service information letter sil671a · sparks booster technology. installation of a continental...

CATEGORY 5

SIL671A Supersedes SIL671

TECHNICAL PORTIONS

FAA APPROVED

CONTINENTAL MOTORS® IGNITION SYSTEMS

SERVICE INFORMATION LETTERContains Useful Information Pertaining To Your Aircraft Ignition System

SUBJECT: Aircraft Supplemental Type Certificate (STC) Installation Instructions for Shower-of-Sparks Starting Vibrator Booster Systems

PURPOSE: To provide installation instructions for CMI Starting Vibrators in support of AML-STC SA04424AT.

COMPLIANCE: At time of Starting Vibrator installation per AML-STC SA04424AT

MODELSAFFECTED: Aircraft as listed in AML-STC SA04424AT, (see Table 4 on page 13)

I. GENERAL INFORMATION

Since the 1940s, most aircraft utilizing four and six cylinder engines have included one of two systems to assist magneto ignition during engine start; either an impulse coupling or Shower-of-Sparks booster technology.

Installation of a Continental Motors (CMI) Starting Vibrator (with associated wiring and magnetos), provides improved “Shower-of-Sparks” starting performance and eliminates required periodic inspections for worn impulse couplings (per AD 2005-12-06 and AD 99-04-04).

A. Impulse Coupling

An impulse coupling is a mechanical device integral to the magneto and attached to the magneto shaft. During cranking, the impulse coupling stores energy in a spring and releases that energy suddenly at a retarded timing position near Top Dead Center (TDC). Thus, each magneto fitted with an impulse coupling delivers a single high-energy spark at each ignition event until engine start. Impulse couplings also incorporate moving parts that are subject to wear.

B. Shower-of-Sparks

Shower-of-Sparks technology, pioneered as booster coils and booster magnetos before WWII, was introduced for light aircraft about 1960. Shower-of Sparks functions similarly to impulse couplings (adding energy to the ignition system during starting, automatically retarding timing), but does so electrically instead of mechanically.

Using the familiar twist-to-start or push-to-start rotary ignition and start switch, the pilot rotates the switch full clockwise, to command START. Battery current is then supplied through a solenoid to the starter motor and to the starting vibrator. The starting vibrator uses an electromechanical oscillator to “chop” the battery DC into a pulsating DC, which is connected back to the switch BO (Booster Output) terminal. The switch splits the BO signal and sends it to both, the left magneto’s main (advance or switch) terminal and left retard terminal through parallel connecting wires. Internal to the left magneto, a secondary set of “retard” contacts (adjusted to a proscribed retard timing) is mounted along with the main, or “advance” contacts. During the start sequence, the BO signal is grounded until both (left advance and retard) contacts are open from ground, at approximately TDC. When the retard contacts open, the BO signal flows

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through the magneto's coil primary wire, where it induces high voltage in the coil secondary. The high voltage is then distributed to the spark plugs. Sparks commence at approximately top-dead-center (TDC) and continue at a fixed frequency as the engine rotates until the main contacts close again, approximately 25 crankshaft degrees later. Each of these spark events have more energy than is typical with an impulse-generated spark, and each sequential spark multiplies the opportunity to ignite less-than-optimally vaporized fuel-air charges. A jumper on the switch automatically disables the right magneto during starting. Once the engine starts, the spring-loaded switch returns to the BOTH position, and the starter and starting vibrator are disconnected from electric power, with both magnetos fire at advance timing.

For optimal performance, starting vibrators are available for 12V or 24V electrical systems, and are tuned for use with S-200 or S-1200 series magnetos. See Table 1 for applicable part numbers.

For most single engine AML aircraft originally equipped with impulse magneto systems, Shower-of-Sparks installation involves:

• Removal of impulse magneto(s) and installation of magneto with retard contacts at engine left magneto position. A “straight drive” or “plain” magneto must be –and often already is– installed at the engine right magneto position.

• Installation of starting vibrator.

