AFS MD500 Series Manual

Document Number: MD500-IBF-KIT-OMM/IPL
Revision: B
Date: 23 MARCH 2007
4 Research Park Drive, Suite 200
St. Charles, MO 63304-5685
Operation & Maintenance Manual/
Illustrated Parts List
INLET BARRIER FILTER SYSTEM
for the
MD Helicopters Inc. (MDHI)
MD500 Series Helicopters
FAA STC No. SR01394LA
COPYRIGHT© 2002
Aerospace Filtration Systems, Inc. (AFS)
UNPUBLISHED — ALL RIGHTS RESERVED
LIMITED and/or RESTRICTED RIGHTS NOTICE
This document, along with its drawings and photographs, contains Trade Secrets and/or Commercial
or Financial Information that is proprietary to Aerospace Filtration Systems, Inc. (AFS) under 5 USC
552 as amended, and is Prohibited from Public Disclosure by 18 USC 1905. Do not duplicate or
disclose outside the U.S. Government without the express written permission of Aerospace Filtration
Systems, Inc.
The Government's rights to use, modify, reproduce, release, perform, display, or disclose these
technical data are restricted to the purpose of evaluating AFS's design for FAA commercial
certification and airworthiness consideration only. Any reproduction of technical data or portions
thereof marked with this legend, or referring to this legend, must also reproduce the markings and
legend. Any person, other than the Government, who has been provided access to such data must
promptly notify: Aerospace Filtration Systems, Inc., Attn: Business Manager, 4 Research Park Drive,
St. Charles, MO 63304-5685
The data subject to this limited/restricted rights notice is contained on all pages.

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Revision No. Revision Description Approved by: Release Date
N/C Initial Submittal M. Scimone 02-08-02
A
Corrected all references to “McDonnell Douglas
Helicopter Incorporated” to read “MD Helicopters Inc.”
and change references to “Westar” to new name “AFS”;
Title pg - add new logo & FAA project no.; Pg i - add
revision block page; Para 2.6 – add new paragraph for
Optional Ground Support Equipment providing supplier
information for the procurement of filter assembly covers;
M. Scimone 06-28-02
B
Added Filter Maintenance Aid (FMA) information to
include Section 4.5 and Figures 4 and 5. Increased IBF
Inspection interval to 500 Hours. Removed Westar
information from the cover page and header. Added
Signature Page (i).
G. Heyne 23 Mar 07

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TABLE OF CONTENTS
1.0 OPERATIONAL REQUIREMENTS............................................................................................................1
1.1 SYSTEM DESCRIPTION ....................................................................................................................................1
1.2 PRE-FLIGHT INSPECTION ................................................................................................................................2
1.3 CAUTIONS-WARNINGS-ADVISORIES/EMERGENCY PROCEDURES ...................................................................3
2.0 AIRWORTHINESS LIMITATIONS & MAINTENANCE REQUIREMENTS.......................................3
2.1 NORMAL SERVICE LIMITS ..............................................................................................................................3
2.2 STANDARD ENVIRONMENT REQUIREMENTS ...................................................................................................4
2.3 DESERT ENVIRONMENT REQUIREMENTS ........................................................................................................4
2.4 ENGINE WATER WASH/RINSE ........................................................................................................................4
2.5 UNCOVERED STORAGE ...................................................................................................................................4
2.6 OPTIONAL GROUND SUPPORT EQUIPMENT .....................................................................................................5
3.0 SERVICING INSTRUCTIONS .....................................................................................................................5
3.1 AUTHORIZED MATERIALS ..............................................................................................................................5
3.2 TOOLS REQUIRED ...........................................................................................................................................5
3.3 FILTER REMOVAL/INSTALLATION ..................................................................................................................6
3.4 INSPECTION AND PRE-CLEANING ...................................................................................................................7
3.5 CLEANING PRECAUTIONS ...............................................................................................................................8
3.6 APPLYING CLEANER.......................................................................................................................................8
3.7 RINSE PROCEDURE .........................................................................................................................................8
3.8 DRYING PROCEDURE ......................................................................................................................................9
3.9 MARKING PROCEDURE ...................................................................................................................................9
3.10 OILING PRECAUTIONS ....................................................................................................................................9
3.11 SQUEEZE BOTTLE .........................................................................................................................................10
4.0 FILTER ELEMENT REPAIR .....................................................................................................................10
4.2 PLEAT STRAIGHTENING ................................................................................................................................10
4.2 PUNCTURE DAMAGE.....................................................................................................................................11
4.2.1 Small Rupture ......................................................................................................................................11
4.2.2 Large Rupture......................................................................................................................................11
4.3 MAINTENANCE DAMAGE..............................................................................................................................11
4.4 FASTENER REPLACEMENT ............................................................................................................................12
4.5 FILTER MAINTENANCE AID INDICATOR (FMA) - OPTIONAL ........................................................................12
4.5.1 Removal ...............................................................................................................................................12
4.5.2 Inspection.............................................................................................................................................12
4.5.3 Adjustment ...........................................................................................................................................12
4.5.4 Repair ..................................................................................................................................................14
4.5.5 Function Check....................................................................................................................................14
4.5.6 Installation...........................................................................................................................................14
5.0 ILLUSTRATED PARTS LIST.....................................................................................................................15

