gear selector and dump valve (Ref. Figure 1, Sheet Grease, AMM 20-95-11, Item 034.
2).
Nose landing gear steering selector valve (Ref. Figure 1, Sheet Grease, AMM 20-95-11, Item 034.
2).
Main landing gear, inboard doors, reversing and sequence Oil, AMM 20-95-101, Item No. 126.
valves (Ref. Figure 2, Sheet 1). Grease, AMM 20-95-11,Item 034.
Grease, AMM 20-95-11,Item 078.

Copyright © Textron Aviation Inc. Page 1 of 19

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:40:39 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-20-11 (Rev A0)

Main landing gear sidestay shims (Ref. Figure 2 (Sheet 1and Corrosion Preventative Lubricant, AMM 20-95-11, Item 092.
Sheet 2, detail A)).
Emergency dump valve linkage and plunger (Ref. Figure 4, Sheet Oil, AMM 20-95-101, Item No. 126.
5, Item E). Grease, AMM 20-95-11, Item No. 034.

400 Hour
Item Lubricant
Area F1
Ventral fuel tank filler cap O-seals (if fitted). Grease, AMM 20-95-11, Item No. 078.
Refuelling coupling O-seals, (Ref. Figure 4, Sheet 1).
Security locks (if fitted) lubricate sparingly. Oil, AMM 20-95-101, Item No. 126.
Main entry door stay center and bottom joints, including lock Oil, AMM 20-95-101, Item No. 126.
rollers and mechanisms (Ref. Figure 4, Sheet 5,Item F). Grease, AMM 20-95-11, Item No. 078.
Rudder bias strut (Ref. Figure 4, Sheet 6, Item J). Oil, AMM 20-95-101, Item No. 126.
Area T1
Elevator and elevator tab hinges (Ref. Figure 3, Sheet 1). Oil, AMM 20-95-101, Item No. 126.
Elevator trim jack (Ref. Figure 3, Sheet 1). Pre Mod.25G138B or Pre Mod. 25G138F, or Pre SB 27-3840:
CAUTION: Grease, AMM 20-95-11, Item No. 078.
When lubricating the Elevator Trim Jack do not mix grease Mod.25G138B or Mod. 25G138F, or SB 27-3840: Grease, AMM
Item 078 with grease Item 094. 20-95-11, Item No. 094.
NOTE:
Mod.25G138B or SB 27-3840 introduces a replacement
grease for the Elevator Trim Jack.
NOTE:
Mod.25G138F introduces a replacement Elevator Trim
Jack.
Rudder and rudder tab hinges (Ref. Figure 4, Sheet 1). Oil, AMM 20-95-101, Item No. 126.
Rudder trim jack, (Ref. Figure 4, Sheet 1). Pre.Mod. 25G138C or Pre.Mod. 25G138E, or Pre. SB 27-3840:
CAUTION: Grease, AMM 20-95-11, Item No. 078.
When lubricating the Rudder Trim Jack do not mix grease Mod. 25G138C or Mod. 25G138E, or SB 27-3840: Grease,
Item 078 with grease Item 094. AMM 20-95-11, Item No. 094 .
NOTE:
Mod.25G138C or SB 27- 3840 introduces a grease change
from Item 078 to Item 094.
NOTE:
Mod. 25G138E introduces a replacement Rudder Trim
Jack.
Area W1/W2
Aileron and aileron tab hinges (Ref. Figure 3, Sheet 1). Oil, AMM 20-95-101, Item No. 126.

Copyright © Textron Aviation Inc. Page 2 of 19

Aileron trim jack (Ref. Figure 3, Sheet 1). Pre Mod.25G138A or Pre Mod. 25G138F, or Pre SB 27-3840:
CAUTION: Grease, AMM 20-95-11, Item No. 078.
When lubricating the Aileron Trim Jack do not mix grease Mod.25G138A or Mod. 25G138F, or SB 27-3840: Grease, AMM
Item 078 with grease Item 094. 20-95-11, Item No. 094.
NOTE:
Mod.25G138A or SB 27-3840 introduces a replacement
grease for the Aileron Trim Jack.
NOTE:
Mod.25G138F introduces a replacement Aileron Trim Jack.

Airbrake hinges (Ref. Figure 3, Sheet 1). Oil, AMM 20-95-101, Item No. 126.
Fuel tank filler cap seals (Ref. Figure 3, Sheet 1). Grease, AMM 20-95-11, Item No. 078.
Fuel tank filler cap locking handle recesses (AMM 28-10-44 in Grease, AMM 20-95-11, Item No. 078.
the applicable maintenance manual 750, 800XP, 800XP/850XP
Pro Line 21 or 900XP). GABB filler caps only, pack with grease
(Ref. Figure 3, Sheet 1).
Flap screwjack threads (Ref. Figure 3, Sheet 4, Item G). Clean Oil, AMM 20-95-101, Item No. 126.
and lightly lubricate.Flap screwjack (mount) trunnions (Ref. Figure
3, Sheet 4,Item G).
Flap synch linkage (Ref. Figure 3, Sheet 4,Item G).
Flap transmitter linkage (Ref. Figure 3, Sheet 4,Item G).
Flap screwjack yoke nut (Ref. Figure 3, Sheet 4,Item G). Grease, AMM 20-95-11, Item No. 040.
Airbrake trim jack and hinges (Ref. Figure 3, Sheet 4, Item H). Oil, AMM 20-95-101, Item No. 126.
Grease, AMM 20-95-11, Item No. 078.

Inspection B (800 Hour)

Item Lubricant
Area F1
Nose cone hinges and stays (Transferred to 1600 Hour lubrication).
Area F3
Escape hatch (Ref. Figure 4, Sheet 6, Item G). Grease, AMM 20-95-11, Item No. 078.
Area F4
Control cables and pressure seals (Ref. Figure 3, Sheet 1). Grease, AMM 20-95-11, Item No. 034.
Equipment bay door hinges (Transferred to 1600 Hour lubrication).
External baggage unit (EBU) loading door and hatch, hinges and Oil, AMM 20-95-101, Item No. 126.
latch mechanisms.
Area W1/W2
Wing transfer valve control (Ref. Figure 3, Sheet 4, Item E). Oil, AMM 20-95-101, Item No. 126. Grease, AMM 20-95-11, Item
No. 078.
LP and Crossfeed fuel valves controls (Ref. Figure 3, Sheet 4, Oil, AMM 20-95-101, Item No. 126.
Item F).
Flap drive system (Ref. Figure 3, Sheet 4,Item G). Oil, AMM 20-95-101, Item No. 126.
Aileron control cables and pressure seals (Ref. Figure 3, Sheet Grease, AMM 20-95-11, Item No. 034.
1).
Aileron operating mechanism (Ref. Figure 3, Sheet 4, Item J). Oil, AMM 20-95-101, Item No. 126.
Area G (Main Landing Gear and bay, Nose Landing Gear and bay).

Copyright © Textron Aviation Inc. Page 3 of 19

Nose gear leg lock and change-over microswitch operating Oil, AMM 20-95-101, Item No. 126.
mechanism (Ref. Figure 1, Sheet 1).
Nose gear door quick release strut (Ref. Figure 1, Sheet 1, Item Grease, AMM 20-95-11, Item No. 078.
A). Lubricate splines.
Main gear door uplock spring strut (Ref. Figure 2, Sheet 1). Grease, AMM 20-95-11, Item No. 078.
Lightly lubricate sliding surface.

Inspection C (1600 Hour)

Item Lubricant
Area F1
Nose cone hinges and stays (Ref. Figure 3, Sheet 1 and Figure Oil, AMM 20-95-101, Item No. 126.
4, Sheet 1).
Area F2
Center pedestal (Ref. Figure 3, Sheet 2, Item A, Item L and Oil, AMM 20-95-101, Item No. 126.
Sheet 3,Item B). Grease, AMM 20-95-11, Item No. 078.
Parking brake controls (Ref. Figure 4, Sheet 2,Item A). Oil, AMM 20-95-101, Item No. 126.
Auxiliary hydraulic system (Ref. Figure 4, Sheet 5,Item E). Oil, AMM 20-95-101, Item No. 126.
Nose landing gear mechanical indicator cable (Ref. Figure 1, Grease, AMM 20-95-11, Item No. 078. Grease, AMM 20-95-11,
Sheet 1) and AMM 32-66-00, 201 in the applicable maintenance Item No. 034.
manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
Bearing plate and rod end. Mechanical indicator shaft.
Sliding portion of the rod end.
Area F3
Drag spigot housing (Ref. Figure 3, Sheet 1). Repack with Pre.Mod.25G317B,Grease, AMM 20-95-11, Item No. 078.
grease. Mod.25G317B, Grease, AMM 20-95-11, Item No. 093
CAUTION:
If grease item 078 was installed on the drag spigot
housing; all traces of grease must be removed before
using item 093. Do not mix greases.
LP and Crossfeed fuel valves controls chain and sprockets (Ref. Grease, AMM 20-95-11, Item No. 078.
Figure 3, Sheet 4, Item F).
Wing transfer valve control cables and pressure seals (Ref. Grease, AMM 20-95-11, Item No. 034.
Figure 3, Sheet 4, Item E).
Ventral tank valve control (Ref. Figure 3, Sheet 4,Item M) (N/A Grease, AMM 20-95-11, Item No. 078.
750 airplane).
Main entry door shaft (Ref. Figure 4, Sheet 5, Item F). Grease, AMM 20-95-11, Item No. 078.
Area F4
Equipment bay door hinges (Ref. Figure 3, Sheet 1). Oil, AMM 20-95-101, Item No. 126.
Engine control assembly (Ref. Figure 4, Sheet 6, Item H) Oil, AMM 20-95-101, Item No. 126.
Area T1
Rudder trim jack chain and sprocket (Ref. Figure 4, Sheet 1). Grease, AMM 20-95-11, Item No. 078.
Elevator trim jack chain and sprocket (Ref. Figure 3, Sheet 1). Grease, AMM 20-95-11, Item No. 078.
Area W1/W2
Aileron trim jack chain and sprocket (Ref. Figure 3, Sheet 1). Grease, AMM 20-95-11, Item No. 078.
Flap drive system (Ref. Figure 3, Sheet 4). Remove gaiters, Grease, AMM 20-95-11, Item No. 040.
repack with grease, install gaiters.

Copyright © Textron Aviation Inc. Page 4 of 19

Inspection D (3200 Hour)

Item Lubricant
Area F2
Steering handwheel and chain (Ref. Figure 3, Sheet 4, Item D). Grease, AMM 20-95-11, Item 078.

Inspection E (12 Month)

Item Lubricant
Area F3
Escape hatch (Transferred to 800 Hour lubrication).
Area F4
Control cables and pressure seals (Transferred to 800 Hour lubrication).
Area W1/W2
Aileron control cables and pressure seals (Transferred to 800 Hour lubrication).

Inspection F (24 Month)

Item Lubricant
Area F1
Wing to fuselage attachment links, brackets and bolts. Corrosion Preventative Lubricant, AMM 20-95-11, Item 092.
Area F2
Flight controls below floor (Ref. Figure 3, Sheet 3, Item C). Oil, AMM 20-95-101, Item No. 126.
Grease, AMM 20-95-11, Item 078.
Landing gear selector controls (Ref. Figure 4, Sheet 2, Item B). Oil, AMM 20-95-101, Item No. 126.
Control columns (Ref. Figure 4, Sheet 3, Item C). Oil, AMM 20-95-101, Item No. 126.
Grease, AMM 20-95-11, Item No. 078.
Rudder pedal assemblies (Ref. Figure 4, Sheet 4,Item D). Oil, AMM 20-95-101, Item No. 126.
Grease, AMM 20-95-11, Item No. 078.
Area G (Main Landing Gear and bay, Nose Landing Gear and bay).
Nose landing gear mechanical indicator system (Transferred to 1600 Hour lubrication).

Inspection G (48 Month)

Item Lubricant
Nose landing gear mechanical indicator system (Transferred to Lubrication, 1600 Hour).

Between 1200 Hours and 2400 Hours

Area M1/M2
Thrust control teleflex cable and disconnect coupling.Lubricate Grease, AMM 20-95-11, Item No. 046 .
(Ref. AMM 76-10-01, page block 601 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
NOTE:
This task may be done during the removal of an Engine (AMM 71-00-01, 401 in the applicable maintenance manual 750,
800XP, 800XP/850XP Pro Line 21 or 900XP). or a Power Plant (AMM 71-00-03, 401 in the applicable maintenance manual
750, 800XP, 800XP/850XP Pro Line 21 or 900XP).

Copyright © Textron Aviation Inc. Page 5 of 19

Figure 1 : Sheet 1 : Nose Landing Gear

Copyright © Textron Aviation Inc. Page 6 of 19

Figure 1 : Sheet 2 : Nose Landing Gear

Copyright © Textron Aviation Inc. Page 7 of 19

Figure 2 : Sheet 1 : Main Landing Gear

Copyright © Textron Aviation Inc. Page 8 of 19

Figure 2 : Sheet 2 : Main Landing Gear

Copyright © Textron Aviation Inc. Page 9 of 19

Figure 3 : Sheet 1 : Fuselage, Wings and Horizontal Stabilizer

Copyright © Textron Aviation Inc. Page 10 of 19

Figure 3 : Sheet 2 : Fuselage, Wings and Horizontal Stabilizer

Copyright © Textron Aviation Inc. Page 11 of 19

Figure 3 : Sheet 3 : Fuselage, Wings and Horizontal Stabilizer

Copyright © Textron Aviation Inc. Page 12 of 19

Figure 3 : Sheet 4 : Fuselage, Wings and Horizontal Stabilizer

Copyright © Textron Aviation Inc. Page 13 of 19

Figure 4 : Sheet 1 : Fuselage, Vertical Stabilizer and Rudder

Copyright © Textron Aviation Inc. Page 14 of 19

Figure 4 : Sheet 2 : Fuselage, Vertical Stabilizer and Rudder

Copyright © Textron Aviation Inc. Page 15 of 19

Figure 4 : Sheet 3 : Fuselage, Vertical Stabilizer and Rudder

Copyright © Textron Aviation Inc. Page 16 of 19

Figure 4 : Sheet 4 : Fuselage, Vertical Stabilizer and Rudder

Copyright © Textron Aviation Inc. Page 17 of 19

Figure 4 : Sheet 5 : Fuselage, Vertical Stabilizer and Rudder

Copyright © Textron Aviation Inc. Page 18 of 19

Figure 4 : Sheet 6 : Fuselage, Vertical Stabilizer and Rudder

Copyright © Textron Aviation Inc. Page 19 of 19

INSPECTION B - 050110
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Inspection B is the top level inspection which covers the accomplishment of Inspections B1 to B12 inclusive. This must
be completed by every 800 hours.
NOTE:
Inspection B must only be signed when Inspections B1 to B12 inclusive have been completed. ALL within a single
tolerance window.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

INSPECTION B (Consists of Inspection B1 to B12 inclusive)

Aircraft Registration:
NOTE:
This inspection may only be signed off when ALL of the above inspections have been completed.

Copyright © Textron Aviation Inc. Page 1 of 1

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:41:33 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-21-01 (Rev A0)

INSPECTION B1 - 050120
1. Inspection
List of Effective Pages
Pages 1 thru 3, Issued Jun.13
Table 1. Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection B1 must be signed off only when accomplished in a phased method and must be completed every 800
hours.
Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Functional Tests
Aircraft Registration: Mechanic Inspector
Bonding Checks
200001 Control surfaces. Do a bonding check (Ref. 125/H-20, 20-10-5016).
200002 Refuel point earthing studs (3 off). Do a function test for bonding resistance
to the local structure (Ref. 125/H-20, 20-10-5016).
Air Conditioning
210002 Airplanes without the digital pressurization control system Mod. 25G726A/C or
Mod. 25G726B/C:
Ram air valve and dump valve.
• Do a check/test (Ref. AMM 21-10-155, 201, in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
Airplanes with the digital pressurization control system Mod. 25G726A/C or
Mod. 25G726B/C:
Ram air valve and vent valve.
• Do a check/test (Ref. AMM 21-10-155, 201, in the applicable
maintenance manual 750, or 900XP).
210003 Environmental control system.
• Do a function test of the Pressure regulator and shut off valve (PRSOV)
(Ref. AMM 21-10-76, 501, in the applicable maintenance manual 750,
800XP, 800XP/850XP Pro Line 21 or 900XP).
• Do a bench check of the PRSOV Overpressure switch (Ref. AMM 21-10-
78, 201, in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
Electrical Power
240002 No.1 and No.2 main static inverters. Operate inverters and make sure, by feel
of hand, of a positive airflow output from the inverter cooling fans.

Copyright © Textron Aviation Inc. Page 1 of 2

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Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-21-01 (Rev A0)

240009 D.C. generating system.

• Do a function test of the emergency contactor control (Ref. AMM 24-30-
01, 501, in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
Fire Protection
260002 Rear equipment bay overheat detection system.
• Do a functional test (Ref. AMM 26-10-00, 201, in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
Fuel
280001 Fuel Transfer System, Wing tanks. Check fuel flow.
• Check for positive flow from the LH and the RH wing tank to the opposite
wing tank.
NOTE:
For positive flow note a 200lb increase in the fuel gauge indication.
Ice and Rain Protection
300001 Rotary ice detector. Do a function test (Ref. AMM 30-80-00, 501, in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
300002 Transferred to Inspection C1.
Lights
330003 Anti-Collision light system that has a strobe type device in any position.
• Clean the strobe light lenses internal and external.
• Clean the wing-tip lens covers internal and external.
• Check the strobe light flash rate (Flash rate of 60 ± 5cycles per minute),
(Ref. AMM 33-40-12, 201 (in the applicable maintenance manual 750,
800XP, 800XP/850XP Pro Line 21 or 900XP)).
NOTE:
Refer to the Component Requirements section of this manual for the
manufacturer's recommended period for replacement and strobe light
intensity test procedure.
Doors
520002 Transferred to Inspection C1.
Engine - Exhaust
780007 Task deleted.

Copyright © Textron Aviation Inc. Page 2 of 2

INSPECTION B2 - 050130
1. Inspection
List of Effective Pages
Pages 1 thru 3, Issued Jun.12
Table 1. Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection B2 must be signed off only when accomplished in a phased method and must be completed every 800
hours.
Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Functional Tests
Aircraft Registration: Mechanic Inspector
Flight Controls
270004 Stall warning and identification system.
• Do a functional test of the stall warning and identification system (Ref. AMM
27-33-00, 501 in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
• Do an angle verification check (Ref. AMM 27-33-00, 501 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
• Do an electrical zero check (Ref. AMM 27-33-00, 501 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
NOTE:
The electrical zero check is only applicable to airplanes with Mod. 25G206A
or Mod. 25G206A and Mod. 25G206B.
270005 Task deleted.
270006 Task deleted.
270007 Task deleted.
270008 Rudder bias strut heater muffs.
• Do a functional test of the rudder bias strut heater muff (Ref. AMM 27-20-
00, 501 in the applicable maintenance manual 750, 800XP, 800XP/850XP
Pro Line 21 or 900XP).
270009 Stall detector unit (third channel). Do a function test:
• 800XP airplanes (Ref. AMM 27-33-14).
• 800XP/850XP Pro Line 21 airplanes (Ref. AMM 27-33-14).
NOTE:
This task is only applicable to 800XP and 800XP/850XP Pro Line 21
airplanes Pre Mod. 25G206A
OR
Pre Mod. 25G206A and 25G206B.

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:41:35 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-21-02 (Rev A0)

270010 Task deleted, covered by task 270001(Inspection A1).

Oxygen
350004 Transferred to Inspection E2.
350005 Transferred to Inspection E2 .

