SERVICE
1243B
BULLETIN
NO.
Piper Aircraft, Inc.
2926 Piper Drive
Vero Beach, Florida, U.S.A. 32960
PIPER CONSIDERS
COMPLIANCE MANDATORY
Date: March 1, 2012
(S)
Service Bulletin 1243B supersedes Service Bulletin 1243A in its entirety.
reason for revision:
SB 1243B revises the hydraulic pump inspection procedure and extends the
compliance time allowance to perform the inspection.
Additionally, SB 1243B includes the Summary statement defining warranty
coverage for all aircraft defined in this Service Bulletin.
Subject:potential Landing Gear MALFUNCTION
Models Affected:
Serial Numbers Affected:
PA-46-350P Mirage
PA-46-500TP Meridian
PA-46R-350T Matrix
4636299, 4636314 through 4636519
4697001 through 4697473
4692001 through 4692173
Compliance Time:
• Each time the aircraft is moved or towed, until such time as Part II (and on
condition, Part III) is accomplished perform Part I. Precautionary Operating
Instructions.
• Within the next one hundred twenty (120) calendar days, perform Part II.
Inspection.
Purpose:
The landing gear component manufacturer, Triumph Actuation Systems, has
notified Piper that some of the affected aircraft may be equipped with a hydraulic
pump that was misassembled at their factory. Aircraft with this condition will exhibit
the following characteristics:
• When parked for an extended period of time with the electrical power OFF, the
landing gear may not remain in the down and locked position. If the aircraft is
subsequently moved or towed, one or more landing gear may retract as the
aircraft rolls.
• As long as the electrical power is ON, normal operation of the landing gear is
not affected.
This Service Bulletin provides an inspection procedure to identify a hydraulic
pump that was assembled incorrectly, as well as instructions to replace or rework
pumps so identified. Additionally, this Service Bulletin provides precautionary
operating instructions which must be followed until the inspection procedure has
been accomplished.
ATA: 3200
(OVER)
SERVICE BULLETIN NO. 1243B
PAGE 2 of 6
Instructions:
Part I.
1.
Precautionary Operating Instructions
Immediately prior to moving or towing the aircraft, turn electrical power to ON position for at least 10 seconds,
and verify that all landing gear are in the down and locked position, as indicated by an instrument panel with
three green lights illuminated near the landing gear selector lever. Then turn power off, and move or tow the
aircraft in a normal fashion.
note:
At the operator’s discretion, electrical power may be applied to the aircraft via a ground cart, instead
of turning on electrical power from the cockpit.
2.
The above procedure must be performed each and every time the aircraft is moved in any way. This includes
towing, pushing by hand, or moving the airplane under its own power. Any movement of any kind.
3.
Posting a copy of this service bulletin in the airplane door window so that it is visible to line personnel is
suggested.
Part II.
Inspection
1.
Turn electrical power to ON position for at least 10 seconds, and verify that all landing gear are in the down
and locked position, as indicated by an instrument panel with three green lights illuminated near the landing
gear selector lever. Then turn power off.
2.
Remove power from the aircraft by pulling the main power circuit breakers.
3.
Remove aircraft interior closeout to gain access to the hydraulic pump.
4.
Examine hydraulic pump nameplate:
a.
If nameplate has a “C” marking or higher in the “MODS INCORPORATED” area, the hydraulic pump has
been correctly assembled at the factory.
1) Reinstall closeout panel and reset the main power circuit breakers.
2) Proceed to “Part VI. Documentation of Compliance”.
b.
If nameplate has any marking other than a “C” or higher in the “MODS INCORPORATED” area, further
inspection is required.
5.
Place aircraft on jacks per instructions in the appropriate Maintenance Manual with landing gear remaining in
the down and locked position.
6.
Fill hydraulic pump reservoir to the full mark using clean MIL-PRF-5606 hydraulic fluid.
7.
Ensure vent on pump reservoir is unobstructed and open to atmosphere.
8.
Using a suitable container to catch the fluid, loosen and remove the hose connection to the DOWN (extend) side
of one of the main landing gear actuators. See Figure 1.
a.
If a steady flow of fluid drains from the DOWN hose and a noticeable drop in fluid level in the reservoir is
observed, the pump is defective and requires rework. Proceed to “Part III. Replace Hydraulic Pump”.
b.
If very little fluid drains from the DOWN hose and no drop in reservoir fluid level is observed, continue to
the next step.
SERVICE BULLETIN NO. 1243B
PAGE 3 of 6
Figure 1
Main Landing Gear Actuator
9.