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LIST OF FIGURES
Figure 1: AFS MD500 Inlet Barrier Filter System .......................................................................................................2
Figure 2: Example of Filter Assembly Data Plate ........................................................................................................9
Figure 3: MD500 IBF Illustrated Parts Breakdown (Sheet 1 of 6) .............................................................................16
Figure 4: MD500 IBF Optional Equipment Illustrated Parts Breakdown (Sheet 1 of 1)............................................23
Figure 5: MD500 IBF Alternative Function Check Method.......................................................................................24
LIST OF TABLES
Table 1: AFS MD500 Inlet Barrier Filter System Parts List ......................................................................................15
Table 2: AFS MD500 Inlet Barrier Filter System Optional Parts List........................................................................22
LIST OF PICTURES
Picture 1: FILTER MAINTENANCE AID .................................................................................................................13
Picture 2: FILTER MAINTENANCE AID RESET....................................................................................................13
Instructions for Continued Airworthiness
“This document serves to meet the intent of the Federal Aviation Requirements (FAR) to provide
Instructions for Continued Airworthiness. Modification of an aircraft by this Supplemental Type
Certificate (STC) obligates the aircraft operator to include the maintenance information
provided by this document in the operator’s Aircraft Maintenance Manual and the operator’s
Aircraft Scheduled Maintenance Program. The Airworthiness Limitations & Maintenance
Requirements section is FAA approved and specifies inspections and other maintenance
required. The STC kit installation information is contained in the Installation Procedures
manual, AFS-MD500-IBF-KIT-IP, and should also be placed into the appropriate operator’s
Aircraft Maintenance Manual.”

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1
AFS MD500 Inlet Barrier Filter (IBF) System
Operation & Maintenance Manual
1.0 OPERATIONAL REQUIREMENTS
1.1 SYSTEM DESCRIPTION
The Aerospace Filtration Systems (AFS) IBF system design includes an all-new aircraft upper
aft engine inlet fairing assembly. For the purpose of this manual, this component will be referred
to as the “aft fairing.” The aft fairing conforms to the inlet duct and upper section of the engine
inlet plenum chamber. The IBF system (Figure 1) is an integral aircraft component with
subsystem components incorporated into the aft fairing. It is comprised of an aerodynamic
structural fairing, integral structural frame and deflector, integral bypass system, two barrier
filter assemblies (forward and upper), integral seals, plumbing for the existing differential
pressure switch, two forward floor plates and a control rod fairing that interfaces with the
existing flexible boot and tail rotor control rod to seal the inlet plenum.
The forward and upper barrier filter assemblies are comprised of the filtration media and
mounting frames with captive fasteners. The current interface with the MDHI forward split
fairings is maintained, and the tail rotor control rod interface is improved over its current
configuration.
The IBF fairing employs a mechanically operated inlet bypass system to permit unfiltered air to
enter the engine inlet plenum chamber should the IBF filter media become obstructed. Once the
bypass system is rigged during the IBF system installation, no recurring maintenance is required.
A standard MDHI MD500 aircraft inlet differential pressure sensor is used and for most
installations the existing sensor can be reused. The sensor provides an indication to the pilot of
debris accumulation on the filter elements, glossing over due to ice or snow, and when to activate
the bypass system prior to the pressure drop across the filters exceeding operational limits.
On the ground, an optional Filter Maintenance Aid (FMA), may be mounted in the compartment
aft of the left hand passenger seat, the FMA displays the maximum differential pressure across
the filter reached during the last flight. It is accessible only on the ground, providing the
mechanic the ability to visually gauge the current condition of the filter. This gives the mechanic
the ability to forecast the timing of the next service cycle. The Filter Maintenance Aid can be
reset by depressing the yellow button marked “PUSH TO RESET” located on the end of the
Filter Maintenance Aid (See Picture 1 & 2).
The Filter Maintenance Aid is designed to hold the highest differential pressure across the filter
assembly reached during the last flight, and should be reset after servicing of the filter assembly.