Copyright © Textron Aviation Inc. Page 2 of 2

INSPECTION B3 - 050140
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08
Table 1. Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection B3 must be signed off only when accomplished in a phased method and must be completed every 800
hours.
Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area F1: External fuselage, nose cone, tail cone and wing-to-fuselage fairing.
Access: Panel F3 removed. Nose cone F1 open. Tail cone F2 removed.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe.
(b) Electrical.
050141 (c) Avionics.
NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements
detailed in Para.(6) of the Introduction at the front of this schedule.
Doors
520003 Transferred to Inspection C3.
Windows
560005 Passenger cabin windows:
• Satisfactory condition of seals and no signs of moisture ingress.
• If you find moisture, renew Silica Gel crystals and verify seal
integrity (AMM 56-00-00, 201 in the applicable maintenance
manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
NOTE:
Pre Mod. 25G360A ONLY.

General Lubrication
Aircraft Registration: Mechanic Inspector
120009 Task deleted (requirement transferred to 1600 Hour Inspection)

Copyright © Textron Aviation Inc. Page 1 of 1

INSPECTION B4 - 050150
1. Inspection
List of Effective Pages
Pages 1 thru 3, Issued Dec.13
Table 1. Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the Introduction section at the
front of this schedule.
NOTE:
Inspection B4 must be signed off only when accomplished in a phased method and must be completed every 800
hours.
Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area F2: Flight compartment. Access: As visible.

Aircraft Registration: Mechanic Inspector
Air Conditioning
210004 Airplanes without the digital pressurization control system
Mod. 25G726A/C or Mod. 25G726B/C:
Manual cabin altitude control valve.
• Make sure of full and free movement.
Equipment/Furnishings
250007 Crew Seats.
• Do an operational check (Ref. CMM 25-11-24, 501 (Check 1)) or
(Ref. CMM 25-11-67, 501 (Check 1)).
Flight Controls
270011 Gust lock, ailerons and elevators.
• Inspect.
• Make sure that the bush in the mounting bracket is lightly lubricated
and free from burrs or scores.
• With the unit in the operated and locked position but without the
engagement of the claw spigots in the control column bushes,
check for positive spring pressure on the claws and for initial
resistance to movement when releasing the knurled locking ring.
Landing Gear
320022 Brake master cylinders.
• Check fluid level and replenish, as necessary (Ref. AMM 32-40-
00, 301, in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
Oxygen

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:41:36 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-21-04 (Rev A0)

350001 Oxygen system master supply valve:

• With the oxygen system fully charged and the supply master valve
closed, exhaust system downstream of the valve until the contents
gauge indicates zero.
• After 15 minutes has elapsed, make sure that there is no increase
in the contents gauge indication which would show leakage past
the closed valve.
350006 Task transferred to Inspection E4
Windows
560006 Windshield panel 'C' Silica Gel container:
• Inspect Silica Gel crystals for discoloration.
• Renew as necessary.
Engine Controls
760001 Throttle lever controls.
• Correct operation of the gust lock operated thrust lever baulk (Ref.
AMM 27-72-00, 501, in the applicable maintenance manual 750,
800XP, 800XP/850XP Pro Line 21 or 900XP).

General Lubrication
Aircraft Registration: Mechanic Inspector
120010 Task deleted.

Copyright © Textron Aviation Inc. Page 2 of 2

INSPECTION B5 - 050160
1. Inspection
List of Effective Pages
Page 1 and 2 Issued Jun.11
Table 1. Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection B5 must be signed off only when accomplished in a phased method and must be completed every 800
hours.
Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area F3: Vestibule, passenger cabin and toilet compartment (underfloor). Access: As necessary.
Aircraft Registration: Mechanic Inspector
NOTE:
No underfloor inspections required at this time.
General Lubrication
Aircraft Registration: Mechanic Inspector
120011 Task deleted.

Copyright © Textron Aviation Inc. Page 1 of 1

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:41:37 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-21-06 (Rev A0)

INSPECTION B6 - 050170
1. Inspection
List of Effective Pages
Pages 1 thru 4, Issued Sep.08
Table 1. Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection B6 must be signed off only when accomplished in a phased method and must be completed every 800
hours.
Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area F3: Vestibule, passenger cabin and toilet compartment (above floor).
Access: Radio compartment access panels removed.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe.
(b) Electrical.
(c) Avionics.
050171
NOTE:
Make sure ALL area inspections are done in accordance
with the Inspection Requirements detailed in Para.(6) of the
Introduction at the front of this schedule.
Equipment/Furnishings
250003 3rd crew members seat (if fitted):
• Make sure that the seat stowing action is satisfactory.
• Make sure of correct operation and satisfactory condition.
NOTE:
To be done at this inspection or at a period conforming to
the requirements of the local regulatory authority.
Ice and Rain Protection
300003 Airframe de-icing system pressure filter.
• Replace the filter element (AMM 30-10-52, 201 in the
applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
Water/Waste

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:41:38 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-21-06 (Rev A0)

380001 Water systems:

• Inspect the toilet and galley water systems.
• Make sure the flow of water is correct through the normal
and overflow drains and that there are no leaks.
If you find signs of fluid leakage:
• Inspect the aileron-cable fuselage pressure-seals and the
adjacent structure in the areas to the rear of frame 16. Do
this to make sure the fluid leakage has drained correctly.
• Make sure the drain holes and drain valves are free from
blockages and function correctly. Do this from the inside
and the outside of the fuselage.
• Remove all fluid remaining in the area.
• Clean the areas where leakage has occurred.
• Lubricate the aileron cables if necessary (AMM 12-20-25,
201 in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
• AMM 12-38-00 Replenish the toilet and galley water
systems, if required:
800XP airplanes (AMM 12-38-00 or MMA Chapter 38 as
applicable).
800XP/850XP Pro Line 21 airplanes (AMM 12-38-00 or
MMA Chapter 38 as applicable).
750 airplanes (MMA Chapter 38).
900XP airplanes (MMA Chapter 38).
Doors and Hatches
520004 Transferred to Inspection C6.
520005 Escape hatch release mechanism. Check the operating load
using the external push button (AMM 52-20-00, 401 in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP).
520006 Escape hatch seals. Inspect for total seal contact with airframe
structure to prevent ingress of rainwater when the cabin is
unpressurized.

General Lubrication
Aircraft Registration: Mechanic Inspector
120012 Do any 800 hour lubrication requirements for Area F3, refer to
Chapter 5, Lubrication.

Copyright © Textron Aviation Inc. Page 2 of 2

INSPECTION B7 - 050180
1. Inspection
List of Effective Pages
Pages 1 thru 3, Issued Sep.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection B7 must be signed off only when accomplished in a phased method and must be completed every 800
hours.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area F4: Rear equipment bay and rear fuselage.

Access: As visible with bay door open. panels F169 and F170 removed.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe.
(b) Engines.
(c) Electrical.
050181 (d) Avionics.
NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements
detailed in Para.(6) of the Introduction at the front of this schedule.
Air Conditioning
210005 Cooling turbine exhaust duct drain. Make sure the
drain is free from blockages.
210006 Transferred to Out of Phase Inspections.
210007 Transferred to Out of Phase Inspections.
210024 Low limit temperature Control Valve Filter (If installed)
.
• Clean or replace (AMM 21-60-61, 201 in the
applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
NOTE:
This task is only applicable to airplanes with a
Honeywell GTCP36-150W APU, installed to
STC ST00459NY.
Hydraulic Power

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:41:39 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-21-07 (Rev A0)

290003 Suction filter . Replace the element (AMM 29-10-21, 401

in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).

Doors
520011 External Baggage Unit (EBU) loading Door (750
Airplanes)
• Do a detailed visual inspection of the baggage
door latch and pin assemblies.
Engine - Fuel and Control
730001 PT2 pipelines to fuel computers. Drain any
accumulations of water from the drain points.
Engine - Exhaust
NOTE:
Before doing Thrust Reverser inspections make sure ALL related Service Bulletins have been examined and obey any
related Airworthiness Directive.
NOTE:
Any part showing signs of wear or defect should be replaced or overhauled at the time of the inspection.
780010 Thrust Reversers.
• Inspect the hydraulic lines for signs of leakage.
• Inspect the wire harness for any chafing in the area
of the hydraulic control valve.

General Lubrication
Aircraft Registration: Mechanic Inspector
120013 Do any 800 hour lubrication requirements for Area F4,
refer to Chapter 5, Lubrication.

Copyright © Textron Aviation Inc. Page 2 of 2

INSPECTION B8 - 050190
1. Inspection
List of Effective Pages
Pages 1 thru 3, Issued Jan.08
Table 1. Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection B8 must be signed off only when accomplished in a phased method and must be completed every 800
hours.
Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area T1: Horizontal and vertical stabilizers, to include elevators and rudder. Access: Panels T18, T43L and T44R are
removed.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe.
(b) Electrical.
050191 (c) Avionics.
NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements
detailed in Para.(6) of the Introduction at the front of this schedule.
Flight Controls
270012 Rudder trim tab and anti-servo tab.
• Check the free movement (backlash) at the trailing edges
of the tabs (AMM 27-20-00, 501 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP).
• While the connecting rods are disconnected check the
rear rod-end bearings for smooth operation.
• Detail inspect the connecting rod attachment lugs on the
tabs for cracks using a X 10 magnifier.
NOTE:
Do not remove the protective coating unless a defect, or
suspected defect, is found.

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:41:40 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-21-08 (Rev A0)

270013 Elevators and trim tabs.

• Check the free movement (backlash) at the trailing edges
of the tabs (AMM 27-30-00, 501 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP).
• While the connecting rods are disconnected check the
rear rod-end bearings for smooth operation.
• Detail inspect the connecting rod attachment lugs on the
trim tabs for cracks, using a X 10 magnifier.
NOTE:
Do not remove the protective coating unless a defect, or
suspected defect, is found.
270014 Rudder and elevators primary surfaces. Make sure of full
and free movement from stop to stop.

General Lubrication
Aircraft Registration: Mechanic Inspector
120014 Task deleted.

Copyright © Textron Aviation Inc. Page 2 of 2

INSPECTION B9 - 050200
1. Inspection
List of Effective Pages
Pages 1 thru 3, Issued Jun.13
Table 1. Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection B9 must be signed off only when accomplished in a phased method and must be completed every 800
hours.
Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area W1: Wing LH.

Access: Flaps lowered and airbrakes open. Main landing gear doors open. Panels W139, W140, W141, W324, W325,
W414, W415, W419, W422, W424, W425, W432, W436, W437, W509, W509A, W510, W510A, W511 and W512 removed.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe.
(b) Electrical.
050201 (c) Avionics.
NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements detailed
in Para.(6) of the Introduction at the front of this schedule.
Flight Controls
270015 Aileron primary surfaces. Make sure of full and free movement from
stop to stop and that all accessible aileron pulleys rotate freely.
270016 Aileron trim and servo tabs.
• Check the free movement (backlash) at the trailing edges of
the tabs (Ref. AMM 27-10-00, 501 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21
or 900XP).
• While the connecting rods are disconnected inspect the rear
rod-end bearings for smooth operation.
• Detail inspect the connecting rod attachment lugs on the tabs
for cracks using a X 10 magnifier.
NOTE:
Do not remove the protective finish unless a defect, or a
suspected defect is found.
270066 Aileron Control cable pressure seals. Inspect for wear.

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:41:41 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-21-09 (Rev A0)

270003 Flap screwjacks . Inspect the screw threads for satisfactory

condition.
270017 Flap Screwjack and reduction gearbox.
• Check the gearbox fluid level (Ref. AMM 27-50-141, 301 in the
applicable maintenance manual 750, 800XP, 800XP/850XP
Pro Line 21 or 900XP).
270018 Flap synchronization system control cables.
• Inspect for fraying, particularly in the vicinity of the pulleys.
• Make sure accessible pulleys rotate freely.
Flight Controls (Continued)
270019 Flap control unit .
• Check the gearbox fluid level (Ref. AMM 27-50-121, 301 in the
applicable maintenance manual 750, 800XP, 800XP/850XP
Pro Line 21 or 900XP).
270020 Flap control unit.
• Do a flap control unit neutral selection check (Ref. AMM 27-50-
02, 501 in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
270021 Flap drive shafts. Inspect for signs of corrosion and for movement
between the end fittings and the shafts.
Wings
570001 Flap hinge fittings. Inspect.
NOTE:
Inspect the bolt head on the bottom skin of the flap (in the area
of the inboard hinge) adjacent to flap screw jack carriage
grease fitting for damage caused by chafing. If damage is
found, replace the bolt.
NOTE:
For details of the repair kit refer to Textron Aviation Technical
Support (1.800.429.5372 OR 316.676.3140).

General Lubrication
Aircraft Registration: Mechanic Inspector
120015 Do any 800 hour lubrication requirements for Area W1, refer to
Chapter 5, Lubrication.

Copyright © Textron Aviation Inc. Page 2 of 2

INSPECTION B10 - 050210

1. Inspection
List of Effective Pages
Pages 1 thru 3, Issued Sep.15
Table 1. Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection B10 must be signed off only when accomplished in a phased method and must be completed every 800
hours.
Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area W2: Wing RH.

Access: Flaps lowered and airbrakes open. Panels W239, W240, W241, W314, W315, W319, W322, W332, W336, W337,
W509, W509A, W510, W510A, W511 and W512 removed.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe.
(b) Electrical.
050211 (c) Avionics.
NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements
detailed in Para.(6) of the Introduction at the front of this schedule.
Flight Controls
270022 Aileron primary surfaces. Make sure of full and free movement from stop to stop
and that all accessible aileron pulleys rotate freely.
270023 Aileron servo tabs.
• Check the free movement (backlash) at the trailing edges of the tabs (Ref.
AMM 27-10-00, 501 in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
• While the connecting rods are disconnected inspect the rear rod-end
bearings for smooth operation.
• Detail inspect the connecting rod attachment lugs on the tabs for cracks
using a X 10 magnifier.
NOTE:
Do not remove the protective finish unless a defect, or a suspected defect
is found.
270067 Aileron Control cable pressure seals. Inspect for wear.

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:41:42 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-21-10 (Rev A0)

270024 Flap Screwjack and reduction gearbox.

• Check the gearbox fluid level (Ref. AMM 27-50-141 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
270025 Flap synchronization system control cables.
• Inspect for fraying, particularly in the vicinity of the pulleys.
• Make sure accessible pulleys rotate freely.
270026 Flap drive shafts. Inspect for signs of corrosion and for movement between the
end fittings and the shafts.
Flight Controls Cont.
270065 Flap screw jacks. Inspect the screw threads for satisfactory condition.
Wings
570002 Flap hinge fittings. Inspect.
NOTE:
Inspect the bolt head on the bottom skin of the flap (in the area of the
inboard hinge) adjacent to flap screw jack carriage grease fitting for
damage caused by chafing. If damage is found, replace the bolt.
NOTE:
For details of the repair kit contact Textron Aviation Customer Support.
Refer to the Introduction, How to Get Customer Assistance.

General Lubrication
Aircraft Registration: Mechanic Inspector
120016 Do any 800 hour lubrication requirements for Area W2, refer to chapter 5,
Lubrication.

Copyright © Textron Aviation Inc. Page 2 of 2

INSPECTION B11 - 050220

1. Inspection
List of Effective Pages
Pages 1 thru 5, Issued Mar.16
Table 1. Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection B11 must be signed off only when accomplished in a phased method and must be completed every 800
hours.
Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area M1, M2: Engine installation and pylon, LH and RH.

Access: Engine cowlings M1L, M2R, M3L and M4R removed. Pylon access panels M9L, M10R, M11L, M12R, M13L,
M14R, M19L and M20R removed.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Engines.
(b) Airframe.
050221 (c) Electrical.
NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements
detailed in Para.(6) of the Introduction at the front of this schedule.
Engine - Air
750001 NOTE:
This task is only applicable to Hawker 900XP airplanes.
Engine Bleed System.
• Inspect the bleed air port low pressure (LP) venturi gasket
for signs of deterioration, deep discoloration, cracks or
missing pieces of gasket and replace as necessary.
Engine - Exhaust
NOTE:
Before doing Thrust Reverser inspections make sure ALL related Service Bulletins have been examined and obey any
related Airworthiness Directive.
NOTE:
Any part showing signs of wear or defect should be replaced or overhauled at the time of the inspection.
Engine - Exhaust Cont.

Copyright © Textron Aviation Inc. Page 1 of 3

780001 Link arm assemblies (8 off).

• Remove the link arms (Ref. AMM 78-31-10, in the
applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
• Inspect the attachment bolts (16 off), particularly for signs of
corrosion and/or seizing.
• Replace any bolts that show signs of corrosion and/or
seizing.
• Lubricate the bolt shafts and threads before installation,
using a dry film lubricant to specification MIL-PRF-907, C5-
A (non-aerosol) Item 084 (Ref. AMM 20-95-11).
• Install the link arms (Ref. AMM 78-31-10, 401 in the
applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
780002 Reverser door seals.
• Inspect for correct seating (Ref. AMM 78-31-20, 501 in the
applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
• Inspect for cracks and wear.
• Make sure the material is pliable.
780009 Thrust Reversers.
• Inspect the afterbody and make sure it is correctly
attached.
• Inspect the doors for corrosion and wear.
• Detail inspect the doors for cracks.
• Inspect the fan flaps for signs of fatigue and make sure they
are correctly attached and stow completely.
• Detail inspect the fan flaps for cracks.
780011 Exhaust nozzle.
• Detail inspect for cracks.
Engine - Exhaust Cont.
780012 Hydraulic Lines.
• Make sure the hydraulic lines are correctly attached.
• Inspect for leaks.
• Inspect the sleeving material for signs of chafing.
780013 Wire harness.
• Make sure the wire harness in the thrust reverser and
afterbody is correctly attached.
• Inspect for signs of chafing.
780014 Fan duct.
• Inspect for signs of corrosion and fatigue.
• Detail inspect for cracks.
• Inspect the contour and general condition of the fan duct
fairings.
780015 Latch box springs.
• Inspect for signs fatigue.
• Detail inspect for cracks.

Copyright © Textron Aviation Inc. Page 2 of 3

780016 Latch monitoring switches.

• Do an operational test (Ref. AMM 78-33-50,
ADJUSTMENT/TEST, 401 in the applicable maintenance
manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
780017 Latches and latch receptacles.
• Inspect for wear (78-31-35, INSPECTION/CHECK, 601 in
the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
780018 Primary (Ref. AMM 78-32-40, in the applicable maintenance
manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP.)and
Latch (Ref. AMM 78-32-50 in the applicable maintenance manual
750, 800XP, 800XP/850XP Pro Line 21 or 900XP)hydraulic
actuators.
• Inspect for leaks, corrosion or wear.
• Detail inspect for cracks.
Engine - Exhaust Cont.
780019 Throttle Retard hydraulic actuators (Ref. AMM 78-32-30, in
the applicable maintenance manual 750, 800XP, 800XP/850XP
Pro Line 21 or 900XP).
• Inspect for leaks, corrosion or wear.
• Detail inspect for cracks.
• Detail inspect the actuator housing at the bearing on the
Throttle Retard.
780020 Fan Flap hydraulic actuators (Ref. AMM 78-32-60, in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP).
• Inspect for leaks, corrosion or wear.
• Detail inspect for cracks.
• Detail inspect the actuator housing at the bearing on the
Fan Flap.
780021 Pylon Plug.
• Make sure the pylon plug fairings M17L and M18R are
correctly installed and make a continuous surface with the
pylon.

General Lubrication
Aircraft Registration: Mechanic Inspector
120017 Task deleted.