• Installation of three connecting wires:

• Power to Vibrator IN terminal, with fuse

• Vibrator BO terminal to switch BO terminal

• Switch Left Retard (LR) terminal to Left Magneto Retard terminal

• Installation of jumper between switch R and adjacent-to the R terminal.

CMI Starting Vibrators installed per AML-STC SA04424AT are designed to be used only with CMI magnetos, and can replace SlickStart™ units in approved aircraft used in conjunction with Continental/Bendix magnetos.

Twin engine Shower-of-Sparks installation is also possible using a single starting vibrator to start both engines.

Table 1. Starting Vibrator Parameters

AML-STC KitPart Number (P/N)

Starting Vibrator Part Number (P/N)

Nominal System Voltage

Nominal Current Draw

For use with Continental Magneto Series

10-400395-1 10-176487-121 12 2.5A S-200

10-400395-2 10-176487-122 12 2A S-1200

10-400395-3 10-357487-241 24 2.5A S-200

10-400395-4 10-357487-242 24 2A S-1200

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II. INSTALLATION INSTRUCTIONS

CAUTION: It is the responsibility of the installer to determine the compatibility of other supplier's STC products when installed in conjunction with STC approved CMI products.

CMI authorizes the installer to use AML-STC SA04424AT (see Figure 8) and detailed instructions contained in this document to accomplish the installation of the products described within AML-STC SA04424AT.

This Service Information Letter provides step-by-step instructions for converting aircraft listed in AML-STC SA04424AT to the Continental Shower-of-Sparks system. The instructions are written to install Shower-of-Sparks in aircraft equipped with rotary action combined ignition/starter switches, or pushbutton 4PST start switches and separate magneto switch(es) along with a dedicated starter solenoid.

In conjunction with installation of CMI Shower-of-Sparks starting vibrator kit in the aircraft, the engine(s) must also be retrofitted to the CMI Shower-of-Sparks magneto configuration. See the latest revision of CMI Ignition Application Data, X44001, for a list of engine models and applicable PMA eligible CMI S-200 and S-1200 series magnetos and matching harnesses.

A. Parts Required

Each Shower-of-Sparks Starting Vibrator AML-STC kit, (P/N 10-400395-X), includes electrical hardware needed to complete the installation and are approved for use in all aircraft listed in AML-STC SA04424AT.

Shower-of-Sparks Starting Vibrators must be installed with matching CMI S-200 or S-1200 series retard breaker magnetos and matched to the aircraft voltage as detailed in Table 1. If CMI Shower-of-Sparks Starting Vibrator is installed with retard breaker magnetos, any SlickStart™ Booster must be removed from the aircraft.

B. Weight Change

12V vibrators weigh approximately 0.7 pound, installed. Installed weight of a 24V vibrator is approximately 1 pound.

Table 2. Kit, Shower-of-Sparks Starting Vibrator, (P/N 10-400395-X)

Quantity(each)

ContinentalPart Number Description

1 see Table 1 starting vibrator

1 10-400687 5A fuse

1 10-400689 fuse holder

2 10-400039 ring terminals, #10

10 10-620013 cable ties

1 10-400577 tefzel wire, 18ga (18’ long)

1 10-126656 switch jumper

3 10-400685 ring terminals, #6

3 10-400683 splices

1 10-126648 screws, 6-32 x 25

8 6547742-3-1.00 shrink tubing

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C. Required Reference Materials

Refer to the following publications for instructions on installation, continued airworthiness, maintenance and overhaul, and parts catalogs:

• X43003 Starting Vibrator Assemblies Service Support Manual• X42002 S-20/S-200 Series Magnetos Service Support Manual• X42001 S-1200 Series Magnetos Service Support Manual• X43002 Ignition/Starter Switches Service Support Manual

D. Detailed Instructions

1. Disconnect aircraft battery and ignition harness:

a. Disconnect and secure the negative lead away from the aircraft battery to prevent inadvertent contact.

b. Disconnect the ignition harness from the spark plugs to prevent accidental magneto firing and uncommanded engine rotation.