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Figure 1: AFS MD500 Inlet Barrier Filter System
1.2 PRE-FLIGHT INSPECTION
Pre-flight inspection shall be made by the pilot to inspect the filters (forward and upper) for
damage, excessive accumulation of debris (straw, leaves, insects, etc.) or snow/ice, missing or
damaged fasteners, or the need for servicing or repair of the filters. After extended operation in
precipitation (i.e., rain, or a combination of rain and sleet/snow), the sand and dust collected on
the external side of the filter media (dirty side) may coagulate in the corners of the filter media
pleats. If visual inspection indicates existence of any of the above conditions, the decision
whether to service the filter assemblies will reside with the flight crew. Damaged or missing
fasteners should be replaced to maintain maximum seal integrity. The filter assemblies use
captive fasteners and should not need replacement during normal service. If the fastener should
become damaged, perform fastener replacement per manufacturer’s recommendations (see
paragraph 4.3). Operation with either missing fasteners and/or filter damage can severely
degrade IBF system separation efficiency and result in possible performance loss, wear, and/or
damage to the engine. Damaged filter elements should be either repaired as described in
paragraph 4.0 below or replaced.

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1.3 CAUTIONS-WARNINGS-ADVISORIES/EMERGENCY PROCEDURES
The “AIR FILTER CLOGGED” advisory light illuminates when the pressure drop across the IBF
elements reaches the aircraft inlet differential pressure switch setting. This light serves as a
caution to the pilot that the Turbine Outlet Temperature (TOT) has increased compared to a clean
filter element, resulting in decreased turbine temperature margin. The pilot must be aware that
under normal operation, TOT gradually increases as pressure drop increases thereby reducing
power available when temperature limited. The pilot must therefore closely monitor TOT;
continued operations in an environment causing the pressure drop and TOT to continue to increase
will eventually result in a reduction in power available. Therefore, upon illumination of the
advisory light, the pilot must evaluate current conditions, closely monitor TOT, and assess mission
requirements to determine whether to continue the flight, open the bypass door or return to place of
origin or nearest airfield. The bypass door is mechanically opened by the pilot from the cockpit by
pulling a lever mounted above and behind the left crew seat. This lever is connected through a
control cable to the bypass door located on the right side of the upper aft fairing assembly. Prior to
opening the bypass door however, the pilot must to the extent possible take action to avoid
operations in any environment that would be harmful to the unprotected engine. Emergency
conditions, requiring immediate opening of the bypass door, could result while operating in
extended brown out conditions, inadvertent icing conditions, or upon accumulation of foreign
object(s) (e.g. shedding a sheet of ice or multiple small objects including bird/insect strikes). Such
emergency conditions would be evident to the pilot by the illumination of the “AIR FILTER
CLOGGED” advisory light followed by an immediate increase in TOT.
2.0 AIRWORTHINESS LIMITATIONS & MAINTENANCE REQUIREMENTS
2.1 NORMAL SERVICE LIMITS
The actual service interval must be based on a combination of tracking engine Power Check data
(Refer to Section V of the applicable MD500 Series Rotorcraft Flight Manual), cumulative
operating hours, “AIR FILTER CLOGGED” indication and visual inspections. Any steady
illumination of the “AIR FILTER CLOGGED” light, where the pressure sensor and indicating
system are shown to be working properly, requires servicing of the filter elements at the earliest
opportunity. The gradual increase in pressure drop across the IBF elements causes a reduction in
temperature margin as measured by the Power Check. When possible, in order to minimize
unnecessary filter changes, the servicing of the IBF should only be performed after standard
troubleshooting methods are exhausted and the only remaining suspect performance driven
anomaly is inlet pressure loss. The recommended service interval is 500 hours or annually,
which can be coupled with other aircraft/engine inspections, this may be preempted by an air
filter indication light or an FMA indication. The decision whether to service the filter based on
the results of a visual inspection will reside with the pilot. If physical evidence is present that a
fungus is growing over a substantial portion of the filter media assembly (30% per assembly), it
will require servicing. Maximum number of service cycles (i.e., cleaning/oiling) is limited to 15
for each filter assembly. The forward and upper filter assemblies include a data plate that must
be scribed to track filter service cycles (see paragraph 3.9). If installed, the FMA should
periodically be checked during scheduled maintenance intervals or on condition for condition
and security. It is recommended that the function check be performed annually per Section 4.5.