Using a suitable container to catch the fluid, loosen and remove the hose connection to the UP (retraction) side
of the same main landing gear actuator. See Figure 1.
a.
If a steady stream of fluid drains from the UP hose and a noticeable drop in fluid level in the reservoir is
observed, the pump is acceptable.
1) Re-attach both the DOWN and UP hoses and refill the reservoir with clean MIL-PRF-5606 hydraulic
fluid, if required.
2) In the “MODS INCORPORATED” area on the nameplate, re-mark the pump as described in the
attached Triumph Service Bulletin 1FA13059-32-0001, page 5, Item F.
3) Proceed to “Part V. Post Inspection / Post Installation Testing”.
b.
If very little fluid drains from the UP hose and no change in the reservoir fluid level is observed, the pump
is defective and must be replaced. Proceed to “Part III. Replace Hydraulic Pump”.
Note:
In this case, the pump must be replaced. It cannot be reworked.
SERVICE BULLETIN NO. 1243B
PAGE 4 of 6
Part III. Replace Hydraulic Pump
1.
Order replacement hydraulic pump Piper Part Number (P/N) 102559-804RBL.
2.
Examine the nameplate on the replacement hydraulic pump received. Verify that the nameplate has the letter
“C” or higher marked in the “MODS INCORPORATED” area prior to installing hydraulic pump in aircraft.
3.
Install replacement pump per instructions in the appropriate Maintenance Manual.
NOTE: Ensure that the new pump is installed with the special Piper “restrictor” elbow (painted red) P/N
85127-008 on the DOWN port of the hydraulic power pack. Reuse of the restrictor elbow originally
installed on the pump being replaced is approved. See Figure 2.
4.
Ensure that the vent cap screw and washer are removed from the new hydraulic pump prior to operation in the
aircraft. See Figure 2.
5.
Proceed to “Part V. Post Inspection / Post Installation Testing”.
Part IV. Hydraulic Pump Rework
1.
Remove hydraulic pump from aircraft per instructions in the appropriate Maintenance Manual.
2.
Rework pump per instructions provided in Triumph Actuation Systems Service Bulletin 1FA13059-32-0001,
attached.
Note:
3.
This rework will require replacement of some pump components, as described in the Triumph Service
Bulletin. Order Piper P/N 187-498 from your nearest authorized Piper Dealer. Additional parts required
as defined in the attached Triumph Service Bulletin 1FA13059-32-0001 can be obtained locally.
Reinstall hydraulic pump in aircraft per instructions in the appropriate Maintenance Manual.
NOTE: Ensure that the pump is installed with the special Piper “restrictor” elbow (painted red) P/N 85127008 on the DOWN port of the hydraulic power pack. Reuse of the restrictor elbow originally installed
on the pump being replaced is approved. See Figure 2.
4.
Proceed to “Part V. Post Inspection / Post Installation Testing”.
Part V.
1.
Post Inspection / Post Installation Testing
Perform a Landing Gear Retraction System Functional Test per instructions in the appropriate Maintenance
Manual, section 32-30-00.
Note:
Inspect the landing gear hydraulic system for leaks.
2.
Remove aircraft from jacks.
3.
Proceed to “Part VI. Documentation of Compliance”.
Part VI. Documentation of Compliance
Make a logbook entry indicating compliance with Part II and/or Part III or Part IV of this Service Bulletin, as
applicable.
SERVICE BULLETIN NO. 1243B
PAGE 5 of 6
Vent Cap Screw and Washer
85127-008 Restrictor Elbow (Red)
AN6289D5 Nut (477-915)
MS28778-5 O-ring (485-099)
MS28773-05 Retainer (584-359)
Torque: 85-95 in. lbs.
Figure 2
Hydraulic Pump
SERVICE BULLETIN NO. 1243B
PAGE 6 of 6
MATERIAL REQUIRED:
Part I.
Precautionary Operating Instructions
One paper copy of this Service Bulletin, printed locally.
Part II.
Inspection
Nomenclature
Piper P/N
Qty
Hydraulic Fluid MIL-PRF-5606
obtain locally
As required
Nomenclature
Piper P/N
Qty
Hydraulic Pump 102559-804RBL
1 (on condition)
Part III. Replace or Rework Hydraulic Pump
Note:
P/N 102559-804RBL is interchangeable with part numbers 102559-002, 102559-003, and 102559004. Additionally, note that the “-nnn” suffix in the part numbers above may appear as “-n”, “-nn”, or
“-nnn”.