Copyright © Textron Aviation Inc. Page 3 of 3

INSPECTION B12 - 050230

1. Inspection
List of Effective Pages
Pages 1 thru 5, Issued Mar.12
Table 1. Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection B12 must be signed off only when accomplished in a phased method and must be completed every 800
hours.
Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Functional Tests
Aircraft Registration: Mechanic Inspector
Flight Controls
270027 Flap control system. Do a function test (Ref. AMM 27-50-02, 501 in
the applicable maintenance manual 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP).
270028 Airbrake and lift dump system.
• Do a functional test (Ref. AMM 27-61-02, 501 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
Hydraulic Power
290004 Main hydraulic system.
• At system shutdown check the pressure dissipation time on the
main pressure accumulator (Ref. AMM 29-10-00, 501 in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP).
290005 Landing gear and flaps emergency lowering system. Do an
operational test (Ref. AMM 29-20-00, 501 in the applicable maintenance
manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
290009 Auxiliary reservoir low-level warning system. Do a function test
(Ref. AMM 29-30-00, 201.in the applicable maintenance manual 750,
800XP, 800XP/850XP Pro Line 21 or 900XP).
NOTE:
Do this task in conjunction with Task # 290005.
Landing Gear

Copyright © Textron Aviation Inc. Page 1 of 4

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:41:43 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-21-12 (Rev A0)

320001 Braking systems.

• Do a test of the emergency and parking brake system operation
(Ref. AMM 32-40-00, 501 in the applicable maintenance manual
750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
320002 Maxaret Units.
• Do a function test (Ref. AMM 32-40-101, 501 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).

Area G : Nose gear, main landing gear, nose gear bay and main landing gear bays. Access: Nose and main landing
gear bay doors open.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe
(b) Electrical
050231 NOTE:
Make sure ALL area inspections are done in accordance with the
Inspection Requirements detailed in Para.(6) of the Introduction at
the front of this schedule.
Landing Gear
320003 Nose gear leg assembly:
• Make sure oil level and gas pressures are correct (Ref. AMM 32-
20-12, 301 in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
• Check the leg extension (Ref. AMM 12-32-00, 301 in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP).
320004 Nose gear leg lock and change-over microswitches operating
mechanism. Make sure of freedom of operation.
320005 Nosewheel steering jack:
• Inspect for satisfactory condition.
NOTE:
Pay particular attention to scores and the cleanliness of the jack
ram.
320006 Nose gear retraction and steering system spring struts. Inspect.
320007 Nosewheel steering ON/OFF valve. Inspect.
320008 Nose gear drag stay assembly. Check clearances (Ref. AMM 32-20-
21, 601 in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
320009 Nosewheel steering jack selector valve:
• Service: Clean and grease the selector valve spring housing and
parts (Ref. AMM 32-50-11, 301 in the applicable maintenance
manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP.)
320037 Nose leg assembly torque links. Examine the torque link pivots for
wear (Ref. AMM 32-20-12, 601 in the applicable maintenance manual
750, 800XP, 800XP/850XP Pro Line 21 or 900XP).

Copyright © Textron Aviation Inc. Page 2 of 4

Landing Gear Cont.

320010 Main gear leg assemblies
• Make sure oil level and gas pressures are correct (Ref. AMM 32-
10-12,301 in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
• Check the leg extension (Ref. AMM 12-32-00, 301 in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP. ).
320011 Main landing gear side-stays.
• Inspect the center joint nut for distortion (Ref. AMM 32-10-25, 601
in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
• Check the side-stay clearances (Ref. AMM 32-10-25, 501 in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP).
320012 Main landing gear torque links. Examine the torque link pivots for wear
(Ref. AMM 32-10-12, 601 in the applicable maintenance manual 750,
800XP, 800XP/850XP Pro Line 21 or 900XP).
320033 Main gear retraction actuator (Ref. AMM 32-30-27, 401 in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21
or 900XP).
NOTE:
To do this inspection, disconnect the cylinder head end of the
actuator. Do not disconnect the hydraulic lines.
• Detail inspect the actuator attachment lugs.
320013 Main landing gear doors.
• Inspect the hinge bracket assemblies for security and tightness of
the nuts.
• Inspect jack attachment brackets and adjacent structure for
cracks.
• Inspect for signs of movement of the forward hinge brackets and
bolts at their attachment to the wing structure by attempting to rock
the doors in the longitudinal and transverse directions.
NOTE:
If the brackets are found to be loose, inspect the attachment bolt
holes and bolts for wear and corrosion.
320014 Main landing gear door uplock spring struts.
• Inspect.
• Clean the sliding surfaces.
• Make sure of correct operation:Check initial breakout/first
movement of the spring strut occurs at 19 lb ±2 lb.Make sure
movement of the strut is free over the length of the stroke.
Landing Gear Cont.
320015 Reversing valves and operating mechanisms:
• Disconnect from the side stay.
• Inspect for satisfactory condition.
• Make sure the mechanisms are free to move correctly.
• Connect to the side stay.

Copyright © Textron Aviation Inc. Page 3 of 4

320034 Plunger Tube/Axle Joint

• Inspect the flexible seal at the plunger tube to axle joint.
• Make sure the seal is not loose or cracked.
• Rectify as necessary (Ref.AMM Chapter 32, MAIN LEG
ASSEMBLY, 501 in the applicable maintenance manual 750,
800XP, 800XP/850XP Pro Line 21 or 900XP).

General Lubrication
Aircraft Registration: Mechanic Inspector
120018 Do any 800 hour lubrication requirements for Area G,
refer to chapter 5, Lubrication.

Copyright © Textron Aviation Inc. Page 4 of 4

INSPECTION C - 050240
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Inspection C is the top level inspection which covers the accomplishment of Inspections C1 to C12 inclusive. This must
be completed by every 1600 hours.
NOTE:
Inspection C must only be signed when Inspections C1 to C12 inclusive have been completed. ALL within a single
tolerance window.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

INSPECTION C (Consists of Inspection C1 to C12 inclusive)

Aircraft Registration:
NOTE:
This inspection may only be signed off when ALL of the above inspections have been completed.

Copyright © Textron Aviation Inc. Page 1 of 1

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:41:44 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-22-01 (Rev A0)

INSPECTION C1 - 050250
1. Inspection
List of Effective Pages
Pages 1 and 2 Issued Sep.08
Table 1. Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection C1 must be signed off only when accomplished in a phased method and must be completed every 1600
hours.
Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Functional Tests
Aircraft Registration: Mechanic Inspector
Air Conditioning
210020 Electrically actuated auxiliary heat valve.
• Do a functional test (AMM 21-60-105, 201 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
NOTE:
This test may be done without engine bleed air.
Electrical Power
240003 Transferred to Inspection D1.
240004 Busbar contactor control.
• Set the bustie switch to CLOSE.
• Trip the LH generator off-line.
• Make sure all d.c. busbars are energized.
• Reset the LH generator.
• Trip the RH generator off-line.
• Make sure all d.c. busbars are energized.
• Reset the RH generator.
Ice and Rain Protection
300002 Windshield electrical de-icing system. Do an operational test of the
windscreen overheat (AMM 30-41-00, 501 in the applicable maintenance
manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
300004 Pitot head and static plate heaters. Do a function test (AMM 30-35-15,
501 in the applicable maintenance manual 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP).
Doors

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:41:45 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-22-01 (Rev A0)

520002 Baggage pannier loading door/upper hatch warning system (if fitted)
OR External baggage unit (EBU) (750 airplanes ONLY).
• Test for correct operation (AMM 52-30-05).
NOTE:
This test is only applicable to airplanes with a baggage pannier in
place of the ventral fuel tank OR 750 airplanes with external baggage
unit .

Copyright © Textron Aviation Inc. Page 2 of 2

INSPECTION C2 - 050260
1. Inspection
List of Effective Pages
Pages 1 and 2 Issued Jan.08
Table 1. Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection C2 must be signed off only when accomplished in a phased method and must be completed every 1600
hours.
Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Functional Tests
Aircraft Registration: Mechanic Inspector
Flight Controls
270029 Task deleted.
270030 Elevator trim servo.
• Operate the elevator
trim switch on the left, or
right, control column.
• As the elevator trim
servo motor operates
the elevator trim tabs,
hold the manual elevator
trim wheel with sufficient
force to stop the trim
wheel.
• The force needed to
stop the trim wheel must
not be more than 15 lbs.

Copyright © Textron Aviation Inc. Page 1 of 1

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:41:46 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-22-03 (Rev A0)

INSPECTION C3 - 050270
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Mar.12

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection C3 must be signed off only when accomplished in a phased method and must be completed every 1600
hours.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area F1: External fuselage, nose cone, tail cone, ventral fuel tank/EBU and wing-to- fuselage fairings
Access: Panels F4, F122, F123, F222, F223, W502, W503, W511 and W512 removed.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe.
(b) Electrical.
(c) Avionic.
050271 NOTE:
Make sure ALL area inspections are done in accordance
with the Inspection Requirements detailed in Para.(6) of the
Time Limits/Maintenance Checks at the front of this
schedule.
Flight Controls
270031 Requirement deleted. Covered by Inspection B12 task # 270027.
Doors
520003 Baggage pannier door (if fitted) OR External baggage unit
(EBU) (750 airplanes ONLY). Inspect AMM 52-30-05, 601, in
the applicable maintenance manual 750 or 800XP:
• The door seal for damage, distortion and maintained
shape profile.
• Seal for adhesion to the door lip.
• Seal to door surround interface for potential leakage.
• Door surround surface for damage which would prevent
good sealing.
NOTE:
This test is only applicable to airplanes with a baggage
pannier in place of the ventral fuel tank OR 750 airplanes
with external baggage unit.

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:41:47 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-22-03 (Rev A0)

General Lubrication
Aircraft Registration: Mechanic Inspector
120019 Do any 1600 hour lubrication requirements for Area F1, refer to
chapter 5, Lubrication.

Copyright © Textron Aviation Inc. Page 2 of 2

INSPECTION C4 - 050280
1. Inspection
List of Effective Pages
Pages 1 thru 3, Issued Mar.12

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection C4 must be signed off only when accomplished in a phased method and must be completed every 1600
hours.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area F2: Flight compartment.

Access: Under seat sidewall panels F16 and F17 removed. Center pedestal panels F11 and F12 removed. Step panel
F55 removed. Panels F14, F41, F42, F43, F44, F45, F46 and F47 removed.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe.
(b) Electrical.
(c) Avionic.
050281 (d) Engine.
NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements
detailed in Para.(6) of the Introduction at the front of this schedule.
Air Conditioning
210008 Airplanes without the digital pressurization control system Mod.
25G726A/C or Mod. 25G726B/C:
Cabin pressure outflow/safety valve controller .
• Visually inspect and make sure that the cabin air sense port
screen is clear.
Flight Controls

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:41:48 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-22-04 (Rev A0)

270032 Aileron autopilot servo control cables . Check cable tensions

are correct:
• 750 airplanes (Ref. AMM 27-00-00, 201 and 22-10-10,
401).
• 800XP airplanes (Ref. AMM 27-00-00, 201 and 27-10-93,
401).
• 800XP/850XP Pro Line 21 airplanes (Ref. AMM 27-00-00,
201 and 22-10-10, 401).
• 900XP airplanes (Ref. AMM 27-00-00, 201 and 22-10-10,
401).

270033 Elevator control system balance/feel spring . Inspect.

Landing Gear
320016 Steering system cables and chains .
• Make sure cable tensions are correct (Ref. AMM 32-50-00,
in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP
320023 Brake hoses to master cylinders. Make sure of an adequate
clearance between the hoses and the floor over the full range of
rudder pedal travel.
Navigation
340003 Autopilot aileron servo unit and mount .
• Inspect, particularly for cable and capstan wear,
contamination, cable spool-off angle and security of the
servo unit and mount.
• With the autopilot disengaged operate the control system
throughout the entire range and make sure there is no
unusual noise, binding, backlash or signs of other
mechanical irregularities from the servo mount.
Engine - Exhaust
780003 Thrust reverser stow/deploy microswitches .
• Test microswitches coded CWA or CXA (Ref. AMM 78-34-
20, 201, 201 in the applicable maintenance manual 750,
800XP, 800XP/850XP Pro Line 21 or 900XP).

General Lubrication
Aircraft Registration: Mechanic Inspector
120020 Do any 1600 hour lubrication requirements for Area F2, refer to
chapter 5, Lubrication.

Copyright © Textron Aviation Inc. Page 2 of 2

INSPECTION C5 - 050290
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the Introduction section at the
front of this schedule.
NOTE:
Inspection C5 must be signed off only when accomplished in a phased method and must be completed every 1600
hours.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area F3: Vestibule, passenger cabin and toilet compartment (underfloor).

Access: Floor panels F60, F65, F66A, F66B, F66C, F67, F70, F73, F75, F77, F78C, F84 and F84A removed.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe.
(b) Engine.
(c) Electrical.
050291 (d) Avionic.
NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements
detailed in Para.(6) of the Introduction at the front of this schedule.
Flight Controls
270034 Elevator primary control cables. Check cable tensions are correct (AMM 27-
30-00, 501 in the applicable maintenance manual 750, 800XP, 800XP/850XP
Pro Line 21 or 900XP).
270035 Flap control cables. Check cable tensions are correct (AMM 27-50-02, 501 in
the applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
Fuel
280002 Fuel valve control cables. Check cable tensions are correct (AMM 28-20-83,
501 in the applicable maintenance manual 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP).
Engine Controls
760002 Engine power control cables. Check cable tensions are correct (AMM 76-10-
00, 501 in the applicable maintenance manual 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP).

General Lubrication

Copyright © Textron Aviation Inc. Page 1 of 2

Aircraft Registration: Mechanic Inspector

120021 Do any 1600 hour lubrication requirements for Area F3, refer to chapter 5,
Lubrication.

Copyright © Textron Aviation Inc. Page 2 of 2

INSPECTION C6 - 050300
1. Inspection
List of Effective Pages
Pages 1 thru 4, Issued Jun.13

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection C6 must be signed off only when accomplished in a phased method and must be completed every 1600
hours.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area F3: Vestibule, passenger cabin and toilet compartment (above floor).
Access: DA panel F25, removed.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe.
(b) Engine.
050301
(c) Electrical.
(d) Avionic.
NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements detailed in Para. (6) of the
Introduction at the front of this schedule.
Air Conditioning
210009 Airplanes without the digital pressurization control system Mod.
25G726A/C or Mod. 25G726B/C:
Pressurization control venturi screen .
• Make sure screen is clean.
210010 Transferred to Inspection G.
210011 Transferred to Inspection G.
210026 Airplanes with the digital pressurization control system Mod. 25G726A/C
or Mod. 25G726B/C:
Digital pressurization cabin air filters.
• Replace both of the filter elements (Ref. AMM 21-31-20, 301, 750,
or 900XP).

Copyright © Textron Aviation Inc. Page 1 of 3

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:41:49 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-22-06 (Rev A0)

210027 Airplanes with the digital pressurization control system Mod. 25G726A/C
or Mod. 25G726B/C:
Electropneumatic outflow valve.
• Clean each EOV poppet valve seat (Ref. AMM 21-31-10, 701,
750, or 900XP).

Electrical Power
240010 PE, PS1 and PS2 busbar feeder cables below Panel DA .
• Inspect for discoloration due to overheating.
• Torque tighten the connections (Ref. AMM 24-01-00, 201 in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP).
Ice and Rain Protection.
300005 Airframe de-icing pump suction-filter.
• Replace the filter element (Ref. AMM 30-10-43, 401 in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP).
Doors
520004 Main entry door "not locked" warning microswitches.
• Energize the dc busbars (Ref. AMM 12-24-00, in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
• With the main entry door open, operate the "door not closed"
microswitch.
• Make sure the "ENT DOOR UNLOCKED" annunciator on the
Master Warning System panel remains on.
NOTE:
If the annunciator goes off, then investigate the 'door lock'
microswitch for seizure in the operated position.
• Release the "door not closed" microswitch.
• De-energize the dc busbars.
520007 Entry door:
• Inspect seal for deterioration and damage.
• Check internal handle operating loads (Ref. AMM 52-11-00, 501 in
the applicable maintenance manual 750, 800XP, 800XP/850XP
Pro Line 21 or 900XP).
520010 Main Entry Door - Folding Handrail (if fitted). Inspect:
• 800XP and 800XP/850XP Pro Line 21 airplanes (Ref. MMA 52-
15-00, 601).
• 750 airplanes (Ref. MMA 52-15-00, 601).
• 900XP airplanes (Ref. MMA 52-15-00, 601).
Windows
560004 Windows dry-air system filter (if fitted).
• Inspect the filter element (Ref. AMM 56-00-00, 201 in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP).

General Lubrication

Copyright © Textron Aviation Inc. Page 2 of 3

Aircraft Registration: Mechanic Inspector

120022 Do any 1600 hour lubrication requirements for Area F3, refer to chapter 5,
Lubrication.

Copyright © Textron Aviation Inc. Page 3 of 3

INSPECTION C7 - 050310
1. Inspection C7
List of Effective Pages
Pages 1 thru 4, Issued Jun.12

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection C7 must be signed off only when accomplished in a phased method and must be completed every 1600
hours.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area F4: Rear equipment bay, rear fuselage and APU enclosure.
Access: Tail cone F2 and hydraulic box cover F92 removed.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe.
(b) Engine.
(c) Electrical.
050311 (d) Avionic.
NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements detailed in
Para.(6) of the Introduction at the front of this schedule.
Air Conditioning
210012 Air conditioning ducts (Ref. AMM 21-10-15, 201 in the applicable maintenance
manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
• Inspect for satisfactory condition.
210013 Ram air duct. Inspect, as far as is possible, for cracks in the vicinity of the take-
off duct to the shut-off valve, and around the cut-out for the inward relief door.
210025 PATS APU GTCP36-150W.
APU bleed air system.
• Inspect for air leaks at clamped joints and pipes.
• Inspect load control valve for cracks, dents, deformation or other damage
that may affect the performance of the valve.
• Remove and inspect the check valve. Repair as required.
Electrical Power

Copyright © Textron Aviation Inc. Page 1 of 3

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:41:50 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-22-07 (Rev A0)

240011 Busbar PE, PS1 and PS2 feeder fuses. Do a functional test of the fuses:
For the UAM 100 Busbar Feeder Fuse Functional Test, ref. AMM 24-01-00, 201 -
Electrical Power Maintenance Practices.
• F31 and F32 on panel ZL.
• F13, F14, F23 and F24 on panel GA.

240012 This inspection item was combined with 240011. This item is deleted.
Flight Controls
270036 Elevator primary and elevator trim control cables. Check cable tensions are
correct (Ref. AMM 27-30-00, 501 in the applicable maintenance manual 750,
800XP, 800XP/850XP Pro Line 21 or 900XP).
270037 Rudder primary and rudder trim control cables. Check cable tensions are
correct (Ref. AMM 27-20-00, 501 in the applicable maintenance manual 750,
800XP, 800XP/850XP Pro Line 21 or 900XP).
270038 Elevator autopilot servo control cables. Check cable tensions are correct:
• 750 airplanes (Ref. AMM 22-10-30, 401).
• 800XP airplanes (Ref. AMM 27-30-81, 401).
• 800XP/850XP Pro Line 21 airplanes (Ref. AMM 22-10-30, 401).
• 900XP airplanes (Ref. AMM 22-10-30, 401).
270039 Rudder autopilot servo control cables. Check cable tensions are correct:
• 750 airplanes (Ref. AMM 22-10-20, 401).
• 800XP airplanes (Ref. AMM 27-20-121, 401).
• 800XP/850XP Pro Line 21 airplanes (Ref. AMM 22-10-20, 401).
• 900XP airplanes (Ref. AMM 22-10-20, 401).
Flight Controls Cont.
270040 Elevator autopilot trim-servo control cables. Check cable tensions are
correct (Ref. AMM 27-30-00, 501 in the applicable maintenance manual 750,
800XP, 800XP/850XP Pro Line 21 or 900XP).
Hydraulic Power
290006 Hydraulic tank pressurization system . Drain any accumulation of liquid from
the drain/ground air charge connection.
Navigation
340004 Autopilot servo units, rudder and elevator.
• Inspect, particularly for cable and capstan wear, contamination, cable
spool-off angle and security of the servo unit and mount.
• With the autopilot disengaged operate the control system throughout the
entire range and make sure there is no unusual noise, binding, backlash or
signs of other mechanical irregularities from the servo mount.
340005 Autopilot elevator trim servo unit and mount .
• Inspect, particularly for cable and capstan wear, contamination, cable
spool-off angle and security of the servo unit and mount.
• With the autopilot disengaged operate the control system throughout the
entire range and make sure there is no unusual noise, binding, backlash or
signs of other mechanical irregularities from the servo mount.
Oxygen

Copyright © Textron Aviation Inc. Page 2 of 3

350008 Oxygen cylinders.

• Inspect cylinder mount clamps for security (Ref. AMM 35-10-14, 401, in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21
or 900XP).