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2.2 STANDARD ENVIRONMENT REQUIREMENTS
During normal conditions and typical operations in and out of prepared airfields and landing
sites, the IBF filter elements will not require frequent servicing. A Power Check should be
performed every 25 aircraft operating hours to gage the rate of engine performance degradation
due to changes in engine inlet pressure drop as the filters accumulate dirt. This is recommended
after the first installation and operation of an IBF system with an operator with no prior
experience or following relocation to an unknown environment. After establishment of a trend
and experience with the IBF system, the Power Check interval may be increased as deemed
reasonable. It is recommended, however, that a Power Check be performed at a minimum every
100 operating hours.
2.3 DESERT ENVIRONMENT REQUIREMENTS
When operating in an environment of high airborne sand and dust levels, frequent servicing of
the filter elements may be required based on the time exposure to the environment. Any
operations in this type environment that can result in “brown out” (i.e. severe dust) type
conditions should therefore be minimized or avoided to the maximum extent possible. If
extended time is being accumulated operating in “brown out” conditions, a Power Check could
be required at as low as 10-hour intervals. This reduced interval will be based on the judgment
of the pilot. It is recommended that for normal operations in a desert environment that Power
Checks be conducted every 25 hours. Servicing requirements for engines operating in this type
of environment will be primarily based on the indicated degradation of the engine performance
as determined by the Power Check results. Regular operation in a fine sand and dust
environment can cause oil loss from the element thus reducing the filter’s separation efficiency.
Under such circumstances occasional re-oiling of the element's clean side may be necessary
based on the coloration of the element.
NOTE:
Visual inspection for loss of oil should be done on
the clean side or down stream side of the filter
assembly.
2.4 ENGINE WATER WASH/RINSE
Do not deviate from the published OEM (Rolls-Royce) procedures.
2.5 UNCOVERED STORAGE
If an IBF equipped aircraft is stored uncovered and exposed to the environment (rain, snow, etc.)
or direct sunlight, the upper filter assembly must be protected and the forward filter assembly
inlet duct should be protected from snow accumulation (see paragraph 2.6 below). In particular,
the cover must be used to protect the upper filter assembly since long-term exposure to sunlight
may degrade the filtration characteristics of the media and generate a service cycle.

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2.6 OPTIONAL GROUND SUPPORT EQUIPMENT
The IBF kit does not include an environmental protection cover, as required in paragraph 2.5
above. This cover is required if the aircraft is not kept in covered storage, e.g. a hanger. The
cover must be capable of protecting both the forward and upper filter assemblies and the static
ports at the aft end of the fairing. One such cover is available from a company called Bruce’s
Custom Covers in Sunnyvale, California. This cover or any equivalent cover must be procured
separately. If using the cover manufactured by Bruce’s Custom Covers, aircraft model 369D uses
the P/N 500D-100 cover and models 369E, 369F, and 369FF all use the P/N 500E-100 cover,
both of which are designated as an “Intake/Doghouse Cover”. The complete supplier
information is as follows:
Bruce’s Custom Covers Phone: [phone]
989 E. California Ave. Toll Free (U.S.): 800.777.6405
Sunnyvale, CA 94085 Fax: [phone]
www.aircraftcovers.com E-mail: [email protected]
3.0 SERVICING INSTRUCTIONS
3.1 AUTHORIZED MATERIALS
Service AFS filters elements with only K&N Air Filter Oil (P/N 99-0551 or 99-0555), AFS Air
Filter Oil (P/N 100100-101 or 100101-101), K&N Air Filter Cleaner (P/N 99-0635 or 99-0640),
AFS Air Filter Cleaner (P/N 100200-101 or 100201-101), or an AFS authorized substitute. See
paragraph 3.6 for cleaning procedure and paragraph 3.11 for oiling quantities/procedure.
3.2 TOOLS REQUIRED
5/16-inch Slotted Screwdriver
#2 Phillips Screwdriver
Hand Seamer – 1 1/4 inch maximum jaw depth
NOTE:
Hand seamers are available through many commercial
aircraft supply stores (local or on-line) and also through
commercial heating and air conditioning supply stores.
Recommend the following: Malco Tools “Hand Seamer
with Forged Steel Jaw”, Catalog # S2, S3 and S6, see
www.malcotools.com. The S3 model is also available
through Wicks Aircraft Supply, Part Number TP44-0,
“Offset Hand Seamer”, see www.wicksaircraft.com.