Restrictor Elbow (red)
85127-008
1 (obtain from pump being replaced)
Hydraulic Fluid MIL-PRF-5606
obtain locally
As required
187-498
1 (on condition)
or
Pilot Piston Seal 1FA1305952
Additional parts as specified in attached Triumph Service Bulletin 1FA13059-32-0001 as required, obtain locally.
Hydraulic Fluid MIL-PRF-5606
obtain locally
As required
AVAILABILITY OF PARTS:
Your Piper Service Facility.
Effectivity date:
This Service Bulletin is effective upon receipt.
summary:
Applicable Factory Participation includes all affected aircraft listed in the Serial
Number Affected category of this Service Bulletin. Factory Participation will
remain in effect for a period of time not to exceed 120 days from the date of this
Service Bulletin.
Please contact your Factory Authorized Piper Service Facility to make
arrangements for compliance with this Service Bulletin in accordance with the
compliance time indicated.
Note:
Please notify the factory of any address/ownership corrections. Changes should include aircraft model,
serial number, current owner’s name and address.
Corrections and/or changes should be directed to:
PIPER AIRCRAFT, INC.
Attn: Customer Service
2926 Piper Drive
Vero Beach, FL 32960
SERVICE BULLETIN
HYDRAULIC REVERSIBLE PUMP – VERIFICATION OF CORRECT
ASSEMBLY OF PILOT CHECK VALVE AND SPRING
1.
PLANNING INFORMATION
A.
Effectivity
This service bulletin applies to the Hydraulic Reversible Pump Unit used on
Piper Mirage/Meridian/Matrix applications.
1FA13059-1 (Piper 102559-2)
1FA13059-2 (Piper 102559-003)
1FA13059-3 (Piper 102559-004)
Serial numbers FAH0001-FAH0931
NOTE: If nameplate has a “C” marking in the “MODS INCORP” area this
service bulletin has already been accomplished.
B.
Reason (Refer to Figure 3)
The Pilot Check Valve Piston PN 1FA1305971 (Item #285) and Spring PN
1FA1305956 (Item # 255) may have been installed in a reverse orientation
during original assembly or during repair activity. Although the piston has a
spring seat on one side, it is symmetrical in configuration and the sole function
of this spring is to bias the piston to hold the UP check valve open when normal
operating pressure is not present, i.e. pump is off and trapped pressures may
bleed down. This causes the UP circuit pressure to normally bleed to reservoir
in all unpressurized cases in order to prevent inadvertent unlocking of the
actuators.
During normal operation, e.g. normal takeoff, flight, and landing when the pump
is energized, the hydraulic force on the piston exceeds the spring force by a
significant factor. Therefore, reverse installation does not affect normal
pressurized operation of the pump or landing gear system. In addition, reverse
installation has no effect on gear function or safety during emergency
deployment, descent, or landing.
When the aircraft is parked and pressure in the DOWN circuit has dissipated,
reverse installation of the Piston and Spring causes pressure to be trapped in
the UP circuit. Long term thermal changes may cause fluid expansion
(pressure increase) in the UP circuit. If the thermal changes are severe
enough, one of the landing gear actuators may unlock. In this case, pressure is
immediately relieved via motion of the actuator lock piston. After such an event,
the unlocked actuator will not freely stroke as there are multiple restrictions in
flow paths in the Power Pack. Therefore there is no safety issue for the landing
Issue December 16, 2011
1FA13059-32-0001
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SERVICE BULLETIN
gear systems. However, over a period of time the unlocked Actuator may slowly
retract due to non-zero leak paths; in the case of an additional hydraulic system
compromise (e.g. serious leak) the affected actuator would freely retract
causing catastrophic collapse of the landing gear.
C.
Description
This service bulletin provides a bench check test procedure to verify correct
installation of the Piston and Spring. If the bench check test procedure reveals
incorrect assembly of the Piston and Spring, this service bulletin provides a
procedure to disassemble the Reversible Pump sufficiently to access the Piston
and Spring and re-install them in the correct orientation.
D.
Compliance
Triumph Actuation recommends that this service bulletin be accomplished at
the next shop visit.
E.
Approval
This service bulletin does not contain any change information that revises the
equipment approved design standard; therefore its technical content does not
require supplementary regulatory approval.
F.
Manpower
No additional manpower will be required if this service bulletin is accomplished
during overhaul or repair of the Hydraulic Reversible Pump.