General Lubrication
Aircraft Registration: Mechanic Inspector
120023 Do any 1600 hour lubrication requirements for Area F4, refer to chapter 5,
Lubrication.

Copyright © Textron Aviation Inc. Page 3 of 3

INSPECTION C8 - 050320
1. Inspection
List of Effective Pages
Pages 1 and 2, Oct.09

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection C8 must be signed off only when accomplished in a phased method and must be completed every 1600
hours.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area T1: Horizontal and vertical stabilizers, to include the elevators and rudder.
Access: Panels T6L, T7R,T14L, T15R, T16L, T17R, T23R, T24L, T25R and T26L removed.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe.
050321 (b) Electrical.
(c) Avionics.
Flight Controls
270041 Elevator trim cables :
• Inspect the condition of the protective coating (AMM 20-
95-11, Item No. 079) on the cables over a length of 42 ins
(1070 mm) from each trim chain where the cables are
exposed between the horizontal stabilizer and the
elevators.
• Apply protective coating (AMM 27-30-00, page block 301
in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).), if necessary.

General Lubrication
Aircraft Registration: Mechanic Inspector
120024 Do any 1600 hour lubrication requirements for Area T1, refer to
chapter 5, Lubrication.

Copyright © Textron Aviation Inc. Page 1 of 1

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:41:51 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-22-09 (Rev A0)

INSPECTION C9 - 050330
1. Inspection
List of Effective Pages
Pages 1 thru 4, Issued Dec.13

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection C9 must be signed off only when accomplished in a phased method and must be completed every 1600
hours.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area W1 Wing LH.

Access: Panels W107, W139, W141, W406, W413, W417, W422, W425, W437, W503, W508, and W510 removed. Flaps
lowered.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe.
(b) Electrical.
050331 (c) Avionic.
Make sure ALL area inspections are done in accordance with the Inspection Requirements detailed in Para.(6) of
the Introduction at the front of this schedule.
Flight Controls
270002 Flap vane inner . With the flaps lowered, inspect the left outer attachment
bracket for cracking and for security of attachment to the flap leading edge.
270003 Transferred to Inspection B9.
270042 Aileron primary and trim control cables. Check cable tensions are correct
(Ref. AMM 27-10-00, 501 in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
270043 Flap drive shaft universal joints . With grease covers removed, inspect
joints for wear and repack with grease (Ref. AMM 27-50-132, 401 in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
270044 Flap Bevel drive assembly . Check that the backlash between the input and
output shafts, measured at the input coupling flange bolts, does not exceed
0.020 in.
270045 Flap control unit baulk release cable . Check cable tension is correct (Ref.
AMM 27-50-02, 501 in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:41:52 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-22-09 (Rev A0)

270046 Flap/Airbrake baulk bobbin. Make sure bobbin setting is correct (Ref. AMM
27-50-02, 501 in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).

270047 Flap spring drum pulley-lever .

• Disconnect rod from pulley lever (Ref. AMM 27-50-02, 501 in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line
21 or 900XP).
• Check the pull off force required to move the lever off the spring drum
internal stops is 5.35 lb. to 7 lb., measured at the connecting rod
attachment point on the lever.
• Check that the lever returns to contact internal stops at or before 5 lb.
force at the connecting rod attachment.
• Reconnect rod to pulley lever.
270048 Flap Screwjack and reduction gearbox . Check that the backlash on the
screw threads does not exceed 0.020 in (Ref. AMM 27-50-141, 401 in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
270049 Flap synchronising system :
• Check the cable tensions are correct (Ref. AMM 27-50-02, 501 in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line
21 or 900XP).
• With the flaps selected up, disconnect the operating link from one
transmitter gearbox only.
• Pressurize the hydraulic system.
• Whilst restraining the disconnected lever arm, select the flaps down.
• Make sure that the flaps start to move and then the system cuts out.
• Depressurize the hydraulic system and connect the transmitter
operating link.
• Pressurize the hydraulic system and make sure that the flaps operate
correctly.
270050 Airbrake control cables . Check the cable tensions are correct (Ref. AMM
27-61-02, 501 in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
Fuel
280005 Suction pipe strainers . Visually inspect for satisfactory condition.

Fuel Cont.
280006 Water transfer system pipe suction blocks . Visually inspect for
satisfactory condition.
280014 Applicable to Intertechnique fuel pumps only.
Fuel system pumps:
• Part No. 2070C01 Check the brush length (14 mm minimum).
• Part No. 2070C11 Check the brush length (10 mm minimum).

General Lubrication
Aircraft Registration: Mechanic Inspector
120025 Do any 1600 hour lubrication requirements for Area W1. Refer to chapter 5,
Lubrication.

Copyright © Textron Aviation Inc. Page 2 of 2

INSPECTION C10 - 050340

1. Inspection
List of Effective Pages
Pages 1 thru 3, Issued Jun.13

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection C10 must be signed off only when accomplished in a phased method and must be completed every 1600
hours.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area W2: Wing RH.

Access: Panels W207, W239, W306, W313, W317, W322, W325, W337, W502, W507 and W509A removed. Flaps lowered.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe.
(b) Electrical.
050341 (c) Avionic.
NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements detailed in
Para.(6) of the Introduction at the front of this schedule.
Flight Controls
270064 Flap vane inner. With the flaps lowered, inspect the right outer attachment
bracket for cracking and for security of attachment to the flap leading edge.
270065 Transferred to Inspection B10.
270051 Aileron primary and trim control cables. Check cable tensions are
correct (Ref. AMM 27-10-00, 501 in the applicable maintenance manual
750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
270052 Flap drive shaft universal joints . With grease covers removed, inspect
joints for wear and repack with grease (Ref. AMM 27-50-132,401 in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21
or 900XP).
270053 Flap bevel drive assembly. Check that the backlash between the input
and output shafts, measured at the input coupling flange bolts, does not
exceed 0.020 in.

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:41:53 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-22-10 (Rev A0)

270054 Flap screwjack and reduction gearbox. Check that the backlash on the
screw threads does not exceed 0.020in. (Ref. AMM 27-50-141, 401 (in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21
or 900XP).

Flight Controls Cont.

270055 Flap synchronising system:
• Check the cable tensions are correct (Ref. AMM 27-50-02, 501 in
the applicable maintenance manual 750, 800XP, 800XP/850XP
Pro Line 21 or 900XP).
• With the flaps selected up, disconnect the operating link from one
transmitter gearbox only.
• Pressurize the hydraulic system.
• Whilst restraining the disconnected lever arm, select the flaps
down.
• Make sure that the flaps start to move and then the system cuts out.
• Depressurize the hydraulic system and connect the transmitter
operating link.
• Pressurize the hydraulic system and make sure that the flaps
operate correctly.
270056 Airbrake control cables. Check the cable tensions are correct (Ref.
AMM 27-61-02, 501 in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
Fuel
280015 Applicable to Intertechnique fuel pumps only.
Fuel system pumps:
• Part No. 2070C01 Check the brush length (14 mm minimum).
• Part No. 2070C11 Check the brush length (10 mm minimum).
280007 Suction pipe strainers . Visually inspect for satisfactory condition.
280008 Water transfer system pipe suction blocks . Visually inspect for
satisfactory condition.

General Lubrication
Aircraft Registration: Mechanic Inspector
120026 Do any 1600 hour lubrication requirements for Area W2, refer to chapter 5,
Lubrication

Copyright © Textron Aviation Inc. Page 2 of 2

INSPECTION C11 - 050350

1. Inspection
List of Effective Pages
Pages 1 thru 3, Issued Jun.12

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection C11 must be signed off only when accomplished in a phased method and must be completed every 1600
hours.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area M1, M2: Engine installation and pylon, LH and RH

Access: Panels M1L, M2R, M3L, M4R, M9L, M10R, M11L, M12R, M13L, M14R, M15L, M16R removed.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Engines.
(b) Airframe.
050351 (c) Electrical.
NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements detailed
in Para.(6) of the Introduction at the front of this schedule.
Engine - Exhaust
NOTE:
Before doing Thrust Reverser inspections make sure ALL related Service Bulletins have been examined and obey any
related Airworthiness Directive.
NOTE:
Any part showing signs of wear or defect should be replaced or overhauled at the time of the inspection.
780004 Pylon skin panels.
• Remove the panels, inspect the fasteners and attachments.
780005 Door link rods and pivot brackets.
• Detail inspect (Ref. AMM 78-31-10, 601 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:41:54 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-22-11 (Rev A0)

780022 NOTE:
This task is NOT APPLICABLE to Series 750 and 900XP Airplanes.
Door link rods (Part No. 5453003-7 Only)
Do a thickness check, Link rod - corrosion removal limits.
• 800XP airplanes (Ref. AMM 78-31-10, 601).

• 800XP/850XP Pro Line 21 airplanes (Ref. AMM 78-31-10, 601).

Engine - Exhaust Cont.
780023 Bonding Straps - 900XP Airplanes.
NOTE:
The Bonding Straps run from the after-body bolt circle to an
attachment point inside the pylon.
• Check for corrosion, arcing, wear or fretting.
• Make sure the end connections are tight to the mounting
attachment points.

General Lubrication
Aircraft Registration: Mechanic Inspector
120027 Transferred to Out of Phase Inspections Task # 760004, refer to
chapter 5, Lubrication.

Copyright © Textron Aviation Inc. Page 2 of 2

INSPECTION C12 - 050360

1. Inspection
List of Effective Pages
Pages 1 thru 3, Issued Sep.15

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the Introduction section at the
front of this schedule.
NOTE:
Inspection C12 must be signed off only when accomplished in a phased method and must be completed every 1600
hours.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Functional Tests
Aircraft Registration: Mechanic Inspector
Hydraulic Power
290007 Flaps, airbrakes, landing gear, nosewheel steering, nose leg self-
centering. Do a test of the main system with a hydraulic test rig (Ref. AMM 29-
10-00, 501 in the applicable maintenance manual 750, 800XP, 800XP/850XP
Pro Line 21 or 900XP)
290008 Emergency brake system leak rate. Check the rate that the pressure
decreases (leakage rate) in the accumulator (Ref. AMM 29-10-00, 501 in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP)
290009 Transferred to Inspection B12.
290010 Hydraulic reservoir pressurization system. Do a functional test of the non-
return valve (Ref. AMM 29-10-13, 501 in the applicable maintenance manual
750, 800XP, 800XP/850XP Pro Line 21 or 900XP)

Area G: Nose landing gear and bay, left and right main landing gear and bays.
Access: Nose and Main landing gear bay doors open.
Aircraft Registration: Mechanic Inspector
(a) Airframe:
(b) Electrical:
050361 NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements detailed
in Para.(6) of the Introduction at the front of this schedule.
Nose Landing Gear
320017 Nose landing gear retraction spring strut. Check the break-out load (Ref.
AMM 32-20-21, 501 in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:41:55 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-22-12 (Rev A0)

320018 Nosewheel steering system spring strut break-out load.

• Check the break-out load (Ref. 32-50-00 in the 125 Series 800A &
800B, Hawker 750, 800, 800XP, 850XP, 900XP CMM.).
• If the load is excessive, dismantle the spring strut, clean, lubricate and
reassemble (Ref. 32-50-00 in the 125 Series 800A & 800B, Hawker
750, 800, 800XP, 850XP, 900XP CMM.).
Main Landing Gear
320024 Axle/Maxaret/Modulator/Plunger Tube .
• Maxaret and modulator unit. Remove and inspect (Ref. AMM 32-40-
91, 401.in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP) and AMM 32-40-101, 401 in
the applicable maintenance manual 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP).
• While the Maxarets and Modulator units are removed, detail inspect
the internal bores of the axles.
• Inspect the Plunger Tube to Axle Bore for signs of corrosion.
• Reinstall Maxarets and Modulator units (Ref. AMM 32-40-91, 401 in
the applicable maintenance manual 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP) and AMM 32-40-101, 401 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
• Do a function test (Ref. AMM 32-40-101, 501, ADJUSTMENT/TEST
in the applicable maintenance manual 750, 800XP, 800XP/850XP
Pro Line 21 or 900XP).
320035 Main Leg Assembly Retraction Lever .
• Inspect for excessive movement.
• Inspect for signs of corrosion.
320036 Sidestay Assembly Lock Mechanism Link .
• Inspect for signs of wear.

General Lubrication
Aircraft Registration: Mechanic Inspector
120028 Task deleted.

Copyright © Textron Aviation Inc. Page 2 of 2

INSPECTION D - 050370
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Inspection D is the top level inspection which covers the accomplishment of Inspections D1 to D12 inclusive. This must
be completed by every 3200 hours.
NOTE:
Inspection D must only be signed when Inspections D1 to D12 inclusive have been completed. ALL within a single
tolerance window.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

INSPECTION D (Consists of Inspection D1 to D12 inclusive)

Aircraft Registration:
NOTE:
This inspection may only be signed off when ALL of the above inspections have been completed.

Copyright © Textron Aviation Inc. Page 1 of 1

INSPECTION D1 - 050380
1. Inspection
List of Effective Pages
Pages 1 thru 3, Sep.15

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection D1 must be signed off only when accomplished in a phased method and must be completed every 3200
hours.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Functional Tests
Aircraft Registration: Mechanic Inspector
Electrical Power
240003 Frequency wild A.C. system. Do a function test (AMM 24-22-02, 501 in
the applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line
21 or 900XP).
240005 APU generator overheat indication circuit. Function test (AMM 24-36-
03, 501 in the applicable maintenance manual 750, 800XP, 800XP/850XP
Pro Line 21 or 900XP), Turbomach APU installation only).
240013 All circuit breakers. Function test for correct mechanical operation. Do
two manual switching cycles for this test.
240014 Main generator control unit (GCU). Do a function test of the overvoltage
protection circuit (AMM 24-30-07, 501 in the applicable maintenance
manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
240015 APU Generator control unit (GCU). Do a function test of the overvoltage
protection circuit (AMM 24-36-03, 501 in the applicable maintenance
manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
Fuel
280003 LP valves . Do a function test for internal leakage (AMM 28-20-00, 501 in
the applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line
21 or 900XP).
Navigation
340008 Mach trim system. Do a test of the Mach trim system:
• 750 airplanes (AMM 22-20-00, 501).
• 800XP airplanes (AMM 34-24-00, 501).
• 800XP/850XP Pro Line 21 airplanes (AMM 22-20-00, 501).
• 900XP airplanes (AMM 22-20-00, 501).

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:41:56 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-23-01 (Rev A0)

340010 Autotrim command isolation relay and autotrim switching relay:

NOTE:
This task is ONLY applicable to airplanes equipped with an FCC-86
Flight Control Computer.
• Do checks as detailed, Ref. (AMM 27-30-00, 501, in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).(Autotrim command isolation relay and autotrim switching
relay checks).

Navigation Cont.
340011 This task is NOT applicable to Pro Line 21 Equipped airplanes.
Mach trim fail annunciation relays.
• Open the MACH TRIM PWR or MACH TRIM MON circuit breaker.
• Make sure that the MACH TRIM FAIL annunciator comes on.
• Close the MACH TRIM PWR or the MACH TRIM MON circuit
breaker.
• Make sure that the MACH TRIM FAIL annunciator goes off.

Copyright © Textron Aviation Inc. Page 2 of 2

INSPECTION D2 - 050390
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection D2 must be signed off only when accomplished in a phased method and must be completed every 3200
hours.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Functional Tests
Aircraft Registration: Mechanic Inspector
Oxygen
350002 Automatic shut-off valve. Do a functional test (AMM 35-10-141, 201 in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).

Copyright © Textron Aviation Inc. Page 1 of 1

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:41:57 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-23-03 (Rev A0)

INSPECTION D3 - 050400
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection D3 must be signed off only when accomplished in a phased method and must be completed every 3200
hours.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area F1: External fuselage, nose cone, tail cone, ventral fuel tanks and wing-to- fuselage fairings Access: As
necessary.
Aircraft Registration: Mechanic Inspector
Electrical Power
240016 Electrical cable pressure bungs (in the forward
pressure bulkhead). Inspect for correct location in their
housings (AMM 24-01-00, 201 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP).

General Lubrication
Aircraft Registration: Mechanic Inspector
120029 Task deleted.

Copyright © Textron Aviation Inc. Page 1 of 1

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:41:58 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-23-04 (Rev A0)

INSPECTION D4 - 050410
1. Inspection
List of Effective Pages
Pages 1 thru 3, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the Introduction section at the
front of this schedule.
NOTE:
Inspection D4 must be signed off only when accomplished in a phased method and must be completed every 3200
hours.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area F2: Flight compartment. Access: Side console panels F52 and F53 removed. Side trim panels F9 and F10
removed.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe.
(b) Electrical.
(c) Avionic.
050411 (d) Engine.
NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements detailed
in Para.(6) of the Time Limits/Maintenance Checks at the front of this schedule.
Electrical Power
240026 Electrical cable pressure bungs (in the forward pressure bulkhead). Inspect
for correct location in their housings (AMM 24-01-00, 201 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
Equipment/Furnishings
250008 Crew Seats.
• Remove the crew seats (Ref. AMM 25-10-14, 401 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
• Do a detailed check (Ref. CMM 25-11-24, 501 (Check 2)) or (Ref. CMM 25-
11-67, 501 (Check 2)).
• Install the crew seats (Ref. AMM 25-10-14, 401 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
Flight Controls

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:41:59 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-23-04 (Rev A0)

270057 Flap control forward spring strut. Check break-out load with one end
disconnected and using a spring balance is 21.5 to 24.5 lb. (AMM 27-50-02, 501 in
the applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).

270058 Flap control input-circuit. Do a static friction check (AMM 27-50-02, 501 in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
Engine Exhaust
780006 Thrust reverser lever baulk mechanism.
• Deploy each thrust reverser in turn.
• Make sure that the baulk release lever of the reverser system which is not
deployed stays down and does not show any tendency to lift when the
solenoid of the deployed system is energized.
• Return both thrust reverser to the stowed position.

General Lubrication
Aircraft Registration: Mechanic Inspector
120030 Do any 3200 hour lubrication requirements for Area F2, refer to Chapter
5,LUBRICATION.

Copyright © Textron Aviation Inc. Page 2 of 2

INSPECTION D5 - 050420
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection D5 must be signed off only when accomplished in a phased method and must be completed every 3200
hours.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area F3: Vestibule, passenger cabin and toilet compartment (underfloor).

Aircraft Registration: Mechanic Inspector
Electrical Power
240025 Electrical cable pressure bungs (in the fuselage keel at the front
spar). Inspect for correct location in their housings (AMM 24-01-00, 201
in the applicable maintenance manual 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP).

General Lubrication
Aircraft Registration: Mechanic Inspector
120031 Task deleted.