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3.3 FILTER REMOVAL/INSTALLATION
The IBF system uses two barrier filter assemblies that can be easily removed for cleaning and/or
replacement. The system is designed for easy access and removal of the filter assemblies with
the aircraft shutdown on the ground.
Upper Filter Removal
CAUTION
After removal of the filter assemblies, inspect the
filter seals on the aircraft for visible damage and
security.
CAUTION
After removal of the filter assemblies, cover the
engine inlet to ensure it is protected from FOD, if
the assemblies are not reinstalled immediately.
Removal of the top filter requires the disengagement of (14) captive Dzus type fasteners.
A ¼ turn (counterclockwise) with a slotted screwdriver is all that is required to remove
the Dzus stud (screw head) from the receptacle. Once all the fasteners are loose, filter
element must be carefully removed so as not to damage the seals. The upper filter has the
seal attached to the underside of the filter assembly.
Upper Filter Installation
WARNING
Prior to installation of the filter assemblies,
remove any FOD protection from the engine
bellmouth.
Prior to installation of serviced filter assembly, the seal shall be visually inspected for
security and damage. Insert the upper filter assembly into the upper aft fairing cutout;
insure the assembly is seated properly in the upper opening. Engage the (14) captive
Dzus type fasteners by rotating ¼ turn clockwise and ensure the seal is uniformly
compressed. Do not over rotate the fasteners, over rotation will result in damage to the
stud and/or the receptacle.

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Forward Filter Removal
CAUTION
After removal of the filter assemblies, inspect the
filter seals on the aircraft for visible damage and
security.
CAUTION
After removal of the filter assemblies, cover the
engine inlet to ensure it is protected from FOD, if
the assemblies are not reinstalled immediately.
To remove the forward filter assembly, remove the right detachable forward upper inlet
fairing. Remove the (10) Phillips head screws that secure the oil cooler FOD screen,
remove the FOD screen. Disengage the (8) captive Dzus type fasteners that fasten the
forward filter assembly to the forward frame. A ¼ turn (counterclockwise) with a slotted
screwdriver is all that is required to remove the Dzus stud (screw head) from the
receptacle. The forward filter assembly seal is attached to the forward frame.
Forward Filter Installation
WARNING
Prior to installation of the filter assemblies,
remove any FOD protection from the engine
bellmouth.
Prior to installation of serviced filter assembly, the seal shall be visually inspected for
security and damage. Insure that the forward filter assembly is seated properly in the
forward frame. Engage the (8) captive Dzus type fasteners by rotating ¼ turn clockwise
and ensure the seal is uniformly compressed. Do not over rotate the fasteners, over
rotation will result in damage to the stud and/or the receptacle. Reinstall the oil cooler
FOD screen and secure with (10) Phillips head screws.
3.4 INSPECTION AND PRE-CLEANING
Remove the filter elements and inspect the serviceability tag. If all the blocks have been marked
through, the assembly should be discarded and replaced with a new or other serviceable
assembly. If there are service cycles left on the assembly, proceed with pre-cleaning. Carefully
remove any large debris by hand or with tweezers then gently brush the dirty side of the filter
with a soft bristle brush similar to a soft paintbrush to remove any heavy deposits.

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3.5 CLEANING PRECAUTIONS
CAUTION
Do not clean AFS elements with gasoline,
solvents, parts cleaners, strong detergents, or
caustic cleaning solutions.
CAUTION
Do not steam clean or use high-pressure washers
to clean the AFS element.
Use only K&N Filter Cleaner, AFS Air Filter Cleaner, or an AFS approved substitute. The K&N
Filter Cleaner is commercially available (see paragraph 3.1). Use of any product other than those
approved by AFS will cause damage the filter media and/or frame assembly. The use of any other
cleaning material is strictly prohibited and voids any manufacturer warranty.
3.6 APPLYING CLEANER
Spray cleaner liberally onto the entire element (both sides) until the filter media is thoroughly
soaked. If procured in bulk, transfer a smaller quantity to a spray bottle. A spray bottle provides
a more uniform distribution of the cleaning agent. With the filter element lying flat (dirty side
down), let the cleaner soak into the filter media for 15 minutes.
3.7 RINSE PROCEDURE
After the cleaner has soaked for 15 minutes, rinse the filter with low-pressure water. Use water
out of a standard faucet or hose (without nozzle). Start flushing in the opposite direction of
airflow, i.e., from the clean side to the dirty side. Arrange the filter so the pleats are vertical, and
begin to rinse in a gradual side-to-side motion starting at the top and working downward. Adjust
the pace to correspond with the cleanliness of the water runoff. As long as the runoff is filled
with debris and oil, do not proceed downward. Upon completion, rotate the filter to clean from
the dirty side to the clean side, pleats still vertical. Using very low water pressure to avoid
driving the debris deeper into the media, repeat the rinsing procedure until there is no visible
debris on the surface and the runoff water is clean. When finished, flip the filter once again and
repeat the rinse from clean side to dirty side. Finally, rotate the filter from top to bottom, and
perform the final rinse until the runoff water is free of all debris and oil. After the final rinse,
inspect filter by viewing through the filter to a direct light source. If debris still remains a repeat
cleaning may be necessary.