2. If removing SlickStart™ booster unit:

a. Wiring that is extraneous and unused must be capped or removed. The SlickStart booster uses a different wiring arrangement than CMI AML-STC SA04424AT.

b. Unbolt and remove the SlickStart booster unit. CMI starting vibrators mounting hole diameters and spacing are identical to SlickStart™ booster units.

WARNING

Normal precautions must be taken to prevent accidental engine operation. The magneto is “on” when the ignition switch wire (p-lead) is detached from the magneto.

3. Install CMI Shower-of-Sparks starting vibrator:

a. Select a suitable location to mount the CMI starting vibrator:

• Ensure the mounting bracket will not interfere with or affect the aircraft structure. Minor rerouting or relocating of accessories may be required.

• Mount the starting vibrator and wiring away from heat sources, clear of exhaust, engine control linkages, any other systems critical to the airworthiness of the aircraft, sources of weathering, corrosion and abrasion. Ensure the risk of mechanical damage and/or damage caused by fluids, vapors, or sources of heat, is minimized.

• Ensure adequate provisions for ventilation, drainage and accessibility for maintenance, inspection or other servicing as required.

• Ensure protection from fuel, oil, water, other detrimental substances, and mechanical damage.

b. Mount CMI starting vibrator in vertical orientation (as shown in Figure 1) to ensure best drainage. It may be mounted in any orientation. The two mounting holes will accommodate 3/16” (No. 10) fasteners.

NOTE: If mounted with the cover underneath the plate (reverse orientation), remove the cover and drill one-to-three 0.12”±0.03 holes into the plastic cover (spaced no closer than 0.25” apart from each other at the lowest area) to ensure drainage. Snap the cover back into place.

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Figure 1. Starting Vibrator, typical mounting orientation

Figure 2. Rotary Action Combined Ignition/Start Switch

4. Connect Continental Starting Vibrator (when converting from Impulse Coupled magneto(s), or SlickStart, to Continental retard breaker magneto & Shower-of Sparks) according to the following steps:

Table 3. Connecting Starting Vibrator

For Installation of... using... ... go to Section II,

step D.4., paragraph

Single Enginerotary ignition/start switch a.

push button start switch and separate magneto switch(es)

b.

Twin Enginepush button start switch and separate magneto switch(es)

c.

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Figure 3. Rotary Ignition/Start Switch and Starting Vibrator Connections(for starting vibrator in engine compartment)

a. Single Engine – To convert from Impulse Coupled magneto(s) to retard breaker magneto or to replace SlickStart™ Booster unit, the engine will be started with only the left magneto using a rotary action combined ignition/start switch (see Figure 2)

1) Connect the Starting Vibrator terminal marked IN to the switched output terminal of the starter solenoid. Electric power will only be applied to the Starting Vibrator when the starter motor is energized. Use the fuse, fuse holder, splice connectors, 3/16” spade terminal, 5/16” ring terminal, cable ties, 18ga wire, and shrink tubing supplied in the Starting Vibrator kit, (P/N 10-400395-X, reference Table 2).

2) Connect the terminal marked BO on the vibrator to the terminal marked BO on the switch using a 3/16” spade terminal, 18ga wire, No. 6 ring terminal, and 6-32 x 0.25 switch terminal screw. Torque the switch terminal screw 8-12 inch pounds.

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Figure 4. Rotary Ignition/Start Switch and Starting Vibrator Connections(for starting vibrator in cabin)

NOTE: Optional wiring per Figure 4 may be used if fuse/circuit protection for starter solenoid is adequate to also carry vibrator current, (see Table 1).

3) Connect the terminal marked LR on the switch to the terminal marked RETARD on the left magneto using 18ga wire, No. 6 ring terminal, 6-32 x 0.25 switch terminal screw, and #10 ring terminal. Torque the switch terminal screw, 8-12 inch pounds. Torque to magneto RETARD terminal nut 15-17 inch pounds.