Copyright © Textron Aviation Inc. Page 1 of 1

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:00 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-23-06 (Rev A0)

INSPECTION D6 - 050430
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Dec.13

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection D6 must be signed off only when accomplished in a phased method and must be completed every 3200
hours.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area F3: Vestibule, passenger cabin and toilet compartment (above floor).Access: As visible.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe
050431 (b) Electrical
(c) Avionic
NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements detailed in Para.(6) of the
Introductionat the front of this schedule.
Air Conditioning
210014 Transferred to Inspection G.
210028 Airplanes with the digital pressurization control system Mod. 25G726A/C
or Mod. 25G726B/C.
Electropneumatic outflow valve (EOV) pressure limiter .
• Do the pressure limiter test (Ref. AMM 21-31-00, 501, in the
applicable maintenance manual 750 or 900XP).
Electrical Power
240006 D.C. busbar protection/voltage sensing unit.
• Check the trip voltage datums (Ref. AMM 24-30-142, 501, in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP).
Ice and Rain Protection.
300005 Transferred to Inspection C6.

General Lubrication
Aircraft Registration: Mechanic Inspector

Copyright © Textron Aviation Inc. Page 1 of 2

120032 Task deleted.

Copyright © Textron Aviation Inc. Page 2 of 2

INSPECTION D7 - 050440
1. Inspection
List of Effective Pages
Pages 1 thru 3, Issued Jun.13

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection D7 must be signed off only when accomplished in a phased method and must be completed every 3200
hours.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area F4: Rear equipment bay and rear fuselage. Access: Hydraulic box cover and pipe covers F88, F89, F90 and F91
removed.
Aircraft Registration: Mechanic Inspector
(a) Airframe.
(b) Electrical.

050441 (c) Avionic.

NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements detailed
in Para.(6) of the Introduction at the front of this schedule.
Air Conditioning
210015 Silencer duct and soundproofing (Ref. AMM 21-10-15, 201 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
• Inspect the silencer duct internally for deterioration of the soundproofing
material and of the perforated inner retaining duct.
• Inspect for internal and external corrosion.
210016 System overheat temperature switch. Do a bench check (Ref. AMM 21-60-85 in
the applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
210017 Baggage pannier heating system inlet and outlet valve (if fitted) OR External
baggage unit (EBU) inlet valve (750 airplanes ONLY).
• Make sure of the correct operation under normal and "smoke detected"
conditions (Ref. AMM 21-10-205).
NOTE:
This test is only applicable to airplanes with a baggage pannier in place of
the ventral fuel tank OR 750 airplanes with external baggage unit.
210019 Cabin supply non-return valve. Inspect, paying particular attention to the security
of the carrier arm/butterfly flap rivets (Ref. AMM 21-10-107, 201 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).

Copyright © Textron Aviation Inc. Page 1 of 2

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:01 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-23-07 (Rev A0)

210021 APU supply, auxiliary supply, ram air supply and main engine supply.
Check/non-return valves:
• Remove and inspect.
• Make sure that the axial and radial play in the flappers is not excessive
(0.025 in. maximum for AiResearch valves).
Electrical Power
240007 Ground power overvoltage sensor (if fitted). Bench check the trip voltage
datum (Ref. AMM 24-30-146, 401 in the applicable maintenance manual 750,
800XP, 800XP/850XP Pro Line 21 or 900XP).
Electrical Power Cont.
240008 Task deleted.
240018 Electrical cable pressure bungs (in the rear pressure-bulkhead). Inspect for
correct location in their housings (Ref. AMM 24-01-00, 201 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
240027 Main batteries
Rebling Plastics "Quick Disconnect" battery connectors, P/N's 7007, 7013, 7016
and 7017 (if fitted):
• 750 airplanes, Check (Ref. AMM 24-30-151, 401).
• 800XP airplanes, Check (Ref. AMM 24-30-104, 401) or 24-30-151, 401).
• 800XP/850XP Pro Line 21 airplanes, Check (Ref. AMM 24-30-151, 401).
• 900XP airplanes, Check (Ref. AMM 24-30-151, 401).
Fuel
280004 APU fuel inlet filter (if fitted) . Inspect, clean or replace the fuel filter element:
• 800XP airplanes (Ref. AMM 28-20-09).
Hydraulic Power
290011 Full-flow relief valve. Clean filter element (Ref. AMM 29-10-71, 201 in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
290012 High temperature warning system. Do a test of the main hydraulic reservoir high
temperature warning system (Ref. AMM 29-30-00 in the applicable maintenance
manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).

General Lubrication
Aircraft Registration: Mechanic Inspector
120033 Task deleted.

Copyright © Textron Aviation Inc. Page 2 of 2

INSPECTION D8 - 050450
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection D8 must be signed off only when accomplished in a phased method and must be completed every 3200
hours.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area T1 : Horizontal and vertical stabilizers, to include elevators and rudder Access: As necessary.
Aircraft Registration: Mechanic Inspector
NOTE:
No inspections in this area at this time.

General Lubrication
Aircraft Registration: Mechanic Inspector
120034 Task deleted.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:02 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-23-09 (Rev A0)

INSPECTION D9 - 050460
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection D9 must be signed off only when accomplished in a phased method and must be completed every 3200
hours.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area W1 : Wing LH.Access: As necessary.

Aircraft Registration: Mechanic Inspector
NOTE:
No inspections in this area at this time.

General Lubrication
Aircraft Registration: Mechanic Inspector
120035 Task deleted.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:03 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-23-10 (Rev A0)

INSPECTION D10 - 050470

1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Sep.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection D10 must be signed off only when accomplished in a phased method and must be completed every 3200
hours.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area W2 : Wing RH.Access: As necessary.

Aircraft Registration: Mechanic Inspector
Flight Controls
270060 Filter, auxiliary hydraulic system supply to flap
control unit. Replace the filter element (Ref. AMM 29-
20-00, 001 in the applicable maintenance manual 750,
800XP, 800XP/850XP Pro Line 21 or 900XP).
NOTE:
The AMM reference is for component location ONLY.

General Lubrication
Aircraft Registration: Mechanic Inspector
120036 Task deleted.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:04 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-23-11 (Rev A0)

INSPECTION D11 - 050480

1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection D11 must be signed off only when accomplished in a phased method and must be completed every 3200
hours.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area M1, M2: Engine installation and pylon, LH and RH. Access: As necessary.
Aircraft Registration: Mechanic Inspector
NOTE:
No Airframe/electrical inspections in these areas required at this time.
NOTE:
For details of Honeywell engine inspections refer to the latest revision of the Honeywell Light Maintenance Manual
(LMM).

General Lubrication
Aircraft Registration: Mechanic Inspector
120037 Task deleted.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:05 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-23-12 (Rev A0)

INSPECTION D12 - 050490

1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jun.13

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection D12 must be signed off only when accomplished in a phased method and must be completed every 3200
hours.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area G: Nose landing gear and bay, left and right main landing gear and bays. Access: Nose and Main landing gear bay
doors open. Wing-to-fuselage fairing F124 and F224 removed.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe
(b) Electrical
050491 NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements detailed
in Para.(6) of the Introduction at the front of this schedule.
Nose Landing Gear bay
320019 Steering system filter element. Remove, inspect and clean filter element (Ref. AMM
32-30-22, 201 in the applicable maintenance manual 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP).
Main Landing Gear bays
320020 Filters, hydraulic supply (4 off). Clean the filter elements (Ref. AMM 32-30-22, 201 in
the applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
320021 Restrictor valves. Clean the micro filters in the pipe connections (Ref. AMM 32-30-01
in the applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).

General Lubrication
Aircraft Registration: Mechanic Inspector
120038 Task deleted.

INSPECTION E - 050500
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Inspection E is the top level inspection which covers the accomplishment of Inspections E1 to E12 inclusive. This must
be completed by every 12 months.
NOTE:
Inspection E must only be signed when Inspections E1 to E12 inclusive have been completed. ALL within a single
tolerance window.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

INSPECTION E (Consists of Inspection E1 to E12 inclusive)

Aircraft Registration:
NOTE:
This inspection may only be signed off when ALL of the above inspections have been completed.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:06 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-24-01 (Rev A0)

INSPECTION E1 - 050510
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jun.12

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection E1 must be signed off only when accomplished in a phased method and must be completed every 12
months.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Functional Tests
Aircraft Registration: Mechanic Inspector
Parking and mooring
100001 Task deleted.
Bonding Checks
200001 Transferred to Inspection B1.
200002 Transferred to Inspection B1.
Electrical Power
240009 Transferred to Inspection B1.
Fire Protection
260001 Airplanes with Fire Extinguisher Pressure Gauges ONLY.
Fire extinguishers, main engines.
• Check the pressure gauge. Make sure the reading is correct, refer to the
pressure/temperature chart.
• Do a functional test (Ref. AMM 26-20-00, 501 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
NOTE:
For airplanes without Fire Extinguisher Pressure gauges refer to
Inspection E7 task 260005.
260002 Transferred to Inspection B1.
Instruments

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:07 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-24-01 (Rev A0)

310001 Flight data recorder (if fitted). Check for correct playback operation (data
dump) and for quality of the recording.
NOTE:
Do the check at this inspection or at a time agreed necessary by the
local airworthiness authority.
NOTE:
For FDR systems not installed under the original Airplane Type
Certificate, reference the applicable Maintenance Manual Addenda for
systems installed by Supplemental Type Certificate (STC).

INSPECTION E2 - 050520
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Mar.16

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection E2 must be signed off only when accomplished in a phased method and must be completed every 12
months.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Functional Tests
Aircraft Registration: Mechanic Inspector
Oxygen
350003 Task deleted.
350004 Passenger oxygen system.
• Test automatic operation of baromatic valve (Ref. AMM 35-06-00,
501 in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
• Test for flow from each mask by reference to operation of the
visual indicator (if fitted) when mask is pulled down to the 'full hang'
position:
750 airplanes (Ref. MMA 35-06-00, 201).
800XP and 800XP/850XP Pro Line 21 airplanes (Ref. MMA 35-
06-00, 201).
900XP airplanes (Ref. MMA 35-06-00, 201).
• Inspect drop-out mask units when deployed during system test:
750 airplanes (Ref. MMA 35-20-05, 301).
800XP and 800XP/850XP Pro Line 21 airplanes (Ref. MMA 35-
20-05, 301).
900XP airplanes (Ref. MMA 35-20-05, 301).
NOTE:
If the passenger masks PN. 289-601* do not meet the
requirements of the annual inspection refer to the vendor
CMM 35-22-26 for Visual, Overhaul and Repair procedures.
• Stow drop-out mask units:
750 airplanes (Ref. MMA 35-20-05, 301).
800XP and 800XP/850XP Pro Line 21 airplanes (Ref. MMA 35-
20-05, 301).
900XP airplanes (Ref. MMA 35-20-05, 301).

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:08 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-24-02 (Rev A0)

350005 Baromatic control valve.

• With passenger supply isolation valve closed, exercise control
valve mechanism by operating the emergency/reset knob several
times.
• Leave the knob at the reset position.

INSPECTION E3 - 050530
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection E3 must be signed off only when accomplished in a phased method and must be completed every 12
months.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area F1: External fuselage, nose cone, tail cone, wing-to-fuselage fairings and nose landing gear bay. Access: As
visible.
Aircraft Registration: Mechanic Inspector
Windows
560005 Transferred to Inspection B3.

General Lubrication
Aircraft Registration: Total Airframe Hours. Mechanic Inspector
120039 Task deleted.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:09 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-24-04 (Rev A0)

INSPECTION E4 - 050540
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Dec.13

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection E4 must be signed off only when accomplished in a phased method and must be completed every 12
months.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area F 2: Flight compartment.Access: As visible.

Aircraft Registration: Mechanic Inspector
Equipment and Furnishings
250004 Task deleted.
Fire Protection
260003 Portable fire extinguisher:
• Check for correct weight or if gauge is fitted, make sure the needle is
in the green sector.
• Inspect and look for signs of leaks or discharge.
Landing Gear
320022 Transferred to Inspection B4.
Oxygen
350006 Crew masks, smoke set mask (if installed) and hoses .
• Inspect.
350007 Portable breathing equipment:
• Inspect:
800XP airplanes (Ref. AMM 35-35-10).
OR
750, 800XP, 800XP/850XP Proline 21 and 900XP (Ref. AMM 35-
35-15, 601 in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
• Check the expiry dates.
Windows
560006 Transferred to Inspection B4.

General Lubrication
Aircraft Registration: Mechanic Inspector

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:10 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-24-04 (Rev A0)

120040 Task deleted.

INSPECTION E5 - 050550
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Aug.12

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection E5 must be signed off only when accomplished in a phased method and must be completed every 12
months.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area F 3: Vestibule, passenger cabin and toilet compartment (under floor).

Access: As necessary.
Aircraft Registration: Mechanic Inspector
NOTE:
No underfloor inspections required at this time.
240029 Task moved to Inspection E6.

General Lubrication
Aircraft Registration: Total Airframe Hours. Mechanic Inspector
120041 Task deleted.

INSPECTION E6 - 050560
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Aug.12

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection E6 must be signed off only when accomplished in a phased method and must be completed every 12
months.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area F 3: Vestibule, passenger cabin and toilet compartment (above floor).Access: As visible.
Aircraft Registration: Mechanic Inspector
Electrical Power
240029 Do a visual inspection for discoloration and signs of heat distress (Ref.
AMM 24-01-00, 201 in the applicable maintenance manual 750,
800XP, 800XP/850XP Pro Line 21 or 900XP). Inspect DA - Panel for
correct mounting of components.
Equipment and Furnishings
250005 Emergency packs (if fitted). Inspect contents for condition and make
sure expiry dates are valid.
250006 First aid kits. Make sure expiry date is valid and make sure seal is
intact.
Fire Protection
260004 Portable fire extinguisher (if fitted):
• Check for correct weight or if gauge is fitted, make sure the
needle is in the green sector.
• Inspect and look for signs of leaks or discharge.
Doors and Hatches
520005 Transferred to Inspection B6.
520006 Transferred to Inspection B6.
520007 Transferred to Inspection C6.

General Lubrication
Aircraft Registration: Mechanic Inspector
120042 Task deleted.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:11 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-24-07 (Rev A0)

INSPECTION E7 - 050570
1. Inspection
List of Effective Pages
Pages 1 thru 3, Issued Jun.13

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection E7 must be signed off only when accomplished in a phased method and must be completed every 12
months.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area F4: Rear equipment bay, rear fuselage and APU enclosure. Access: As visible.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Engines.
(b) Airframe.
050571 (c) Electrical.
NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements detailed in
Para.(6) of the Time Limits/Maintenance Checks at the front of this schedule.
Air Conditioning
210025 Transferred to Inspection C7.
Electrical Power
240028 Panel GG and Terminal block M (transferred to Out Of Phase
Inspections).
Fire Protection

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:12 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-24-07 (Rev A0)

260005 For airplanes without Fire Extinguisher Pressure Gauges ONLY.

Fire extinguishers, main engines:
• Remove (Ref. AMM 26-20-12, 201 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
• Inspect.
• Check weight (Ref. AMM 26-20-12, 201 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
• Install (Ref. AMM 26-20-12, 201 in the applicable maintenance
manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
• Do a functional test (Ref. AMM 26-20-00, 501 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
NOTE:
For airplanes with Fire Extinguisher Pressure Gauges refer to
Inspection E1, task 260001.
260006 Requirement deleted. Covered by Inspection E1 task # 260001.
Fire Protection Cont.
260007 Fire extinguisher, APU (Solar T-40 (Turbomach ONLY)):
• Inspect.
• Check pressure gauge (Ref. AMM 26-20-54).
• Check Hydrostatic and Cartridge due dates.
• Do a functional test (Ref. AMM 26-20-00).
260010 PATS APU GTCP36-150W.
APU fire extinguisher.
• Inspect.
• Check pressure gauge (Meggitt CMM 26-20-02).
• Check Hydrostatic and Cartridge due dates.
• Do a functional test (Ref. AMM 49-61-20, 501 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
260011 External Baggage Unit Fire Extinguisher.
• Inspect.
• Check Pressure gauge.
• Check cartridge expiry date.
• Do a functional test (Ref. AMM 26-20-60, 201).
NOTE:
This task is ONLY applicable to 750 airplanes.
Flight Controls
270059 Control cable pressure seals at rear pressure bulkhead. Inspect for
wear.
Oxygen
350008 Transferred to Inspection C7.

General Lubrication
Aircraft Registration: Mechanic Inspector
120043 Task deleted.

INSPECTION E8 - 050580
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection E8 must be signed off only when accomplished in a phased method and must be completed every 12
months.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area T1: Horizontal and vertical stabilizers, to include the elevators and rudder. Access: As necessary.
Aircraft Registration: Mechanic Inspector
NOTE:
No inspections in Area T1 required at this time.

General Lubrication
Aircraft Registration: Total Airframe Hours. Mechanic Inspector
120044 Task deleted.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:13 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-24-09 (Rev A0)

INSPECTION E9 - 050590
1. Inspection
List of Effective Pages
Page 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection E9 must be signed off only when accomplished in a phased method and must be completed every 12
months.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area W1 : Wing LH.Access: As necessary.

Aircraft Registration: Mechanic Inspector
NOTE:
No inspections in Area W1 required at this time.

General Lubrication
Aircraft Registration: Mechanic Inspector
120045 Task deleted.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:14 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-24-10 (Rev A0)

INSPECTION E10 - 050600

1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection E10 must be signed off only when accomplished in a phased method and must be completed every 12
months.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area W2 : Wing RH.

Access: As necessary.
Aircraft Registration: Mechanic Inspector
NOTE:
No inspections in Area W2 required at this time.
General Lubrication
Aircraft Registration: Mechanic Inspector
120046 Task deleted.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:15 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-24-11 (Rev A0)

INSPECTION E11 - 050610

1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection E11 must be signed off only when accomplished in a phased method and must be completed every 12
months.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area M1, M2: Engine installation and pylon, LH and RH.

Access: As necessary.
Aircraft Registration: Mechanic Inspector
NOTE:
No Airframe/electrical inspections in these areas required at this time.
NOTE:
For details of Honeywell engine inspections refer to the latest revision of the Honeywell Light Maintenance Manual
(LMM).
General Lubrication
Aircraft Registration: Mechanic Inspector
120047 Task deleted.

INSPECTION E12 - 050620

1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection E12 must be signed off only when accomplished in a phased method and must be completed every 12
months.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area G: Nose landing gear and bay, left and right main landing gear and bays.
Access: As necessary.
Aircraft Registration: Mechanic Inspector
Main Landing Gear
320034 Transferred to Inspection B12.

General Lubrication
Aircraft Registration: Mechanic Inspector
120048 Task deleted.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:16 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-25-00 (Rev A0)

INSPECTION F - 050630
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Inspection F is the top level inspection which covers the accomplishment of Inspections F1 to F12 inclusive. This must
be completed by every 24 months.
NOTE:
Inspection F must only be signed when Inspections F1 to F12 inclusive have been completed. ALL within a single
tolerance window.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

INSPECTION F (Consists of Inspection F1 to F12 inclusive)

Aircraft Registration:
NOTE:
This inspection may only be signed off when ALL of the above inspections have been completed.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:17 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-25-01 (Rev A0)

INSPECTION F1 - 050640
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection F1 must be signed off only when accomplished in a phased method and must be completed every 24
months.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Functional Tests
Aircraft Registration: Mechanic Inspector
Communications
230001 Task deleted.
Navigation
340006 Transferred to OOP
Inspections.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:18 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-25-02 (Rev A0)

INSPECTION F2 - 050650
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection F2 must be signed off only when accomplished in a phased method and must be completed every 24
months.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Functional Tests
Aircraft Registration: Mechanic Inspector
NOTE:
No functional tests in this inspection at this time.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:19 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-25-03 (Rev A0)

INSPECTION F3 - 050660
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Sep.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection F3 must be signed off only when accomplished in a phased method and must be completed every 24
months.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area F1: External fuselage, nose cone, tail cone, ventral fuel tanks and wing-to- fuselage fairings.
Access: F121, F221, F122, F222, F123, F223 and as visible.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe.
(b) Electrical.
050661 (c) Avionic.
NOTE:
Make sure ALL area inspections are done in accordance with the Inspection
Requirements detailed in Para.(6) of the Introduction at the front of this schedule.
Ice and Rain Protection
300006 Transferred to Navigation, Task
340014
Navigation
340002 Transferred to OOP
Inspections.
340014 Task deleted.