If this service bulletin is not accomplished during a scheduled overhaul or repair
of the Hydraulic Reversible Pump, then it is estimated to take 0.25 man-hours
of labor to comply with the bench check test procedure and 1.50 man-hours of
labor to disassemble and re-install the Piston and Spring in the correct
orientation. The ATP requires 1.00 man-hours to complete. This labor estimate
does not include full disassembly of the Hydraulic Reversible Pump,
rectification of any other discrepancies which may be discovered during
accomplishment of this service bulletin.
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SERVICE BULLETIN
G.
Weight and Balance
Not Applicable
H.
Electrical Load Data
Not applicable.
I.
Software Accomplishment Summary
Not applicable.
J.
References
None.
K.
Other Publications Affected
Not applicable.
L.
Interchangeability or Interminability of Parts
This service bulletin does not affect interchangeability of the Hydraulic
Reversible Pump configurations.
2. MATERIAL INFORMATION
A.
Kit Material – Price and Availability
Kit Information does not apply.
B.
Industry Support Information
Not applicable.
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SERVICE BULLETIN
C.
Material Necessary for Each Component
Hydraulic Reversible Pump 1FA13059-1/-2/-3
PART
NUMBER
M83461/1-012
M83461/1-014
1FA1305952
(Piper#187-498)
MS28778-4
SOURCE
KEYWORD
QTY
Packing
Packing
2
2
(1)
(1)
Pilot Piston Seal
1
(2)
Boss Packing
1
(1)
SOURCE
(1) Standard hardware available through normal suppliers
(2)
Piper Aircraft, Inc.
2926 Piper Drive
Vero Beach, FL 32960
The parts listed above are the only parts required to disassemble the Hydraulic
Reversible Pump sufficiently to remove the Piston and Spring and re-install
them in the correct orientation - it does not reflect any parts necessary to rectify
any other discrepancies which may be discovered during this process.
D.
Material Supplied by the Operator
Only the material required during normal servicing of the Hydraulic Reversible
Pump will be required to accomplish this service bulletin.
E.
Material Necessary for Each Spare
Necessary material is shown in Section 2.C. above.
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SERVICE BULLETIN
F.
Re-identified Parts
After correct installation of the piston and spring, or verification of correct
installation, re-identify by permanently scribing, stamping, or laser marking “C”
in the “MODS INCORP” marking area of the Hydraulic Reversible Pump name
plate (refer to Figure 1).
G.
Tooling – Price and Availability
A #4-40 UNC-3B threaded screw will be needed to withdraw both Caps (Item
#40) from the Pilot Check Valve bore in the Housing (Item #5), (Refer to Figure
3).
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SERVICE BULLETIN
3. ACCOMPLISHMENT INSTRUCTIONS
A. BENCH CHECK TEST PROCEDURE TO VERIFY CORRECT
INSTALLATION OF THE PISTON AND SPRING.
REFER TO FIGURES #1 AND #2 FOR THE FOLLOWING STEPS
1.
Remove Air Vent and Fill Port Plug PN 1FA1305935 (Item #55).
2.
Remove and discard Boss Packing PN MS28778-4 (Item #205) as shown in
Figure #2.
3.
Fill reservoir to normal level with clean oil per MIL-PRF-5606.
4.
Place suitable clean catch container below both the UP and DOWN port
fittings/shipping caps.
5.
Remove DOWN port fitting/shipping cap to insure complete venting of the
DOWN hydraulic circuit. If steady flow is subsequently noted from the DOWN
port and reservoir fluid level decreases, skip following steps and proceed to
Section 3.B. If steady flow is not observed, re-install DOWN fitting/shipping cap
and proceed with next step.
6.
Remove UP port fitting/shipping cap and allow reservoir to drain – this should
result in free flow and deplete the reservoir for a correctly configured pilot piston
and spring.
NOTE: IF THERE IS NO FREE FLOW OF FLUID FROM EITHER THE UP OR
DOWN PORT, THE UNIT MUST BE RETURNED FOR REPAIR.
7.
Replace UP port fitting/shipping cap.
8.
Install new Boss Packing PN MS28778-4 (Item #205) on Air Vent and Fill Port
Plug PN 1FA1305935 (Item #55) and install in Housing Assembly (Item #5) and
tighten to 36 – 44 in-lbs (4.06 – 4.97 Nm).
9.
After verification of correct installation of the piston and spring as evidenced by
free flow from the UP port, re-identify by permanently scribing, stamping, or
laser marking “C” in the “MODS INCORP” marking area of the Hydraulic
Reversible Pump name plate (Refer to Figure 1).