4) Connect the two switch R terminals (see Figure 2) using a jumper and two 6-32 x 0.25 switch terminal screws. Torque the two switch terminal screws, 8-12 inch pounds.

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Figure 5. Single Engine Push Button Start and Starting Vibrator Connections(for starting vibrator in engine compartment)

b. Single Engine (optimum when installing vibrator in engine compartment) – To convert from Impulse Coupled magneto(s) to retard breaker magneto or replace SlickStart™ Booster unit, the engine will be started with only the left magneto using push button start switch and separate magneto switch(es) (see Figure 5)

1) Connect the starting vibrator terminal marked IN to the switched output terminal of the starter solenoid. Electric power will only be applied to the starting vibrator when the starter motor is energized. Use fuse, fuse holder, crimp splice connectors, 3/16” spade terminal, 5/16” ring terminal, cable ties, 18ga wire, and shrink tubing supplied in the kit.

2) Connect the vibrator BO terminal to the adjacent C terminals on the 9910079-1 (Cessna) start switch. Use a 3/16” spade terminal and 18ga wire.

3) Connect one NO switch terminal to left magneto RETARD terminal (as shown in Figure 5). Use 18ga wire, and #10 ring terminal. Torque the RETARD nut 15-17 inch pounds.

4) Connect the next NO switch terminal to left magneto SWITCH terminal, or to the 'hot' side of the left magneto control switch. Use 18ga wire. If connecting direct to the mag-neto, use #10 ring terminal at the magneto. Torque the capacitor stud to 15-17 inch pounds. If connecting to the magneto control switch, use the terminal and torque appro-priate to that switch.

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Figure 6. Single Engine Push Button Start and Starting Vibrator Connections(for starting vibrator in cabin)

NOTE: Optional wiring per Figure 6 may be used if fuse/circuit protection for starter solenoid is adequate to also carry vibrator current, (see Table 1).

5) Connect the C terminal on the 9910079-1 (Cessna) start switch to airframe ground. Use 18ga wire.

6) Connect corresponding NO switch terminal to right magneto SWITCH terminal, or to the 'hot' side of the right magneto control switch (as shown in Figure 5 & 6). Use 18ga wire. If connecting direct to the magneto, use #10 ring terminal at the magneto. Torque the capacitor stud to 15-17 inch pounds. If connecting to the magneto control switch, use terminal and torque appropriate to that switch.

7) Connect the remaining C terminal to airframe bus through a circuit breaker or fuse appropriate to protect the solenoid control circuit. Connect the remaining NO terminal to the starter solenoid. Use 18ga wire, appropriate terminals and torques.

8) Ensure start switch is clearly labeled “START”.

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Figure 7. Twin Engine Push Button Start and Starting Vibrator Connections

c. Twin Engine – To convert from Impulse Coupled magneto(s) to retard breaker magneto or replace SlickStart™ Booster unit, the engines will be started with only the left magneto using push button start switch and separate magneto switch(es). One vibrator will provide boost energy to both engines (see Figure 7).

1) Connect the starting vibrator terminal marked IN to the aircraft main bus through the 5A fuse. Electric power will be applied to the starting vibrator when the master switch is on; vibrator boost action will only occur when the circuit is completed through the start switch and left magneto. Use the fuse, fuse holder, splice connectors, 3/16” spade termi-nal, 5/16” ring terminal, cable ties, 18ga wire, and shrink tubing supplied in the kit.

2) Connect the vibrator BO terminal two adjacent C terminals on the 9910079-1 (Cessna) switch. Use a 3/16” spade terminal, 18ga wire.

3) Connect one NO switch terminal to left magneto RETARD terminal (reference Figure 7). Use 18ga wire, and #10 ring terminal. Torque the RETARD nut to 15-17 inch pounds.

4) Connect the next NO switch terminal to left magneto SWITCH terminal, or to the 'hot' side of the left magneto control switch. Use 18ga wire. If connecting direct to the magneto, use #10 ring terminal at the magneto. Torque the capacitor stud to 15-17 inch pounds. If connecting to the magneto control switch, use terminal and torque appropri-ate to that switch.