General Lubrication
Aircraft Registration: Mechanic Inspector
120049 Do any 24 month lubrication
requirements for Area F1, Refer
to chapter 5, Lubrication.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:20 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-25-04 (Rev A0)

INSPECTION F4 - 050670
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection F4 must be signed off only when accomplished in a phased method and must be completed every 24
months.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area F2: Flight compartment

Access: Instrument panels F6 and F8 and roof panel F5 lowered. Floor panels F41, F42, F43, F44,F45 and F47 removed.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe.
(b) Electrical.
050671 (c) Avionic.
NOTE:
Make sure ALL area inspections are done in accordance with the Inspection
Requirements detailed in Para.(6) of the Introduction at the front of this schedule.
Landing Gear
320023 Transferred to Inspection C4.
Navigation
340007 Transferred to OOP
Inspections.

General Lubrication
Aircraft Registration: Mechanic Inspector
120050 Do any 24 month lubrication requirements for Area
F2, Refer to chapter 5, Lubrication

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:21 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-25-05 (Rev A0)

INSPECTION F5 - 050680
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection F5 must be signed off only when accomplished in a phased method and must be completed every 24
months.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area F3: Vestibule, passenger cabin and toilet compartment (under floor).
Aircraft Registration: Mechanic Inspector
NOTE:
No inspections required in this area at this time.

General Lubrication
Aircraft Registration: Mechanic Inspector
120051 Task deleted.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:22 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-25-06 (Rev A0)

INSPECTION F6 - 050690
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Sep.16

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection F6 must be signed off only when accomplished in a phased method and must be completed every 24
months.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area F3: Vestibule, passenger cabin and toilet compartment.

Access: DA panels F22, F23, F24 and F25 removed. Front and rear radio compartments access panels removed. Radio
junction cover removed. Duct panel F29 removed.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe.
(b) Electrical.
050691 (c) Avionic.
NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements detailed
in Para.(6) of the Introduction at the front of this schedule.
Electrical Power
240010 Transferred to Inspection C6.
Windows
560007 Screen heat circuit breakers.
• Do a visual inspection for heat distress, discoloration and
deformation (Ref. AMM 30-41-00, 501 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP).

General Lubrication
Aircraft Registration: Mechanic Inspector
120052 Task deleted.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:23 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-25-07 (Rev A0)

INSPECTION F7 - 050700
1. Inspection
List of Effective Pages
Pages 1 and 2 Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection F7 must be signed off only when accomplished in a phased method and must be completed every 24
months.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area F4: Rear equipment bay and rear fuselage.

Access: As visible with rear equipment bay door open.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe.
(b ) Electrical.
050701
(c) Avionic.
(d) Engine.
NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements detailed in Para.(6) of the
Introduction at the front of this schedule.
Electrical Power
240011 Transferred to Inspection C7.
240012 Transferred to Inspection C7.

General Lubrication
Aircraft Registration: Mechanic Inspector
120053 Task deleted.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:24 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-25-08 (Rev A0)

INSPECTION F8 - 050710
1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Sep.15

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection F8 must be signed off only when accomplished in a phased method and must be completed every 24
months.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area T1: Horizontal and vertical stabilizers, to include the elevators and rudder.
Access: T13, T25R, T26L and T45 removed.
Aircraft Registration: Mechanic Inspector
550008 Horizontal stabilizer to vertical stabilizer rear attachment
fitting.
• Inspect for signs of corrosion, paying special
attention to the condition of the outboard flanges
and webs.
NOTE:
For corrosion limits refer to Textron Aviation Inc.
General Lubrication
Aircraft Registration: Mechanic Inspector
120054 Task deleted.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:25 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-25-09 (Rev A0)

INSPECTION F9 - 050720
1. Inspection
List of Effective Pages
Pages 1 thru 3, Issued Sep.16

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection F9 must be signed off only when accomplished in a phased method and must be completed every 24
months.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area W1: Wing LH.

Access: Panels W406, W411 and W413 removed.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe
(b) Electrical
050721 (c) Avionic
NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements detailed in
Para.(6) of the Introduction at the front of this schedule.
Fuel
280005 Transferred to Inspection C9.
280006 Transferred to Inspection C9.
Wings
570003 The internal structure of the wing in the area of Ribs 0 to 4 .
• Detail inspect.
• Look for signs microbiological contamination and corrosion.
NOTE:
If corrosion or microbiological contamination is found:
• Progressively extend the detail inspection, by visual
means or X-Ray technique, forward of the centre spar and
outboard of Rib 4 until a clean bay rib is found.
• Remove the ventral fuel tank (if fitted) and detail inspect
internally.
• Do the shock preventative procedure (Ref. AMM 28-10-00,
page block 701 in the applicable maintenance manual 750,
800XP, 800XP/850XP Pro Line 21 or 900XP).

570004 Applicable to Mod. 259071A airplanes only.

Flap skin protection panels (if fitted). Remove panels and inspect
the flap skin for corrosion and deterioration of the protective treatment.
NOTE:
Mod. 259071A introduces protective skins on the flap inboard
underside for rough runway protection.
Wings Cont.
570030 Applicable to Airplanes with BC Winglets
Rib 16 and spar fitting where the winglet is attached to the wing.
Access: Remove winglet (Ref. SRM 57-30-12, 201)
NOTE:
It is recommended to re-apply the corrosion preventive
treatment every 2 years.
Refer to 57-10-19, 201 and inspect for signs of corrosion. If corrosion
is found, and beyond limits, contact Repair Design Office or replace the
rib.

General Lubrication
Aircraft Registration: Mechanic Inspector
120055 Task deleted.

INSPECTION F10 - 050730

1. Inspection
List of Effective Pages
Pages 1 thru 3, Issued Sep.16

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection F10 must be signed off only when accomplished in a phased method and must be completed every 24
months.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area W2: Wing RH.

Access: Panels W306, W311 and W313 removed.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe.
(b) Electrical.
050731 (c) Avionic.
NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements detailed in
Para.(6) of the Introduction at the front of this schedule.
Fuel
280007 Transferred to Inspection C10.
280008 Transferred to Inspection C10.
Wings
570005 The internal structure of the wing in the area of Ribs 0 to 4 .
• Detail inspect.
• Look for signs microbiological contamination and corrosion.
NOTE:
If corrosion or microbiological contamination is found:
• Progressively extend the detail inspection, by visual means
or X-Ray technique, forward of the center spar and outboard
of Rib 4 until a clean bay rib is found.
• Remove the ventral fuel tank (if fitted) and detail inspect
internally.
• Do the shock preventative procedure (Ref. AMM 28-10-00,
page block 701 in the applicable maintenance manual 750,
800XP, 800XP/850XP Pro Line 21 or 900XP).

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:26 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-25-10 (Rev A0)

570006 Applicable to Mod. 259071A airplanes only.

Flap skin protection panels (if fitted) . Remove panels and inspect the
flap skin for corrosion and deterioration of the protective treatment.
NOTE:
Mod. 259071A introduces protective skins on the flap inboard
underside for rough runway protection.
Wings Cont.
570031 Applicable to Airplanes with BC Winglets
Rib 16 and spar fitting where the winglet is attached to the wing.
Access: Remove winglet (Ref. SRM 57-30-12, 201).
NOTE:
It is recommended to re-apply the corrosion preventive treatment
every 2 years.
Refer to SRM 57-10-19, 201 and inspect for signs of corrosion. If
corrosion is found, and beyond limits,contact Repair Design Office or
replace the rib.

General Lubrication
Aircraft Registration: Mechanic Inspector
120056 Task deleted.

INSPECTION F11 - 050740

1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection F11 must be signed off only when accomplished in a phased method and must be completed every 24
months.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area M1, M2: Engine installation and pylon, LH and RH.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:27 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-25-12 (Rev A0)

INSPECTION F12 - 050750

1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
NOTE:
Inspection F12 must be signed off only when accomplished in a phased method and must be completed every 24
months.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Area G: Nose landing gear and bay, left and right main landing gear and bays.
Access: Nose and main landing gear doors open.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe:
(b) Electrical:
050751 (c) Avionic:
NOTE:
Make sure ALL area inspections are done in accordance with the Inspection
Requirements detailed in Para.(6) of the Introduction at the front of this schedule.
Main Landing Gear
320024 Transferred to Inspection C12.
320035 Transferred to Inspection C12.
320036 Transferred to Inspection C12.
320025 Transferred to Task # 320024.

General Lubrication
Aircraft Registration: Mechanic Inspector
120058 Task deleted.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:28 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-26-00 (Rev A0)

INSPECTION G - 050760
1. Inspection
List of Effective Pages
Pages 1 thru 9, Issued Jun.12

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the Introduction section at the
front of this schedule.
NOTE:
Inspection G must be completed every 48 months.
Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #

Functional Tests
Aircraft Registration: Mechanic Inspector
Bonding Checks
200003 Radio racking, electrical-
bonding. Do a bonding check
with all the equipment fitted
(Ref. AMM 125/H-20, 20-10-
5016).
Air Conditioning
210020 Transferred to Inspection C1.
Electrical Power
240013 Transferred to Inspection D1.
240014 Transferred to Inspection D1.
240015 Transferred to Inspection D1.
Navigation
340008 Transferred to Inspection D1.
340009 Transferred to task 340010.
340010 Transferred to Inspection D1.

General Lubrication
Aircraft Registration: Mechanic Inspector
120059 Task deleted (Transferred to
Lubrication, 1600 Hour).

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:29 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-26-00 (Rev A0)

Area F1: External fuselage, nose cone, tail cone, ventral fuel tanks and wing-to- fuselage fairings
Access: Panels F3, F125, F155, F162, F163, F160L, F161R, and F225 removed.
NOTE:
It is not necessary to remove panels F160L, F161R, until the second 48 month inspection (96 months). Remove them at
every 48 month inspection from that time onwards.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe.
(b) Electrical.
(c) Avionics.
050761
NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements detailed in
Para.(6) of the Introduction at the front of this schedule.
Electrical Power
240016 Transferred to Inspection D3.
Landing Gear
320026 Task deleted. Covered by chapter 5, Lubrication
320027 Nose-wheel steering on/off-valve :
• Remove the plunger stop cap.
• Visually inspect the plunger and spring for corrosion, clean and lubricate all
surface areas as required using Grease (Ref. AMM 125/H-20, 20-95-11, Item
034).
• Install the stop cap.
Fuselage
530027 Fuselage Skin :
• Do a visual inspection.

Area F2: Flight compartment.Access: Soundproofing bags on the forward pressure bulkhead removed.
NOTE:
It is not necessary to remove the soundproofing on the forward pressure bulkhead until the second 48 month
inspection (96 months). Remove the soundproofing at every 48 month inspection from that time onwards.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe.
(b) Electrical.
(c) Avionics.
050762 (d) Engine.
NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements detailed in
Para.(6) of the Introduction at the front of this schedule.
Electrical Power
240026 Transferred to Inspection D4.
Flight Controls

270068 Aileron Servomotor assembly SVO-85B (P/N 622-5027-001).

Lubricate and clean as detailed in Collins SVO-85B/C Service Information
Letter SIL 1-01.
Navigation
340011 Transferred to Inspection D1.
Engine Exhaust
780006 Transferred to Inspection D4.

Area F3: Vestibule, passenger cabin and toilet compartment.

Access: Passenger service units lowered. Toilet trim removed. Cable duct floor panels F29 to F39 inclusive removed.
Floor panels F61A, F61B, F64A, F64B, F68A, F68B, F71A, F71B, F72, F74A, F74B, F74C, F76, F78, F82A, F82B, F83 and
F87 removed.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe.
050763 (b) Electrical.
(c) Avionics.
NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements detailed in Para.(6) of the
Introduction at the front of this schedule.
Air Conditioning
210010 Airplanes without the digital pressurization control system Mod. 25G726A/C or
Mod. 25G726B/C:
Pressure regulators .
• Clean the filter screens (Ref. AMM 21-30-55, 201 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
210011 Airplanes without the digital pressurization control system Mod. 25G726A/C or
Mod. 25G726B/C:
Outflow/safety valves .
• Clean the outflow valve poppet valve and seat (Ref. AMM 21-30-25, 701,
in the applicable maintenance manual 750, 800XP, 800XP/850XP Pro
Line 21 or 900XP).
• If required, clean exterior of the outflow valve using a cloth or sponge
soaked in cleaning fluid (Ref. AMM 21-30-25, 701, in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
• Check that the orifice in the cabin air filter connection is free of obstruction.
• Check that the cabin air sense ports are free and clear of any obstruction.
• Functionally test operation of valves (Ref. AMM 21-30-25, 501, in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21
or 900XP).
210014 Airplanes without the digital pressurization control system Mod. 25G726A/C or
Mod. 25G726B/C:
Cabin air filters (pressurization system):
• Inspect.

210018 Altitude switch, cabin depressurization warning.

• Do a functional test (Ref. AMM 21-30-70, 201, in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
NOTE:
Mod. 259747C (SB 21-3136) introduces a second Altitude Warning Switch
(set to 14,000 ft.) to permit operation at high altitude airfields.
Electrical Power
240025 Transferred to Inspection D5.

Area F4: Rear equipment bay and rear fuselage.Access: Hydraulic box cover removed.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe.
(b) Electrical.
(c) Avionics.
050764
NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements detailed
in Para.(6) of the Introduction at the front of this schedule.
Air Conditioning
210019 Transferred to Inspection D7.
210020 Transferred to Inspection C1.
210021 Transferred to Inspection D7.
Electrical Power
240017 Earth stations *16, *17, *18 and *19:
• Inspect. Look for signs of arcing.
• Do an impedance check (Ref. AMM 24-01-00, in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
NOTE:
It is not necessary to do this task until the second 48 month inspection (96
months). Do the task at every 48 month inspection from that time onwards.
240018 Transferred to Inspection D7.
240027 Transferred to Inspection D7.
Flight Controls
270069 Elevator Servomotor assembly SVO-85B (P/N 622-5027-001).
Lubricate and clean as detailed in Collins SVO-85B/C Service Information Letter
SIL 1-01.
Hydraulic Power
290012 Transferred to Inspection D7.

Area T1: Horizontal and vertical stabilizers, to include elevators and rudder.
Access: Panel T12 removed.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe.
(b) Electrical.

050765 (c) Avionics.

NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements detailed in
Para.(6) of the Introduction at the front of this schedule.
Flight Controls
270070 Rudder Servomotor assembly SVO-85B (P/N 622-5027-001).
Lubricate and clean as detailed in Collins SVO-85B/C Service Information
Letter SIL 1-01.
270071 Rudder Trim Jack
• Do an inspection (Ref. AMM 27-20-111, 301, in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
270072 Elevator Trim Jack
• Do an inspection (Ref. AMM 27-30-51, 301, in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).

Area W1, W2: Wings, LH and RH.

Access: Panels W329, W429, W507 and W508 removed.
Aircraft Registration: Mechanic Inspector
Area Inspection
(a) Airframe.
(b) Electrical.
(c) Avionics.
050766
NOTE:
Make sure ALL area inspections are done in accordance with the Inspection Requirements detailed in
Para.(6) of the Introduction at the front of this schedule.
Flight Controls
270060 Transferred to Inspection D10.
Fuel
280016 Low pressure fuel valve support strut. Part No. 25 PF361,25 PF361-
5A (Mod. 25G310A) and 25 PF363.
Do a visual inspection of the low pressure fuel valve support strut,
attachment bolt and drain hole for corrosion.
NOTE:
If corrosion is found replace the affected part.

INSPECTIONS AFTER AN OVERWEIGHT OR HEAVY LANDING

1. Introduction
List of Effective Pages
Pages 1 thru 6, Issued Sep.15

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #
NOTE: If there is more than 5% residual fuel in the ventral tank on landing it is classed as a heavy landing.
The airplane has been designed to withstand a vertical descent velocity of 6 ft./second at the maximum take-off weight and 10
ft./second at the maximum landing weight.
Providing the above values are not exceeded then no inspection should be required, but as it is difficult to accurately determine
vertical descent velocity the following inspections, checks and tests must be done whenever an unusually heavy or overweight landing
has been reported or is suspected.
It is not possible to lay down precise details of the inspection procedure to be adopted after every incident due to the wide variations
in weight, speed, nature and direction of loads that can be encountered. It is therefore recommended that before starting the
inspection the pilot is consulted for information regarding the landing conditions. Ascertain, for example:
1. Whether the landing was straight, drifting, wing low, nose or tail heavy.
2. If any noise indicative of a structural failure was heard.
3. The weight of the airplane and the fuel distribution.
2. Main Landing Gear Bays
A. Inspect:
(1) Wheels and brakes for signs of damage.
(2) Tires for bulges, cuts, impact damage.
(3) Shock absorbers for signs of fluid leakage and damage.
(4) Main leg front and rear attachments for cracks and signs of movement.
(5) Sidestay assemblies for distortion and other damage.
(6) Retraction jack top attachments for cracks, distortion and other damage.
(7) Bay structure, particularly in the vicinity of the landing gear attachments, for distortion and signs of bolt and rivet failures.
(8) Main gear doors and fairing attachments for damage and distortion.
(9) For signs of hydraulic fluid leakage.
B. Check:
(1) Shock absorbers for correct inflation pressures.
3. Nose Landing Gear Bay
A. Inspect:
(1) Wheels for signs of damage.
(2) Tires for bulges, cuts, impact damage.
(3) Nose gear attachment fittings for cracks and signs of movement.
(4) Drag stay and attachments for distortion, cracks and signs of movement.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:30 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-50-01 (Rev A0)

(5) Shock absorber for signs of fluid leakage and damage.

(6) Steering jack and attachments for damage.
(7) Retraction jack attachments for cracks, distortion and other damage.
(8) Nose gear bay structure, particularly in the areas of the landing gear attachments, for distortion and signs of bolt and rivet
failures.
(9) Nose gear doors for distortion, cracks and security.
(10) For signs of hydraulic fluid leakage.
B. Check:
(1) Nose gear shock absorber for correct inflation pressure.
4. Wings
A. Inspect:
(1) Skins generally for distortion, wrinkling or other damage.
(2) Ribs 4 aft of the rear spar for cracks and signs of movement.
(3) Rear spar webs for buckling in the vicinity of Ribs 4 and 5.
(4) Flap screwjacks and attachments, and flap hinges for cracks and signs of movement.
(5) Airbrake hinge attachments, airbrake jacks and attachments for cracks and distortion.
(6) Aileron hinges for cracks.
(7) Ailerons for damage in the vicinity of the hinges and distortion in the vicinity of the balance weights.
(8) For signs of fuel or hydraulic fluid leakage.
5. Fuselage
A. Inspect:
(1) Skinning for distortion, wrinkling or other damage. Pay particular attention to the skin joint areas and the areas around the
entry door, escape hatch, wing fillets and wing-to-fuselage attachments.
(2) For signs of fuel leakage including ventral tank fuel line connections and tank skin joints.
(3) For signs of hydraulic fluid leakage.
(4) Ballast weights (if fitted) for security of attachment.
(5) To be done after a landing with fuel in the ventral tank.
NOTE: If there is more than 5% residual fuel in the ventral tank on landing it is classed as a heavy landing
and is considered to be 'Not Empty'.
Examine the following areas for wrinkling, buckling, distortion, elongated rivet holes or any other damage.
• Stringers: Lower half of the fuselage, from frame 13 (wing forward spar) to frame 23 (ventral tank aft attachment).
• Frames: Frame 16 (wing rear spar attachment) and frame 19 (aft pressure bulkhead).
• Skins: From frame 16 to frame 23 (full fuselage circumference).
• Ventral tank, attachment fittings and associated structure.
6. Rear Equipment Bay
A. Inspect:
(1) Electrical panels for security and signs of movement.
(2) Cold air unit and heat exchanger mountings for damage and security.
(3) APU and mountings for damage and security.
(4) Ducting for signs of movement.
(5) Fire extinguisher bottles for security.
(6) Batteries for security, with no signs of spilt electrolyte.
(7) Inverters for security.
(8) For signs of fluid leakage, particularly from the hydraulic box.
B. Test:

(1) The inverters for correct functioning.