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3.8 DRYING PROCEDURE
CAUTION
Do not use compressed air since it will damage
the filter media.
CAUTION
Do not use heat from any source to dry the AFS
element. Heat will shrink the filter media and
may damage the coring material within the filter
frames.
After rinsing, shake off the excess water and let the element dry at room or outside air
temperature (above freezing).
NOTE
After cleaning and before oiling of the dry filter
element, the pleats should be inspected and, if
required, straightened or crimped per the
procedure at paragraph 4.1 below.
3.9 MARKING PROCEDURE
After the filter assembly has dried take a sharp instrument (scribe or center punch) or a vibro-
peen and scratch an “X” through one of the unmarked boxes on the serviceability tag. Use
caution not to slip and injure yourself or damage the filter element. When the last unmarked box
is crossed through the filter assembly will have to be replaced when servicing is required again.
Figure 2: Example of Filter Assembly Data Plate
3.10 OILING PRECAUTIONS
WARNING
Never put an AFS Filter Assembly in service
without oiling it.

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CAUTION
Use only K&N Air Filter Oil, AFS Air Filter Oil,
or an AFS approved substitute.
The filter will not function properly if other types of oil are used. Both K&N Air Filter Oil and
AFS Oil are a unique blend of oil base stocks and special polymers that form a very efficient
“tack barrier.” Dye is added to show areas of oil application. Do not use transmission fluid, any
kind of motor oil, or diesel fuel to oil the AFS filter. Do not use “WD-40,” “LPS,” or any other
type of lightweight spray lubricants to oil the AFS filter. Use of any product other than those
approved by AFS will cause damage the filter media and/or frame assembly. The use of any
other oiling material is strictly prohibited and voids any manufacturer warranty.
3.11 SQUEEZE BOTTLE
CAUTION
Use caution not to over oil.
A squeeze bottle allows for the controlled application of a specific amount of oil per filter.
Seven fluid ounces (7 fl. oz., 102465-101) is the quantity to be applied to the forward filter
assembly (P/N 102450-101) and fourteen fluid ounces (14 fl. oz., 102425-101) should be applied
to the upper filter assembly (P/N 102400-101). Lay filter flat, gently squeeze a small stream of
oil along the entire length of each pleat peak, then flip the filter over and repeat this on the
backside. Apply sparingly to ensure coverage of the entire filter. Use caution not to over oil.
Let the filter sit for 30 minutes as the oil “wicks” into the surrounding filter media. The oil
wicks most effectively when the filter is laying flat. Apply remaining filter oil (not to exceed the
quantities above) to any areas that are still white or not yet uniform in color. Use caution not to
over oil.
4.0 FILTER ELEMENT REPAIR
4.2 PLEAT STRAIGHTENING
CAUTION
Hand seamer must be limited to a maximum jaw
depth of 1 1/4 inch. A deeper jaw depth can
result in deformation or damage to the adjoining
pleats.

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CAUTION
Do not over crimp and crush pleat, care must be
taken to squeeze the pleats without deforming or
damaging the pleated screen.
After servicing of the filters, the pleats may require straightening or crimping. When looking
down on the filter from either side, you must be able to see the bottom of the pleat. If you cannot
see the bottom of the pleat, the airflow will be restricted and/or the pleats will stick together
when dust loaded. Any restriction to the flow through the pleats will result in increased pressure
drop and reduction in sand loading capacity. In order to insure ideal flow characteristics through
the filter media, the pleats must be straightened or crimped with a standard sheet metal tool
(hand seamer). Once one side is crimped, flip the filter over and crimp the other side as required
following the guidance above.
4.2 PUNCTURE DAMAGE
In the event of damage to the filter system, ruptures in the filter can be repaired without risk of
structural deformation of the filter element. Small ruptures defined as smaller than a dime can be
sealed shut without degradation of performance. Larger ruptures exceeding a dime in size
require the assembly to be returned to AFS for evaluation. Details of these repair procedures are
defined below. Prior to performing any of these repairs, the filter material must be cleaned and
void of contamination and oil.
4.2.1 Small Rupture
Ruptures or voids in the material up to a dime in size can be trimmed clean to remove loose
material (wire or cotton gauze) and encased in a sealing material. The sealing material shall be a
two-part sealant, such as AMS 3276, for standard use on aircraft. Allow the sealant to bleed into
the filter material and cure before operating to ensure it will not dislodge into the engine inlet
plenum.
4.2.2 Large Rupture
Ruptures in the material exceeding a dime in size are not repairable in the field, and the element
shall be returned to AFS for evaluation and disposition.
4.3 MAINTENANCE DAMAGE
The repair procedures defined above are valid for handling damage resulting in ruptures as
described above. Any unrepairable damage to the filter frames that impair the integrity of the
structural security or sealing surfaces shall require the element to be returned to AFS for
evaluation and disposition.