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5) Connect C terminal on the 9910079-1 (Cessna) switch to airframe ground (as shown in Figure 7). Use 18ga wire, appropriate terminals and torques.

6) Connect corresponding NO switch terminal to right magneto SWITCH terminal, or to the 'hot' side of the left magneto control switch (as shown in Figure 7). Use 18ga wire. If connecting direct to the magneto, use #10 ring terminal at the magneto. Torque the capacitor stud to 15-17 inch pounds. If connecting to the magneto control switch, use terminal and torque appropriate to that switch.

7) Connect the remaining C terminal to airframe bus through a circuit breaker or fuse appropriate to protect the solenoid control circuit. Connect the remaining NO terminal to the starter solenoid. Use 18ga wire, appropriate terminals and torques.

8) For the second engine, repeat steps 2 through 7.

9) Ensure start switch is clearly labeled “START” and “LEFT ENGINE” and “RIGHT ENGINE” as applicable.

5. Check starting vibrator installation.

a. Inspect all wiring connections for proper termination.

b. Check all wiring for proper routing away from heat generating sources, mechanical stresses and abrasion.

c. Check for removal of all installation tools and debris.

6. Reconnect the ignition harness to the spark plugs.

7. Reconnect aircraft battery.

a. Confirm that aircraft ignition and master switches are in the OFF position

b. Reconnect the negative lead of the aircraft electrical system to the negative battery terminal.

8. Create all appropriate logbook entries (CMI starting vibrator installation is approved by AML-STC SA04424AT).

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Figure 8. AML-STC SA04424AT, reprographic

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Table 4. FAA Approved Model List (AML) No. SA04424AT Installation of CMI Shower-of-Sparks Starting Vibrator Booster Systems

Item MakeModel/ Series

Cert Basis/Amendment/

CategoryTCDS

NoMDL/ Inst

DWG FMS ICA MFG P/N

Model Specific Notes

Initial Approve

DateAmended

Date

1

Aircraft Parts &

Development Corp.

A-9A-9B

CAR 8/None/

Restricted

A-758 Rev 23

10-400395 Rev A,

Dated 9/26/2017 or

Latest FAA Approved Revision

N/A

X43003, Rev 3,

dated 5/31/2018 or the

latest FAA approved revision

A-9 12V: 10-176487-121

A-9 24V: 10-357487-241

A-9B 12V: 10-176487-122

A-9B 24V: 10-357487-242

N/A 6/4/18 N/A

2

Aircraft Parts &

Development Corp.

A-9A

CAR 3 effective 5/15/

56, with amendments 3-1 through 3-

7 / Normal

A4WERev 6

10-400395 Rev A,

Dated 9/26/2017 or


N/A

X43003, Rev 3,



A-9A 12V: 10-176487-121

A-9A 24V: 10-357487-241

N/A 6/4/18 N/A

3 B-N Group LTD

BN-2BN-2A

BN-2A-6BN-2A-8BN-2A-2BN-2A-9BN-2A-3BN-2A-20BN-2A-21BN-2A-26BN-2A-27BN-2B-20BN-2B-21BN-2B-26BN-2B-27

14 CFR Part 23, effective February 1,

1965 including amendment 23-1 /Normal

A17EURev 18

10-400395 Rev A,

Dated 9/26/2017 or


N/A

X43003, Rev 3,



12V: 10-176487-122

24V: 10-357487-242

N/A 6/4/18 N/A

4 B-N Group LTD

BN-2A MK. III

BN-2A MK. III-2

BN-2A MK. III-3

14 CFR Part 23 effective February 1,

1965 as amended by amendments 23-1 through

23-9 inclusive /Normal

A29EU Rev 5

10-400395 Rev A,

Dated 9/26/2017 or


N/A

X43003, Rev 3,



12V: 10-176487-122

24V: 10-357487-242

N/A 6/4/18 N/A

5Textron

Aviation Inc. (Cessna)