7. Stabilizers
A. Inspect:
(1) Horizontal stabilizer attachments for damage and signs of movement.
(2) Elevators for cracks and distortion in the vicinity of the balance weights.
(3) Elevator and rudder hinges for cracks.
(4) Superstructure for damage and distortion.
8. Engines and Mountings
A. Inspect:
(1) Cowlings and pod fillet fairings for wrinkling and distortion.
(2) Engine mountings and attachments for damage and signs of movement.
(3) For signs of fuel or hydraulic fluid leakage.
9. Systems and Equipment/Furnishings
A. Inspect:
(1) Radar scanner for damage and security.
(2) Radio racks and components for damage and security.
(3) Equipment for correct stowage and security.
(4) Water tanks for security and signs of leakage.
(5) Instruments and panels for damage and security.
(6) Elevator 'G' weight assembly for signs of movement between the torque tube and shear bushes.
(7) The emergency lighting inertia switch (if fitted) and make sure it has not operated.
(8) All flying control cables and check the tensions.
B. Test:
(1) Function test the 3rd channel stall detector unit (applicable to Pre-Mod 25G206A or B only).
(2) The correct functioning of the gyroscopic units.
(3) The correct functioning of the radar scanner and radio equipment.
(4) The correct operation of the navigation and essential lighting services.
(5) The correct functioning of the avionics flight system.
10. Final Items
A. If structural damage is found:
(1) Do the rigging and symmetry checks.
(2) Do a cabin leak rate test.
(3) Do the landing gear retraction tests.
B. Function test:
(1) All the flying control systems.
(2) The engine control system.
(3) The engines by doing engine runs.

INSPECTIONS AFTER A FLIGHT IN HEAVY TURBULENCE

1. Introduction
List of Effective Pages
Pages 1 thru 4, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #
In the event of a reported flight in heavy turbulence the following inspections and checks must be done before the airplane is released
for further flight.
NOTE: Damage may be experienced whenever the values of negative and positive "g" approach -0.5g and 2.5g
respectively. A fatigue meter count of either level will give a reasonable indication of severe turbulence.
2. General
A. Inspect:
(1) All external skinning of the wings, fuselage and stabilizers for wrinkling and distortion.
3. Wings
A. Inspect:
(1) Flap hinges for cracks and evidence of movement, and flaps for damage in the vicinity of the hinges.
(2) Aileron hinges for cracks, and ailerons for damage in the vicinity of the hinges.
(3) Aileron balance arms for distortion and pulled rivets.
(4) For no evidence of fuel leakage.
B. Check:
(1) The clearance between the aileron balance arms and the wing cut-outs.
4. Fuselage
A. Inspect:
(1) Skinning in the vicinity of the skin joints, around the entry door and escape hatch, the wing fillet and the wing-to-fuselage
attachments for distortion, wrinkling and evidence of loose rivets.
(2) The fuselage for damage at the forward left-hand wing to fuselage side load link attachment point.
5. Stabilizers
A. Inspect:
(1) Horizontal stabilizer for damage and evidence of movement.
(2) Elevators and hinges for cracks, and elevator skinning for distortion in the vicinity of the balance weight.
(3) The rudder hinges for cracks, and rudder skinning for distortion.
6. Rear Equipment Bay
A. Inspect:
(1) Electrical panels for security and evidence of movement.
(2) The cold air unit and heat exchanger mountings for damage and security.
(3) The APU and mountings for damage and security.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:31 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-50-02 (Rev A0)

(4) The fire extinguisher bottles for security.

(5) For no evidence of fluid leakage.
7. Engines and Mountings
A. Inspect:
(1) Engine cowlings and pod fillets for wrinkling and distortion.
(2) Engine mountings and attachments for damage and evidence of movement.
(3) For no evidence of fuel or hydraulic fluid leakage.
8. Electrical
A. Inspect:
(1) The batteries for security and evidence of leakage.
(2) The inverters for security.
(3) The emergency lighting inertia switch (if fitted) and make sure it has not operated.
B. Test:
(1) The inverters for correct functioning.
9. Furnishings/Equipment
A. Inspect:
(1) The emergency equipment for security and correct stowage.
10. Flight Controls
A. Make sure:
(1) All the control cable tensions are correct.
B. Test:
(1) The flight control systems for correct operation.
11. Final Items
A. If damage is found:
(1) Do the symmetry and rigging checks.
(2) Do a cabin leak rate test.

INSPECTIONS AFTER A LIGHTNING STRIKE

1. Inspection
List of Effective Pages
Pages 1 thru 3, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #
2. General
In the event of a lightning strike the following inspections, checks and tests must be done before the airplane is released for further
flight.
Lightning strikes usually produce two types of damage, that caused by the actual strike and that caused by the discharge of static
electricity which follows the strike.
A lightning strike usually causes the burning of small circular holes, which may be clustered in one locality or scattered over a large
area. A strike may also be indicated by burnt or discoloured skin, the blistering of Neoprene coverings or the cracking of glassfibre
components. Strike damage usually appears at the fuselage nose, along the top surface of the fuselage and on the wing and
stabilizer leading edges.
Damage due to the static discharge usually appears on the tips of the wings and stabilizers, trailing edges and antennae, and may
be in the form of localized pitting or burning, or damaged or destroyed static dischargers.
3. Fuselage
A. Inspect:
(1) Radome for damage, particularly to the lightning diverter strips and the radome fasteners.
(2) Fuselage skinning for pitting and burning, particularly in the area of the windshields, along the fuselage top and in the area
of the ram air intake.
(3) Pitot heads and structure in the area for signs of damage.
(4) Aerials, masts and dielectric panels for damage.
(5) The nose landing gear doors for distortion and damage.
(6) If the landing gear was extended at the time of the strike, then inspect the lower portion of the landing gear for signs of
static discharge.
4. Wings
A. Inspect:
(1) Wing leading edges and spoilers for pitting and burning.
(2) Wing tips, trailing edges of ailerons and flaps for pitting, burning and signs of static discharge.
(3) Static dischargers for damage or disintegration.
(4) The main landing gear doors for distortion and damage.
(5) If the landing gear was extended at the time of the strike, then inspect the lower portion of the landing gear for signs of
static discharge.
5. Stabilizers
A. Inspect:
(1) Vertical stabilizer for burning, pitting and signs of static discharge.

(2) Horizontal stabilizer for burning, pitting and signs of static discharge.
(3) Rudder for burning, pitting and signs of static discharge.
(4) Elevators for burning, pitting and signs of static discharge.
(5) Bullet and overfin fairings for burning, pitting and signs of static discharge.
(6) If there is any signs of a strike on the overfin fairing, then remove the fairing and inspect the structure revealed for damage.
(7) Static dischargers on vertical and horizontal stabilizers for damage or disintegration.
6. Engines and Mountings
A. Inspect:
(1) Engine pods and structure for signs of burning or pitting.
(2) The power plant in accordance with the Garrett Light Maintenance Manual.
7. Final Items
A. Test:
(1) All radio and radar equipment.
(2) All navigation and essential lighting systems.
(3) All flying control systems.
(4) Compass systems.

INSPECTIONS AFTER MISUSE OF REVERSE THRUST

1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jun.11

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #
2. General
If reverse thrust in excess of idle power has been used at speeds below 50 knots, before any subsequent engine ground running or
further flight do the following inspections.
A. Inspect:
(1) Fan blades for foreign object damage, erosion, nicks, cracks or distortion which may affect balance or blade security.
Rotate the fan rotor assembly to inspect all fan blades.
(2) If the inspection requirements of (1) are not met, repair or replace the damaged fan rotor blades in accordance with the
Honeywell Light Maintenance Manual 72-70-03, 4, Approved Repairs.
(3) If foreign object damage is found on any fan blade, then a borescope inspection of the low pressure compressor first stage
rotor blades must be done in accordance with the Honeywell Light Maintenance Manual 72-30-04, Maintenance Practices.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:32 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-50-05 (Rev A0)

INSPECTIONS AFTER LANDING GEAR VIBRATION

1. INSPECTIONS AFTER LANDING GEAR VIBRATION
List of Effective Pages
Pages 1 thru 6, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #
NOTE: Do ALL items marked with an asterisk (*). If damage, distortion or a failure of any part or component
inspected on an asterisk inspection is found, the full inspection must be done.
NOTE: It is recommended that any major disassembly of the landing gear for crack testing is done at a repair center
with the necessary equipment for overhaul and testing of the assembly.
NOTE: It is necessary that all items are thoroughly cleaned before any inspections for excessive wear, cracks,
damage, distortion or dimensional checks are done.
2. Preparation
A. General
(1) (*) Remove airplane electrical power (AMM Chapter 24, ELECTRICAL POWER).
(2) Display signs in the flight compartment to tell personnel "DO NOT USE ELECTRICAL POWER".
(3) Display signs in the flight compartment to tell personnel "DO NOT USE THE LANDING GEAR"
(4) Open, safety and tag the landing gear circuit breakers (AMM Chapter 24, ELECTRICAL POWER).
(5) Make sure that the landing gear locking pins are installed (AMM Chapter 10, PARKING AND MOORING).
(6) Raise the airplane on jacks (AMM Chapter 07, JACKING AND TRESTLING).
3. Inspection
A. Nose Landing Gear, Drag Stay Assembly and NLG bay
NOTE: Before doing any crack testing using the liquid dye penetrant method, make sure that all the surface
finish and protective coatings are removed from the areas to be tested. After the crack testing is
complete the protective coating and surface finish must be restored (OM Chapter 32).
Check/Inspect:
(1) Inspect nosewheels and tires for damage.
(2) Inspect torque link joints for excessive wear.
(3) Inspect strut for signs of fluid leakage and damage.
(4) Check strut for correct nitrogen and fluid servicing (AMM Chapter 12, LANDING GEAR).
(5) Inspect steering jack and attachments for damage and excessive wear.
(6) Inspect nose gear doors for distortion, cracks and security.
(7) Check the balance of the Nosewheel assemblies (Refer to the relevant Vendor CMM).
(8) Check axle assembly and bearings for excessive wear and damage (Disassembly required, refer to AMM Chapter 32,
NOSE AXLE ASSEMBLY).
(9) Inspect nose gear attachment fittings for cracks and signs of movement.
(10) Inspect drag stay and attachments for distortion, cracks and signs of movement.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:33 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-50-05 (Rev A0)

(11) Inspect nose gear bay structure, particularly in the vicinity of the landing gear attachments, for distortion and signs of bolt
and rivet failure.
(12) Check the tightness of all bolts securing the leg and drag stay attachment fittings to the landing gear bay sidewalls.
(13) Check nosewheel steering upper and lower pivot link assemblies for cracks using an approved crack detection method.
(14) Check nosewheel steering levers for cracks using an approved crack detection method.
(15) Check nose landing gear casing for cracks (NTM, Chapter 32, LEG CASING).
(16) Check nose landing bay sidewalls for cracks (NTM, Chapter 53, NOSE LANDING GEAR BAY SIDEWALL).
B. Main Landing Gear and MLG Bays
NOTE: This inspection is applicable to both LH and RH Main Landing Gear Assemblies.
Check/Inspect:
(1) Inspect tires for cuts, bulges and other damage.
(2) Inspect wheels and brakes for signs of damage.
(3) Inspect brake hoses for damage, security of attachment and signs of fluid leakage.
(4) Check torque link pivots (AMM Chapter 32, MAIN LEG ASSEMBLY - INSPECTION/CHECK).
(5) Inspect struts for signs of fluid leakage and damage.
(6) Check struts for correct nitrogen and fluid servicing (AMM Chapter 12, LANDING GEAR).
(7) Inspect main leg front and rear attachments for cracks and signs of movement.
(8) Inspect the bay structure, particularly near the landing gear attachments, for distortion and signs of bolt and rivet failure.
(9) Inspect retraction jack top attachments for cracks and signs of movement.
(10) Inspect main gear doors, fairings and associated attachments and fittings for damage and distortion.
(11) Inspect weight-on-wheels and gear indication microswitches for security of attachment and damage.
C. Main Landing Gear - Side Stay Assembly.
CAUTION: When doing any dismantling of side stays make sure that all right hand side stay components are kept
apart from all left hand side stay components. It is important that components are reassembled to their
original side stay.
NOTE: This inspection is applicable to both LH and RH Main Landing Gear Side Stay Assemblies.
NOTE: Before doing any crack testing using the liquid dye penetrant method, make sure that all the surface
finish and protective coatings are removed from the areas to be tested. After the crack testing is
complete the protective coating and surface finish must be restored (OM Chapter 32, SIDE STAY
ASSEMBLY).
Inspection:
(1) Examine the side stay center pivot nut for damage and distortion (AMM Chapter 32, SIDE STAY ASSEMBLY -
INSPECTION/CHECK).
(2) Do a visual inspection of the side stay and attachments in situ.
(3) Remove the side stay (AMM chapter 32, SIDE STAY ASSEMBLY - REMOVAL/INSTALLATION).
(4) Refer to Figure 1. Do a crack test of the side stay to wing attachment lug as given:
(a) Remove the bush, the surface finish and the protective coating. Degrease the areas to be crack tested.
(b) Do a crack test of the areas given, use a Type 1, Level 1, Method A liquid penetrant in accordance with the Non-
Destructive Testing Manual (NTM) General Techniques - Part C. If you find cracks, report in full and request
instructions from: Textron Aviation Inc.. The instructions must be obeyed before the airplane flies.
(c) Restore the protective treatment and surface finish to the area tested (AMM 125/H-20, Chapter 20 -**-**).
(d) Install the bush in accordance with (AMM 125/H-20, SHRINK FITTING OF BOLTS, BUSHES, PINS, ETC.).
(e) Check the flanged distance tube (OM Chapter 32-10-05, Fig. 2, Index No. 5) for distortion of the flange. If any
distortion is found then replace with a new item of the correct part number.
(5) Install the side stay (AMM Chapter 32, SIDE STAY ASSEMBLY - REMOVAL/INSTALLATION).
D. Rear Equipment Bay
(1) Inspect the bleed air and air conditioning ducting for security and signs of movement.

(2) Inspect for signs of fluid leakage, particularly from the hydraulic box.
E. Flap Hinges and Attachments
(1) Inspect the flaps for signs of contact with the wing trailing edge.
F. Systems and Equipment/Furnishings
(1) Inspect the radar antenna for damage and security.
(2) Inspect the avionics racks and components for damage and security.
(3) Inspect cabin equipment/furnishings for the correct stowage and security.
(4) Inspect the water tanks for security and signs of leakage.
(5) Inspect the instruments and panels for damage and security.
(6) Check that the emergency lighting inertia switch (if installed) has not operated.
4. Close Up and Test
A. Test
(1) Remove warning notices displayed at paragraph 1.A. (2) and (3).
(2) Remove the safety tags and close the landing gear circuit breakers (AMM Chapter 24, ELECTRICAL POWER) opened at
paragraph 1.A.(4).
(3) Energize the airplane electrical bus-bars (AMM Chapter 24, ELECTRICAL POWER).
(4) Do the landing gear retraction test (AMM Chapter 29, MAIN SYSTEM).
(5) Lower the airplane off the jacks (AMM Chapter 07, JACKING AND TRESTLING).
(6) Do a function test of the gyroscopic units, if installed.
(7) Do a function test of the radar (AMM Chapter 34, WEATHER RADAR).
B. Close Up
(1) Remove airplane electrical power (AMM Chapter 24, ELECTRICAL POWER).
(2) Make sure all areas are clean and free of tools and miscellaneous items of equipment.

Figure 1 : Sheet 1 : Wing - side stay attachment fitting - Area to be crack tested.

INSPECTIONS AFTER A COLD SOAK BELOW -40C

1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #
2. General
In the event of the aircraft experiencing a cold soak below -40°C for a period in excess of four hours on the ground, the following
inspection/checks must be done within 3 days.
A. Test:
(1) Do the functional test of the stall detection system (AMM 27-33-00, 501 in the applicable maintenance manual 750,
800XP, 800XP/850XP Pro Line 21 or 900XP), Adjustment/Test).

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:37 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-50-07 (Rev A0)

INSPECTIONS AFTER LANDING OR ABORTED TAKE-OFF IN DEEP WATER PUDDLES, SLUSH OR SNOW
1. Introduction
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #
NOTE: This inspection is only applicable if a landing or aborted take-off on a runway covered in deep water
puddles, slush or snow has been reported since the last 300 Hour Inspection.
2. Flap inner hinge bolts.
1. Adequately support flaps
2. Remove inner hinge bolts.
3. Inspect for signs of overloading.
4. Install inner hinge bolts.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:38 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-50-08 (Rev A0)

INSPECTIONS AFTER AN EMERGENCY STOP

1. Inspection
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #
2. General
WARNING: Take care when you approach the wheels after an emergency stop. Let an adequate cooling period elapse
before you attempt to remove the wheels or brake units.
WARNING: THE ground locking pins must be installed whenever the main and nose landing gears are in the down and
locked position (Chapter 10, Parking and Mooring).
WARNING: Before you disassemble any part of the landing gear hydraulic system, make sure all the hydraulic pressure
is released (AMM Chapter 29, Main System).
CAUTION: Hydraulic fluid drained or bled from the landing gear system is to be discarded. Use only new hydraulic fluid
to replenish the hydraulic system or ground servicing rigs.
3. Procedure
Do "Action after an emergency stop", AMM Chapter 32, BRAKE UNIT, Inspection/Check.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:39 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-50-09 (Rev A0)

INSPECTIONS AFTER ABNORMAL APU CONDITIONS

1. Do Oil and Oil filter samples whenever one of the following conditions occur (PATS APU GTCP36-150W CMM, Chapter
49-20-00):
A. Inspection Procedure
List of Effective Pages
Pages 1 and 2, Issued Jan.08

INSPECTIONS AFTER FLAP OVERSPEED

1. Introduction
In the event of a reported flap extension at airspeeds exceeding the recommended Vfe and Vfo by 10% or more, the following
checks must be done before the airplane is released for further flight.
List of Effective Pages
Pages 1 and 2, Issued Jan.08

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.
Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #
2. General
A. Inspect
(1) Flap surfaces for cracks, wrinkling, distortion and loose or missing fasteners.
(2) Flap system drive components for damage and security of attachment (Ref. AMM 27-50-02, 1, Figure 1 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
3. Flaps
A. Inspect
(1) Flap Hinge brackets, Screwjack and Synchronizer linkage for distortion, loose or missing fasteners/rivets and any other
structural damage.
B. Check
(1) Flap Hinge brackets, Screwjack and Synchronizer linkage for excessive play.
4. Final Items
A. Check
(1) Do the Rigging, Range of Movement, Friction and Spring Strut function tests (Ref. AMM 27-50-02, 501 in the applicable
maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
(2) Do a Flap control system functional test (Ref. AMM 27-50-02, 501 in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
5. Close Up
A. Make sure the working area is clean and free of tools and miscellaneous items of equipment.
NOTE: If this inspection turns up any findings like damaged hinge points, skin crinkling, popped rivets, etc.,
contact Hawker Beechcraft Corporation, Technical Support for further advice.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:42 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-50-11 (Rev A0)