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4.4 FASTENER REPLACEMENT
In the event a fastener becomes damaged and is no longer functional, replacement fasteners are
identified in the section 5.0 Illustrated Parts List. Cut the retaining grommet with a pair of
diagonal cutters and remove stud from hole. Insert new stud through ejector blade hole and
place new grommet over the end of the stud. Flatten grommet with suitable tool to make the stud
captive. If the receptacle is damaged, drill out rivets that secure receptacle. The receptacles used
on the IBF are floating receptacles, Dzus Type RF35. When replacing a receptacle be sure to
install the spacers, Dzus Type RF35-5L in the receptacle holes prior to riveting the receptacle
back in place. Ensure receptacle floats after assembly.
4.5 FILTER MAINTENANCE AID INDICATOR (FMA) - OPTIONAL
The Filter Maintenance Aid provides an indication to maintenance personnel as to the trend of
the differential pressure across the Filter Assembly. The construction details of the component
do not warrant field maintenance. Repair of this component requires it to be sent back to AFS
for disposition, or replacement. The FMA is an aid to help maintenance personnel to ascertain
the current condition or trend in accumulation of dirt on the Filter Assembly.
4.5.1 Removal
Access the aft compartment behind the left hand passenger seat. Disconnect the hose from the
AN842-4D nipple. Then remove the hardware and FMA Retaining Ring from Filter Maintenance
Aid Mount. Remove Filter Maintenance Aid.
4.5.2 Inspection
Inspect the Filter Maintenance Aid and associated mounting for discoloration affecting
readability, cracks, deformation, missing or damaged components, and serviceability. Inspect
the Filter Maintenance Aid Tube Assembly for debris and insure that the tube is clear and
unobstructed. Inspect the associated components, such as the Mount Assembly and hardware for
missing components, cracks, distortion or deformation, scratches or gouges, or missing
protective coatings. If Filter Maintenance Aid Bracket assembly is cracked or nut-plates are
unserviceable, drill out the attaching rivets that secure the component and obtain new component
and re-attach using same type rivets (MS20470AD4 for bracket) or (MS1097AD3 for nut-
plates).
4.5.3 Adjustment
The Filter Maintenance Aid is designed to hold the highest differential pressure across the filter
assembly reached during the last flight, and can be reset by depressing the yellow button marked
“PUSH TO RESET” located on the end of the filter maintenance aid (See Pictures 1 & 2).

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Picture 1: FILTER MAINTENANCE AID
(ABOVE) “YELLOW Indicator” position relative to SAFE OPERATING ZONE (“GREEN Zone”) or SERVICE
FILTER (“RED Zone”) markings defines current filter condition and pushing “YELLOW RESET Button” resets
indicator. (BELOW) FMA unit is mounted to the scavenge valve bracket assembly behind the left hand passenger
compartment quarter panel assy.
Picture 2: FILTER MAINTENANCE AID RESET
RED Zone
RED Zone
GREEN Zone
YELLOW
RESET Button
YELLOW
Indicator
Press YELLOW
Button to RESET