182S, 182T,T182T

14 CFR Part 23 … as

amended … through 23-6,

except as follows:

FAR23.611 as amended by Amendment 23-7. FAR 23.1301 as amended by Amendment

23-20. 23.1357 as amended by Amendment

23-43 /Normal

3A13Rev 72

10-400395 Rev A,

Dated 9/26/2017 or


N/A

X43003, Rev 3,



182S, 182T: 10-357487-241

T182T: 10-357487-242

N/A 6/4/18 N/A

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6Textron

Aviation Inc. (Cessna)

206H, T206H

14 CFR Part 23 … as

amended … through 23-6,

except as follows:

FAR 23.611 as amended by Amendment 23-7. FAR 23.607…

as amended by

Amendment 23-17. FAR 23.1301 as amended by Amendment

23-20. FAR 23.1357 as amended

by Amendment

23-43 /Normal

A4CERev 49

10-400395 Rev A,

Dated 9/26/2017 or


N/A

X43003, Rev 3,



206H: 10-357487-241

T206H: 10-357487-242

N/A 6/4/18 N/A

7Commander

AircraftCorporation

114B, 114TC

14 CFR Part 23/ through amendment 23-7 /Normal

A12SORev 23

10-400395 Rev A,

Dated 9/26/2017 or


N/A

X43003, Rev 3,



114B 12V: 10-176487-121

114B 24V: 10-357487-241

114TC 24V: 10-357487-242

N/A 6/4/18 N/A

8

Extra Flugzeugproduktions und

Vertreibs GmbH

EA 300, EA 300/S,EA 300/L,EA 300/LC

14 CFR Part 23/ through amendment

23-34 /Acrobatic,

Normal

A67EURev 12

10-400395 Rev A,

Dated 9/26/2017 or


N/A

X43003, Rev 3,



12V: 10-176487-121

24V: 10-357487-241

N/A 6/4/18 N/A

9Diamond Aircraft

Industries GmbH

DA 40

14 CFR Part 23 effective February 1,

1965, including

Amendments 23-1 through Amendment

23-51 /Normal and Utility

A47CE Rev 15

10-400395 Rev A,

Dated 9/26/2017 or


N/A

X43003, Rev 3,



10-357487-241 N/A 6/4/18 N/A




CategoryTCDS

NoMDL/ Inst

DWG FMS ICA MFG P/N


Initial Approve

DateAmended

Date

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10Found

Aircraft, Canada, Inc

FBA-2C,FBA-2C1,FBA-2C2,FBA-2C3,FBA-2C4,

FBA-2C3T,FBA-2C4T

FBA-2C: 14 CFR Part 23 …

as amended … through 23-6

except:FAR 23.611; amended by

amendment 23-7. FAR 23.1529 amended by

amendment 23-26.FAR 23.1351;

23.1357; amended by amendment 23-

43.FBA-2C1:

14 CFR Part 23 … through 23-6

except:FAR 23.611; amended by

amendment 23-7. FAR 23.607; amended by

amendment 23-17.FAR 23.1301 amended by

amendment 23-20.FAR 23.1529 amended by

amendment 23-26.FAR 23.1351; amended by

amendment 23-43.FBA-2C2

The Certification Basis for the model FBA-2C1, except:

FAR 23.1365; amended by

amendment 23-43.FBA-2C3, FBA

2C4, FBA-2C3T, FBA-2C4T

14 CFR Part 23 … through

23-6 except:23.1301,

As amended by Amendment 23-20

23.605As amended by

Amendment 23-2323.1529

As amended by Amendment 23-26

23.1357, As amended by

Amendment 23-4323.607, 23.611, As amended by

Amendment 23-4823.1351 As amended by

Amendment 23-49 /Normal

A7EARev 8

10-400395 Rev A,

Dated 9/26/2017 or


N/A

X43003, Rev 3,



12V, S-200: 10-176487-12112V, S-1200:

10-176487-12224V, S-200:

10-357487-24124V, S-1200:

10-357487-242

N/A 6/4/18 N/A

11 GA8 AirvanGA8,

GA8-TC 320

GA8:14 CFR Part 23 … through

23-54 GA8TC320

FAR 23, dated December 18, 1964…through 23-55 /Normal

A00011LA

Rev 10

10-400395 Rev A,

Dated 9/26/2017 or


N/A

X43003, Rev 3,



12V: 10-176487-122

24V:10-357487-242

N/A 6/4/18 N/A




CategoryTCDS

NoMDL/ Inst

DWG FMS ICA MFG P/N


Initial Approve

DateAmended

Date

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12 GA200 GA200 GA200C

14 CFR Part 23 … through

23-36 Except: 23.562

(see letter dated April 5, 1995, from Manager,

LAACO) for the special purpose of:

(1) Agricultural operations under FAR

21.25 (b)(1)./Restricted

A00001LA

Rev 3

10-400395 Rev A,

Dated 9/26/2017 or


N/A

SX43003, Rev 3,



12V, S-200: 10-176487-12112V, S-1200:

10-176487-12224V, S-200:

10-357487-24124V, S-1200:

10-357487-242

N/A 6/4/18 N/A

13 Helio H-250

CAR 3/ as amended to

May 16, 1953 /Normal

1A8Rev 37

10-400395 Rev A,

Dated 9/26/2017 or


N/A

X43003, Rev 3,



12V: 10-176487-121

24V:10-357487-241

N/A 6/4/18 N/A

14 Helio 500

CAR 3, dated May 15, 1956,

plus Amendments 1-3 through 3-

5 /Normal

A2EARev 10

10-400395 Rev A,

Dated 9/26/2017 or


N/A

X43003, Rev 3,



12V: 10-176487-121

24V:10-357487-241

N/A 6/4/18 N/A

15Lavia

Argentina S. A.

PA-25-235PA-25-260

CAR 8.10(b), effective

October 11, 1950.

/Restricted

2A10Rev 28

10-400395 Rev A,

Dated 9/26/2017 or


N/A

X43003, Rev 3,



12V, S-200: 10-176487-12112V, S-1200:

10-176487-12224V, S-200:

10-357487-24124V, S-1200:

10-357487-242

N/A 6/4/18 N/A

16Lavia

Argentina S. A.

PA-25-235PA-25-260

CAR 3 effective May

15, 1956, Amendment 3-

1, April 1, 1957.

/Normal

2A8Rev 22

10-400395 Rev A,

Dated 9/26/2017 or


N/A

X43003, Rev 3,



12V, S-200: 10-176487-12112V, S-1200:

10-176487-12224V, S-200:

10-357487-24124V, S-1200:

10-357487-242

N/A 6/4/18 N/A

17

Maule Aerospace

Technology, Inc.