10. If Hydraulic Reversible Pump does not free flow from the UP port, remove and reinstall Piston and Spring in correct orientation as described in section 3.B. below.
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SERVICE BULLETIN
B.
PISTON AND SPRING RE-INSTALLATION IN CORRECT
ORIENTATION
REFER TO FIGURE #3 FOR THE FOLLOWING STEPS
1.
Remove two Plug Assemblies PN 1FA1305958 (Item #265) from both
ends of the Pilot Check Valve bore in the Housing (Item #5).
CAUTION: DEBRIS MAY BE PRESENT IN THE UP AND DOWN PORTS.
ENSURE PORTS ARE THOROUGHLY CLEANED PRIOR TO
PROCEEDING TO STEP 2.
2.
Remove two Caps PN 1FA1305930 (Item #40), using a #4-40 UNC-3B
threaded screw, two Packings PN M83461/1-014 (Item#170), two
Check Valves PN 1FA1305981 (Item #70), two Packings PN
M83461/1-012 (Item #165), two Pilot Check Valve Washers PN
1FA1305982 (Item #50), Pilot Check Valve Piston PN 1FA1305971
(Item #285) and Pilot Check Valve Spring PN 1FA1305956 (Item
#255).
CAUTION: ONE SIDE OF WASHER (ITEM #50) IS A SEALING SURFACE
WITH PACKING (ITEM #165) AND HAS A FINER SURFACE
FINISH; USE CAUTION TO PREVENT DAMAGE TO THIS
SEALING SURFACE.
3.
Remove one Pilot Piston Seal PN 1FA1305952 (Item #115) from bore
of Housing (Item #5) and discard.
REFER TO FIGURE #4 FOR THE FOLLOWING STEPS
CAUTION: USE CAUTION TO PREVENT PACKING AND SEAL DAMAGE
DURING ASSEMBLY. LIGHTLY LUBRICATE PACKINGS WITH
MIL-PRF-5606 OR MIL-PRF-83282 HYDRAULIC FLUID PRIOR
TO ASSEMBLY
4.
Lubricate and install new Pilot Piston Seal PN 1FA1305952 (Item
#115) and install into Housing (Item #5).
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1FA13059-32-0001
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SERVICE BULLETIN
REFER TO FIGURES #3 AND #4 FOR THE FOLLOWING STEPS
5.
From the “UP” port side of the Housing (Item #5), install one Pilot
Check Valve Washer PN 1FA1305982 (Item #50), one Packing PN
M83461/1-012 (Item #165), and Check Valve PN 1FA1305981 (Item
#70). Be sure to install both Check Valves (70) as shown in Figure 3
with the chamfered end toward the inside.
CAUTION: ONE SIDE OF WASHER (ITEM #50) IS A SEALING SURFACE
WITH PACKING (ITEM #165) AND HAS A FINER SURFACE
FINISH; THIS SURFACE MUST BE ASSEMBLED FACING THE
PACKING (ITEM #165) AND CHECK VALVE (ITEM #70). USE
CAUTION TO PREVENT DAMAGE TO THIS SEALING
SURFACE.
6.
Lubricate the new Packing PN M83461/1-014 (Item #170) and install
into Housing (Item#5) as shown in Figure 4.
7.
Install Cap PN 1FA1305930 (Item #40), and Plug Assembly PN
1FA1305958 (Item #265).
8.
Tighten the Plug Assembly PN 1FA1305958 to 27 – 33 in-lbs (3.05 –
3.72 Nm).
CAUTION: DO NOT OVERTORQUE PLUG OR DAMAGE MAY OCCUR TO
WASHER
9.
From the DOWN port side of the Housing (Item #5), install Pilot Check
Valve Piston PN 1FA1305971 (Item #285) with machined spring seat
facing away from the UP port (Refer to Figure 3), Pilot Check Valve
Spring PN 1FA1305956 (Item #255), Pilot Check Valve Washer PN
1FA1305982 (Item #50), Packing PN M83461/1-012 (Item #165),
Check Valve P/N 1FA1305981 (Item #70).
CAUTION: ONE SIDE OF WASHER (ITEM #50) IS A SEALING SURFACE
WITH PACKING (ITEM #165) AND HAS A FINER SURFACE
FINISH; THIS SURFACE MUST BE ASSEMBLED FACING THE
PACKING (ITEM #165) AND CHECK VALVE (ITEM #70). USE
CAUTION TO PREVENT DAMAGE TO THIS SEALING
SURFACE.
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SERVICE BULLETIN
10.