INSPECTIONS AFTER EXPOSURE TO VOLCANIC ASH

1. Information
List of Effective Pages
Pages 1 thru 9, Issued Mar.12

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #
A. Operations In Or Around Volcanic Ash
Flight operations in, or exposure to volcanic ash may cause airframe damage and/or contamination to airplane operating
systems. Volcanic ash is highly corrosive and airborne ash particles can be abrasive to both unpainted/polished and painted
exterior components and surfaces. Additionally, ash can obstruct and contaminate airframe systems and components such as,
but not limited to, heat exchangers, air cycle machine assembly, water separator condenser and pitot/static system plumbing.
Engine internal hot and cold section components such as fan blades, compressor blades, stators, impellers and turbine blades
can have significant abrasion and can induce airflow disturbances that cause engines to operate out of balance. Engine
components such as starter/generators, bleed air ducting and P2T2 (intake probe) may also become contaminated or
obstructed.
If an airplane has been operated in or exposed to volcanic ashes, including ash cloud fallout, perform an ash encounter survey
to determine the level of contamination to the airplane systems and possible abrasion to airplane components and
unpainted/polished or painted surfaces. At this time a continued airworthiness document can be formulated with a maintenance
action for continued airworthiness of the airplane.
2. Ash Encounter Survey
A. Procedure
In most cases, an initial indicator of volcanic ash encounter will be noted on a flight crew's post flight or preflight inspection. In
more extreme cases, the crew may experience engine fluctuations while in-flight. Airplane airframe system performance may
show signs of degradation. A dusting or fogging of the flight compartment and/or the cabin interior and furnishings may also be
noted. Volcanic ash can be circulated by the airplane's air distribution system. If the crew determines a more in depth ash
encounter survey is necessary, guidelines for this survey and recommended maintenance actions for continued airworthiness
are provided below.
If an airplane has been operated in or exposed to volcanic ash, taxied on airfields subjected to volcanic ash fallout or exposed
to blowing ash, this survey will require gaining access to the nose avionics area, wing flap and spoiler cove areas, landing gear
wheel wells, engine compartments and the rear fuselage. The air cycle machine should be accessed.
This survey should also be conducted by personnel familiar with Hawker 125 series airplane configurations and systems. The
airplane flight manual (AFM), preflight inspection, exterior inspection will provide a logical path through the areas of external
evaluation. While conducting this inspection, particular attention should be given to airframe and engine leading edge surfaces,
engine inlet and bypass areas, external lights and lenses and fuselage air inlet and exhaust openings and drains (including
pitot/static system) for abrasion or contamination. Wing flap and wing spoiler coves, airframe cavities, low points or other semi-
protected areas may harbour ash deposits. For the interior of the airplane, attention should be given to air distribution ducts
and/or air outlets and flight compartment and cabin furnishings for evidence of ash deposits.
Crew reports of in-flight ash encounters and any associated airplane performance issues should also be considered during this
survey. This information, along with any inspection findings should be reviewed to determine a volcanic ash exposure category.
Volcanic ash exposure is identified as Category l, ll or lll. Each category of exposure has an associated level of maintenance
which should be performed to make sure of continued airworthiness.
During the survey, if any one item is observed from a higher category of exposure, the higher category maintenance action

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:43 CDT 2024
Hawker 750, 800XP, 850XP and 900XP Aircraft Flexible Maintenance Schedule (Rev A0)
05-50-11 (Rev A0)

should be performed. For example, if moderate abrasion damage (Category ll criteria) is observed on the exterior leading
edge surfaces, but all other findings meet Category l criteria, the Category ll maintenance action should be accomplished.
3. Volcanic Ash EXposure
A. Category l
If the airplane survey findings and/or pilot reports indicate any of the following, perform the Category l maintenance action.
• Evidence of acrid odor (e.g. smell of sulfur gas or a hot electrical smell) noted in the flight compartment or cabin area.
• Evidence of electrostatic discharge (St. Elmo's fire) on windshield, nose or engine cowlings.
• Evidence of engine interstage turbine temperature (ITT) fluctuations with return to normal values.
• Evidence of dusting or ash particles in the flight compartment or cabin area in which the crew and/or passengers did not
require the use of oxygen.
• Evidence of ash in the pitot heads, static vent ports and/or stall vent ports (if installed) refer to Category ll.
• Evidence of light abrasion of the unpainted/polished surfaces of the leading edges of the wings, horizontal stabilizer and
engine inlets and windshield retainers. This criteria also applies to landing, taxi and navigation lights and lenses
NOTE: Light abrasion of an unpainted/polished surface is defined as a slight surface roughness when felt with
the fingers or viewed with magnification.
• Evidence of light abrasion of the painted surfaces of the radome, vertical stabilizer leading edge and elevator horns.
NOTE: Light abrasion of a painted surface is defined as erosion of the topcoat of paint only but the base primer
is still visible. No bare metal or composite material is exposed.
B. Category ll
If the airplane survey findings and/or pilot reports indicate any of the following, perform the Category ll maintenance action.
• Evidence of ash deposits accumulated in the nose avionics compartment, landing gear wheel wells and/or wing flap and
spoiler cove areas.
• Evidence of minor obstruction or plugging of pitot heads, static vent ports and/or stall vent ports (if installed), insufficient
to affect instrument readings.
• Evidence of visible airborne particles or contaminants, or similar report of air quality, in the flight compartment or cabin
area during flight. Crew and/or passengers required the use of oxygen.
• Evidence of ash deposits present in the air distribution system or air cycle machine components.
• Evidence of ash deposits noted from pitot/static system drains.
• Evidence of ash deposits in the engine bypass ducts or engine nacelles.
• Evidence of engine fan, compressor or stator damage.
• Evidence of frosting or chipping of flight compartment windshields, landing, taxi and navigation lights and lenses due to
impact of ash.
• The air conditioning fails or the cabin air overheat annunciator illuminates.
• Evidence of moderate abrasion of the unpainted/polished surfaces of the leading edges of the wings, horizontal
stabilizer and engine inlets and windshield retainers.
NOTE: Moderate abrasion of an unpainted/polished surface is defined as a visible surface roughness when
viewed from a distance of approximately 3 feet (1 meter) using ambient daytime lighting.
• Evidence of moderate abrasion of the painted surfaces of the radome, vertical stabilizer leading edge and elevator
horns.
NOTE: Moderate abrasion of a painted surface is defined as erosion of the topcoat of paint and base primer
exposing the underlying bare metal or composite material.
C. Category lll
If the airplane survey findings and/or pilot reports indicate any of the following, perform the Category lll maintenance action.
• Reported vibration, surging or mismatch of engines.
• Uncommanded in-flight engine shutdown (flameout).
• Evidence of obstruction or plugging of pitot heads, static vent ports and/or stall vent ports (if installed) resulting in
erroneous instrument readings.
• Loss of engine generator due to ingestion of ash.
• Evidence of heavy abrasion of the unpainted/polished surfaces of the leading edges of the wings, horizontal stabilizer
and engine inlets and windshield retainers.
NOTE: Heavy abrasion of an unpainted/polished surface is defined as the removal of base metal or composite

material from a main structure or subassembly.

• Evidence of heavy abrasion of the painted surfaces of the radome, wing surfaces, fuselage and vertical stabilizer.
NOTE: Heavy abrasion of a painted surface is defined as removal of the topcoat of paint, base primer and any
portion of bare metal or composite material.
4. Maintenance Action
A. Category l
WARNING: Do not spray water on electrical and avionic components.
WARNING: Prior to performing external cleaning, desalination and washing of the airplanes engines it is
emphasized that a compressor wash should only be performed if specified by the engine
manufacturer's technical data.
NOTE: Volcanic ash deposits should be completely removed from all airframe and engine surfaces, including
all wing and flight control enclosures, landing gear wheel wells and nacelles. If the surface
accumulation of ash deposits is greater than 1/4 inch (6 mm), initial removal should be accomplished
with hand brushes or vacuum equipment. Ash deposits which collect in close tolerance areas or
moving surface hinge points may cause sticky or binding operation.
NOTE: Prior to cleaning the airplane it is recommended that the airplane should be allowed to stand to avoid
contact with hot surfaces such as pitot heads and AOA vanes.
(1) Install external covers and blanks. Using copious amounts of clear, clean water to perform a fresh water wash of the
complete airplane exterior structure. No ash deposits should remain. Remove any standing or pooled water by drying to
prevent corrosion formation.
(2) Deploy the thrust reverser doors and perform a clear, fresh water rinse of the thrust reverser doors and linkage
assemblies. No ash deposits should remain.
(3) Inspect the complete exterior airframe and engine cavities and low points for standing water. Remove any standing or
pooled water by drying to prevent corrosion formation.
(4) Perform external cleaning, desalination and washing of the airplane's main and APU engines as instructed by the engine
manufacturer:
(a) Main engine:Honeywell Aerospace1944 E Sky Harbor Circle NorthPhoenix, AZ 85034-
3442www.honeywell.comTel: (602) 365-3099.
(b) Hamilton Sundstrand Turbomach APU engine:General Dynamics Aviation ServicesW6355 Atlantic DriveAppleton,
WI 54914-9190Tel: 1-866-271-4327
(c) PATs (Honeywell) APU engine:9570 Berger RoadColumbiaMaryland 21046-1513www.patsinc.comTel: 410-381-
5533
NOTE: Following any powerplant cleaning or desalination wash, perform an engine run at idle setting to
dry the engines.
(5) Inspect or replace the low limit temperature control valve filter (Ref. AMM, 21-60-61, 201, in the applicable maintenance
manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
(6) Replace the water separator condenser (AMM, 21-10-95, 401, in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).Make sure the water separator drain plumbing is not obstructed (Ref. AMM, 21-10-
95, 601, in the applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
(7) Lubricate the landing gear. Refer to chapter 5, Lubrication.
(8) Visually inspect static wicks for condition (Ref. AMM, 23-60-11, 201, in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP). or AMM, 23-60-13, 201, in the applicable maintenance manual 750, 800XP,
800XP/850XP Pro Line 21 or 900XP).
(9) Run the TKS system to flush out the TKS distribution panels on the wings and on the horizontal stabilizer (Ref. AMM, 12-
30-00, 301, in the applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
B. Category ll
(1) Accomplish all Category l maintenance actions.
(2) Visually inspect the nose radome for condition and for erosion of the composite radome and inspect for any of the anti-
static paint that may have been removed (Ref. AMM, 53-50-14, 201, in the applicable maintenance manual 750, 800XP,

800XP/850XP Pro Line 21 or 900XP), and AMM 125/H-20, 20-10-3537, 201).

(3) Visually inspect the left and right pitot heads, static vent ports and stall vent ports (if installed) for condition and obstruction.
Visually inspect pitot/static drain ports for moisture and evidence of ash contamination (Ref. AMM, 34-11-19, 301, in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP). If lines are contaminated:
(a) Disconnect and blank all associated components and instruments.
(b) Blow the system out with clean dry air.
(c) Flush the system with isophenol cleaning fluid and dry using clean dry air.
(d) Remove blanks and connect all components and instruments.
(e) Perform pitot/static sense and leak checks (Ref. AMM, 34-11-19, 501, in the applicable maintenance manual 750,
800XP, 800XP/850XP Pro Line 21 or 900XP).
(4) Visually inspect:
• Window panel "A" (Ref. SRM-125-800, 56-10-11, 101).
• Window panel "B" (Ref. SRM-125-800, 56-10-21, 101).
• Window panel "C" (Ref. SRM-125-800, 56-10-31, 101).
• Inspect window sealant for erosion.
(5) Visually inspect both AOA vanes for condition, freedom of movement and visual damage.
(6) Visually inspect all fuselage antennas for condition, erosion, paint flaking, condition of sealer (sealant) and deformities, for
antenna location refer to the particular Aircraft Supplement.
(7) For airplanes without the digital pressurization control system Mod. 25G726A/C or Mod. 25G726B/C, perform the cabin
pressurization control adjustment/test procedure (Ref. AMM 21-30-00, 501, in the applicable maintenance manual 750,
800XP, 800XP/850XP Pro Line 21 or 900XP).
(8) For airplanes with the digital pressurization control system Mod. 25G726A/C or Mod. 25G726B/C, perform the cabin
pressurization control adjustment/test procedure (Ref. AMM 21-31-00, 501, in the applicable maintenance manual 750 or
900XP).
(9) For airplanes without the digital pressurization control system Mod. 25G726A/C or Mod. 25G726B/C, replace the cabin air
filters (Ref. AMM, 21-30-115 in the applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
(10) For airplanes with the digital pressurization control system Mod. 25G726A/C or Mod. 25G726B/C, replace the cabin air
filters (Ref. AMM, 21-31-20, 301 in the applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
(11) Visually inspect all nacelle and fuselage drain masts for condition, obstruction and erosion (Ref. AMM, 71-70-00, in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP). and AMM, 53-09-12, in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
(12) Visually inspect wing leading edges and wing fuel vents for condition, obstruction and erosion (Ref. SRM-125-800,
Chapter 57).
(13) Visually inspect wing spoilers, wing flap control surfaces for condition, erosion and freedom of movement (Ref. SRM-125-
800, Chapter 57).
(14) Visually inspect the wing spoiler and wing flap cove areas for condition and ash contamination (Ref. SRM-125-800,
Chapter 57).
(15) Visually inspect the aileron and aileron tab surfaces for condition, erosion and freedom of movement (Ref. SRM-125-800,
Chapter 57).
(16) Visually inspect wingtip navigation, main landing lights, nose taxi lights, anti-collision beacons, logo lights (if installed) and
strobe light lenses for condition and erosion (Ref. AMM, Chapter 33, select 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
(17) Visually inspect the main engine inlet assembly leading edges for condition and erosion (Ref. AMM, 71-10-00, in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
(18) Visually inspect the APU engine inlet assembly and exhaust ducts for condition, erosion and ash contamination.
(19) Inspect the main engine P2T2 intake probes located in the engine inlet and the bypass duct for condition and obstruction.
Refer to the applicable section of the engine manufacturer's maintenance manual.
(20) Visually inspect the main engine compressor inlet cone and LP compressor rotor assemblies for condition and erosion.

Refer to the applicable section of the engine manufacturer's maintenance manual.

NOTE: If the main engine LP inlet cone or compressor rotor assemblies exhibit damage, contact engine
manufacturer's representative for additional guidance.
(21) Replace both main engine oil filters. Refer to the applicable section of the engine manufacturer's maintenance manual.
(22) Visually inspect the main engine and APU engine starter/generator air inlet, brushes, brush holders, commutator and
cooling fan for condition and ash contamination (Ref. AMM, Chapter 24, select 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
(23) Visually inspect the thrust reverser doors and mechanical linkage for condition, ash contamination and freedom of
movement (Ref. AMM, Chapter 78, select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
(24) Visually inspect all landing gear wheel wells and doors for condition and ash contamination (Ref. AMM, 32-10-01, in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP). and AMM, 32-20-00 in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
(25) Perform both normal and emergency landing gear retraction/extension verification check (Ref. AMM, 29-10-00, 501 in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
(26) If the airplane has been operated on ash covered runways or taxiways, or been subjected to blowing ash, remove all
landing gear wheel assemblies and inspect for condition. Clean, inspect and re-lubricate all main wheel bearings Refer to
AMM, 32-40-12, in the applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP). and chapter
5, Lubrication and nose axle assembly bearings. Refer to chapter 5, Lubrication.
(27) If the airplane has been operated on ash covered runways or taxiways, or been subjected to blowing ash, visually inspect
the main landing gear brake assemblies for condition, ash contamination and freedom of operation (Ref. AMM, 32-40-
114, in the applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
(28) Visually inspect the environmental systems ram air inlet scoop and ducting for condition, ash contamination and
obstruction (Ref. AMM, 53-50-17, 401, in the applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or
900XP).
(29) Visually inspect the environmental control unit primary and secondary heat exchanger for condition, ash contamination and
obstruction. Removal of the refrigeration unit may be required for adequate inspection (Ref. AMM, 21-10-87, 201, in the
applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
(30) Visually inspect the environmental control air cycle machine for condition, ash contamination and obstruction (Ref. AMM,
21-10-87, 201, in the applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
(31) Visually inspect the vertical stabilizer leading edge assembly for condition and erosion (Ref. SRM-125-800, Chapter 55).
(32) Visually inspect the horizontal stabilizer leading edge assemblies for condition and erosion (Ref. SRM-125-800, Chapter
55).
(33) Visually inspect the elevator surfaces and elevator horns for condition, erosion and freedom of movement (Ref. SRM-125-
800, Chapter 55).
(34) Visually inspect the rudder and rudder trim tab surfaces for condition, erosion and freedom of movement (Ref. SRM-125-
800, Chapter 55).
(35) Perform lubrications as necessary . Refer to chapter 5, Lubrication.
C. Category lll
(1) Accomplish all Category l and Category ll maintenance actions.
(2) Remove the main engines from service (Ref. AMM 71-00-** select 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
Inspect the engines for internal damage including a boroscope inspection of the compressor section and turbine section
as described in the appropriate engine manufacturer's maintenance manual.
(3) Replace both main engine starter/generators (Ref. AMM, 24-30-21, 401, in the applicable maintenance manual 750,
800XP, 800XP/850XP Pro Line 21 or 900XP).
(4) If abrasion exists or if they can't be sufficiently cleaned, replace both pitot head assemblies (Ref. AMM, 34-11-24, 401, in
the applicable maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
(5) If contamination is found in the fuel filters defuel the airplane (Ref. AMM, 12-28-00, 301, in the applicable maintenance
manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).
(6) Visual inspect for and clean, if required, any ash deposits from all fuel tanks (Ref. AMM, 28-10-15, 301, in the applicable

maintenance manual 750, 800XP, 800XP/850XP Pro Line 21 or 900XP).

(7) Drain the hydraulic system reservoir and replace the reservoir suction and pressure filters (Ref. AMM, Chapter 29, select
750, 800XP, 800XP/850XP Pro Line 21 or 900XP).

INSPECTIONS FOR HYDRAULIC CONTAMINATION OF CABIN VENTILATION SYSTEM

1. Information
List of Effective Pages
Pages 1 and 2, Issued Jun.13

Instructional Data
NOTE:
Before you proceed with this inspection make sure that you have read and understood the introduction section at the
front of this schedule.

Completion of Inspection
Aircraft registration:
Aircraft total airframe hours:
Date of completion of inspection:
Checked by: License #
If hydraulic contamination of the cabin ventilation system has occurred as a result of hydraulic fluid bypassing the hydraulic reservoir
check valve then before any subsequent engine ground running or further flight do the following inspections.
A. INSPECT
(1) Charging and Drain connection for hydraulic contamination. If contamination is found replace the hydraulic reservoir check
valve, inward relief valve and reducing valve. Clean lines and unions with solvent.
(2) Right side and Left side Main Air Valves and adjacent ducts for hydraulic contamination. If contamination is found replace
both the Right side and Left side Main Air Valves and both Engine Bleed Non-Return Valves. Clean lines and bleed ducts
with solvent.
(3) Right side and Left side Mixer Valves for hydraulic contamination. If contamination is found replace both Right side and
Left side Mixer Valves. Clean surrounding bleed ducts with solvent.
(4) Pressure Regulator and Shut-off Valve (PRSOV) for hydraulic contamination. If contamination is found replace the
PRSOV. Clean surrounding bleed ducts with solvent.
(5) Water separator assembly for hydraulic contamination. If contamination is found replace the condenser sock and clean
contaminated area with solvent. Replace the Environmental Control Unit (both the heat exchanger and air cycle machine).
(6) Flow Control Venturi, Cabin Temperature Control Valve and Silencer for hydraulic contamination. If contamination is found
clean the Flow Control Venturi with solvent. Replace temperature control valve and clean ducts with solvent.
(7) Auxiliary Heating Valve and surrounding duct for hydraulic contamination. If contamination is found replace the Auxiliary
Heating Valve and clean ducts with solvent.
(8) If hydraulic contamination was found at the silencer then remove and clean with solvent all the cabin ventilation duct
installation.

Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Fri Apr 26 08:42:44 CDT 2024

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