M-5-235CM-6-235M-7-235

M-7-235AM-7-235BM-7-235CM-7-260

M-7-260CMT-7-235MT-7-260MX-7-235M-8-235M-9-235

Part 3, Civil Air Regulations, effective May 15, 1956 as

amended by 3-1 thru 3-5 and

3.705 as amended by 3-

7 /Normal

3A23Rev 32

10-400395 Rev A,

Dated 9/26/2017 or


N/A

X43003, Rev 3,



12V: 10-176487-121

24V:10-357487-241

N/A 6/4/18 N/A




CategoryTCDS

NoMDL/ Inst

DWG FMS ICA MFG P/N


Initial Approve

DateAmended

Date

ISSUED REVISED

P.O. Box 90 Mobile, AL 251-436-8299


2018/05/31 2019/03/25 16 of 20 SIL671 A

18Mooney

International Corporation

M20M

CAR 3 effective

November 1, 1949, as

amended to May 18, 1954,

… 3.74 as amended to August 25,

1955; …3.109, 3.112, 3.115, 3.118, 3.120, and 3.441 of

CAR 3 effective May 15, 1956, as amended to October 1,

1959. In lieu of corresponding

CAR 3 paragraphs,

where applicable -

FAR 23, effective

February 1, 1965; 23.1351 as amended to September 14, 1969 /Normal

2A3Rev 57

10-400395 Rev A,

Dated 9/26/2017 or


N/A

X43003, Rev 3,



10-357487-242 N/A 6/4/18 N/A

19 Piper PA-28-235

CAR 3 effective May

15, 1956, … 3-2; … 3.304

and 3.705 of Amendment 3-

7 effective May 3, 1962 /

Normal

2A13 Rev 57

10-400395 Rev A,

Dated 9/26/2017 or


N/A

X43003, Rev 3,



12V: 10-176487-121

24V:10-357487-241

N/A 6/4/18 N/A




CategoryTCDS

NoMDL/ Inst

DWG FMS ICA MFG P/N


Initial Approve

DateAmended

Date

ISSUED REVISED

P.O. Box 90 Mobile, AL 251-436-8299


2018/05/31 2019/03/25 17 of 20 SIL671 A

20 Piper

PA-32-260PA-32-300PA-32S-

300PA-32R-

301PA-32-301PA-32R-

301TPA-32-301FT

PA-32R-301FTPA-32-301XTC

PA-32-260,PA-32S-300,PA-32-300, PA-32R-301PA-32-301

PA-32R-301TCAR 3,

effective May 15, 1956, through

Amendment 3-8, effective

December 18, 1962.

PA-32-301FT, PA-32-301XTCCAR 3,

effective May 15, 1956, through

Amendment 3-8, effective

December 18, 1962. FAR 23.1529 as amended by Amendment

23-26, effective

October 14, 1980; /Normal

A3SORev 33

10-400395 Rev A,

Dated 9/26/2017 or


N/A

X43003, Rev 3,



12V, S-200: 10-176487-12112V, S-1200:

10-176487-12224V, S-200:

10-357487-24124V, S-1200:

10-357487-242

N/A 6/4/18 N/A

21 Piper PA-36-300

14 CFR Part 23 including Amendments 23-1 through 23-6 dated August 1,

1967 /Normal

A9SO Rev 10

10-400395 Rev A,

Dated 9/26/2017 or


N/A

X43003, Rev 3,



12V: 10-176487-122

24V:10-357487-242

N/A 6/4/18 N/A

22 Piper PA-36-300

14 CFR Part 23 including Amendments 23-1 through 23-6 dated August 1, 1967, with

exception to FAR 23 per

FAR 21.25(a)(1)./ Restricted

A10SORev 13

10-400395 Rev A,

Dated 9/26/2017 or


N/A

X43003, Rev 3,



12V: 10-176487-122

24V:10-357487-242

N/A 6/4/18 N/A




CategoryTCDS

NoMDL/ Inst

DWG FMS ICA MFG P/N


Initial Approve

DateAmended

Date

ISSUED REVISED

P.O. Box 90 Mobile, AL 251-436-8299


2018/05/31 2019/03/25 18 of 20 SIL671 A

23The King’s

Engineering Fellowship

44

14 CFR Part 23/ through amendment

23-36 /Normal

A2WIRev 3

10-400395 Rev A,

Dated 9/26/2017 or


N/A

X43003, Rev 3,



12V: 10-176487-122

24V:10-357487-242

N/A 6/4/18 N/A

24 Twin Commander 500

CAR 3 as amended May

15, 1956 / Normal

6A1 Rev 48

10-400395 Rev A,

Dated 9/26/2017 or


N/A

X43003, Rev 3,



12V: 10-176487-121

24V:10-357487-241

N/A 6/4/18 N/A




CategoryTCDS

NoMDL/ Inst

DWG FMS ICA MFG P/N


Initial Approve

DateAmended

Date

ISSUED REVISED

P.O. Box 90 Mobile, AL 251-436-8299


2018/05/31 2019/03/25 19 of 20 SIL671 A

Intentionally Left Blank

ISSUED REVISED

P.O. Box 90 Mobile, AL 251-436-8299


2018/05/31 2019/03/25 20 of 20 SIL671 A

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