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4.5.4 Repair
The construction details of the component do not warrant field maintenance. There is no repair
for this component, contact AFS to obtain a new component. If the Filter Maintenance Aid fails
the function check, disconnect the hose assembly and inspect for damage or blockage of the tube
assembly. Inspect the opening on the Filter Maintenance Aid for obstructions. Remove
obstructions if present. Reattach hose assembly and perform function check (Refer to Section
4.5.5). If it fails function check, replace FMA. Replace damaged sheet metal components of the
Mount Assembly and missing or damaged hardware if required. Re-apply corrosion protection
to mount as required.
4.5.5 Function Check
CAUTION
IMPROPER USE OF THE ALTIMETER TEST SET COULD RESULT IN DAMAGE TO THE
FILTER MAINTENANCE AID.
CAUTION
IMPROPER USE OF THE ALTIMETER TEST SET SUCH AS PULLING AN ALTITUDE OF
GREATER THAN 1880 FEET ABOVE FIELD ELEVATION WILL DAMAGE THE FILTER
MAINTENANCE AID.
Connect the Barfield (or equivalent) altimeter test set vacuum system to the end of the fitting
inside the plenum area. Ensure that the fit between the test set and fitting is tight, i.e., no leakage.
Reset the Filter Maintenance Aid by depressing the yellow button marked “PUSH TO RESET”
located on the end of the filter maintenance aid (See Picture 2). The maintenance aid should
indicate in the red zone within the following range:
Test Station Elevation (ft)
Test Method 0 2000 4000 6000 8000 10000
Low Pressure Calibrator (inches of H2O) 10.5 ± 1.1
Altimeter Test Set (ft above test station elevation) 720 ±70 770 ±80 810 ±80 870 ±90 920 ±90 980 ±100
* Note: See Figure 5 for an alternate function check method.
4.5.6 Installation
Position the Filter Maintenance Aid into the Mount Assembly. Install hardware and connect hose assembly.
Perform Function Check of Filter Maintenance Aid (Refer to Section 4.5.5).

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5.0 ILLUSTRATED PARTS LIST
Parts can be ordered by calling Aerospace Filtration Systems (AFS), at [phone].
Item No. Part No. Description Qty Ref. Fig. 3
1. 102450-101 Filter Assembly – Forward 1 Sheet 1
2. 102315-201 Seal – Filter, Upper 1 Sheet 1
3. 102400-101 Filter Assembly – Upper 1 Sheet 1
4. 102413-203 Grip – Finger 1 Sheet 1
5. 102323-201 Shim – Hinge 1 Sheet 2
6. 102309-201 Hinge Half – Fairing 1 Sheet 2
7. 102317-201 Seal – Bypass Door 1 Sheet 2
8. 102324-201 Stop – Latch 1 Sheet 2
9. 102321-201 Shim – Latch 1 Sheet 2
10. MS21219WG3 Clamp 5 Sheet 2 & 6
11. 102301-201 Fairing 1 Sheet 2
12. 102311-201 Deflector 1 Sheet 2
13. 102307-201 Frame – Structural, Forward 1 Sheet 2
14. 102313-201 Seal – Filter, Forward 1 Sheet 2
15. 102319-201 Fairing – Control Rod 1 Sheet 2
16. 102303-201 Floor Plate 1 Sheet 2
17. 102303-203 Floor Plate – L/H 1 Sheet 2
18. 102305-201 Attach Plate – Sides 2 Sheet 2
19. 102306-201 Attach Plate – Aft 1 Sheet 2
20. 102370-101 Latch Assembly 1 Sheet 3
21. MS24665-132 Cotter Pin 1 Sheet 3
22. 102375-201 Plunger – Latch 1 Sheet 3
23. C0360-035-0560-M Spring 1 Sheet 3
24. 102371-201 Body – Latch 1 Sheet 3
25. 102373-201 Lever – Latch 1 Sheet 3
26. AN960PD-10 Washer 4 Sheet 3
27. MS20392-2C11 Clevis Pin 1 Sheet 3
28. 102377-201 Pin – Latch 1 Sheet 3
29. AN310-3 Nut 1 Sheet 3
30. FF303-01 Bushing 1 Sheet 3
31. 102350-101 Door Assembly – Bypass 1 Sheet 4
32. 102359-201 Hinge Pin – Door 1 Sheet 4
33. 102357-201 Hinge Half – Door 1 Sheet 4
34. 102351-201 Door – Bypass 1 Sheet 4
35. 102353-201 Handle – Door 1 Sheet 4
36. 102355-201 Strike Plate – Door 1 Sheet 4
37. X-1031 Ejecting Blade 22 Sheet 5
38. RF35 Receptacle 22 Sheet 5
39. RF35-5L Spacer 44 Sheet 5
40. GH35 Grommet 22 Sheet 5
41. A35T33 Stud (Upper filter assy. – front) 10 Sheet 5
42. A35T36 Stud (Upper filter assy. – side/aft) 4 Sheet 5
43. A35T27 Stud (Forward filter assy.) 8 Sheet 5
44. 102325-201 Cable 1 Sheet 6
Table 1: AFS MD500 Inlet Barrier Filter System Parts List