Lubricate the new Packing PN M83461/1-014 (Item #170) and install
into housing (Item #5) as shown in Figure 4.
11.
Install Cap PN 1FA1305930 (Item #40), and Plug Assembly PN
1FA1305958 (Item #265).
12.
Tighten the Plug Assembly PN 1FA1305958 to 27 – 33 in-lbs (3.05 –
3.72 Nm).
CAUTION: DO NOT OVERTORQUE PLUG OR DAMAGE MAY OCCUR TO
WASHER
13.
Accomplish bench check test procedure shown in Section 3.A. above.
14.
Power Pack Functional Bench Check (Refer to Figure 2):
Equipment Required:
- 28 VDC, 50 amp minimum power supply
- High pressure caps/plugs for “UP” and DOWN” fittings/ports
- Appropriate wrenches
- 0-2000 psig pressure gage
a.
Gear “UP” Test:
1. Fill the reservoir fluid to normal level
2. Attach tubing and gage to “UP” and “DOWN” port outlet fittings.
Cap off or valve off the end of the line.
3. With power supply OFF, connect the motor to the power supply:
RED to Positive (+), BLACK to Negative (-).
4. Turn the power supply ON.
5. Pump will energize and pressurize the manifold. Turn power
supply OFF when pressure on the gage is above 1100 psig.
Note pressure on the gage.
6. Keep the outlet pressure on the gage above 1100 psig for 2
minutes by turning the power supply ON as necessary. Check
for any external leakage at the Plug Assemblies (Items #265).
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SERVICE BULLETIN
7. Turn the power supply OFF.
8. Disconnect the wiring to the pump.
9. Crack the high pressure fitting on the “UP” outlet port to relieve
the pressure in the system. Note: A very small amount of fluid
will be necessary to relieve the pressure. If the cap is completely
removed, the fluid from the reservoir will drain out.
b.
Gear “DOWN” Test:
1. Fill the reservoir fluid to normal level.
2. Attach tubing and gage to “UP” and “DOWN” port outlet fittings.
Cap off or valve off the end of the line.
3. With power supply OFF, connect the motor to the power supply
WHITE to Positive (+), BLACK to Negative (-).
4. Turn the power supply ON.
5. Pump will energize and pressurize the manifold. Note pressure
on the gage.
6. Keep the outlet pressure on the gage above 1100 psig for 2
minutes by turning the power supply ON as necessary. Check
for any external leakage at the Plug Assemblies (Items #265).
7. Turn the power supply OFF.
8. Disconnect the wiring to the pump.
9. Crack the high pressure fitting on the “DOWN” outlet port to
relieve the pressure in the system. Note: A very small amount of
fluid will be necessary to relieve the pressure. If the cap is
completely removed, the fluid from the reservoir will not drain
out.
15.
After the unit has passed TEST and final inspection, partially fill the unit
(approximately 50%) with Hydraulic Fluid per MIL-PRF-5606 or MILPRF-83282 fluid.
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SERVICE BULLETIN
16.
After correct installation of the piston and spring and test verification,
re-identify by permanently scribing, stamping, or laser marking “C” in
the “MODS INCORP” marking area of the Hydraulic Reversible Pump
name plate (Refer to Figure 1).
Figure 1
PUMP ASSY, HYDRAULIC
1500 PSI MIL - H - 5606 RED OIL
PIPER PN 102559 - ____ REV ___
TRIUMPH PN 1FA13059 - _______
SN FAH ________ DATE ________
MODS INCORP C
Triumph logo in this area
Mark “C” here
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SERVICE BULLETIN
Figure 2
Air vent and filler
plug (55) port and
Boss packing (205)
Pressure
Switches
Housing (5)
DOWN port side
ID marking
DOWN port fitting
UP port side
ID marking
UP port fitting
Issue December 16, 2011
Pilot Check Valve Port
(this passage extends
completely through the
housing (5) and is
plugged at each end)
Refer to CMM IPL
Figure 1 for item
numbers
1FA13059-32-0001
Page 12 of 14
SERVICE BULLETIN
Figure 3
265
40
170
70
NOTE: Machined
spring seat MUST
be at this end. Do
not reverse during
installation.
165
50
255
285
115
DOWN side
Housing (5)
UP side
DOWN port
UP port
50
165
70
170
40
265
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SERVICE BULLETIN
Figure 4
Pilot Check Valve port
Housing (5)
Packing (170)
Packing (170)
Pilot Piston Seal (115)
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1FA13059-32-0001
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