• ~AlPHA AVIATION 

SERVICE BULLETIN 

AA-SB-79-001 

REPLACEMENT OF OIL PRESSURE TRANSDUCER LINE 

1 Planning Information 

1.1 EFFECTIVITY 

Alpha R2000 Series Aircraft S/N 001 to 378 

Alpha HR200 Series Aircraft, all serial numbers. 

1.2 CONCURRENT REQUIREMENTS 

Nil 

1.3 REASON 

The hose that connects the oil pressure transducer to the engine has been found to be not fire 

resistant. 

1.4 DESCRIPTION 

This service bulletin provides instructions for replacement of the oil pressure transducer hose and 

associated interface fitting at the engine end of the hose. 

1.5 COMPLIANCE 

Within the next 50 flying hours or by 30th April 2012, whichever occurs first. 

1.6 APPROVAl 

By delegated authority (Alpha Aviation Concept Ltd, 0075990) GOA AA/60/11 05 

1.7 WEIGHT AND BALANCE 

Negligible effect on aircraft weight and balance. 

1.8 REFERENCES 

R2000 and HR200 Illustrated Parts Catalogue 

APEX R2000 Service Manual 

APEX HR200 Service Manual 

1.9 OTHER PUBLICATIONS AFFECTED 

Nil 

----··--·------- ·-·-··--·-··-·-·-··--·-·-·-·-·-··--------·--·--·----·- -·-----·-·-- ··-·-·---·-·-··---··-· DES 16 Ver 1: 1.06.05 Revision 0, Feb 2012 AA·SB-79·001 

Page 1 of 4 
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DiAlPHA AVIATION 

SERVICE BULLETIN 

2 Material Information 

2.1 MATERIALS IDENTIFICATION 

Part Number ! Descri~tion I 

124J003-3CR·0144 I 

I Hose Assembly 

60·28-121·001 i 

I Restrictor fitting 

AN816-30 I Nipple - AN910·1 0 I Coupling I 

I . ----·--·-

These components are available from Alpha Aviation Ltd. 

2.2 OTHER PUBLICATIONS AFFECTED 

Nil 

2.3 SPECIAL TOOLING 

Nil 

3 Accomplishment Instructions 

3.1 At The Engine Oil Pressure Ports: 

I Quantity i 

I 

I 1 i 

I 

I 1 1 

I 

I 1 J I 1 ! 

I 

J 

Figure 3·1 shows the engine oil pressure ports. These are designated Port A and Port B. 

Perform the following operations: 

a) Remove the existing hose from the existing fitting in Port A and then remove and discard the 

existing fitting in Port A. 

b) Remove the plug installed in Port Band install this plug in port A. 

c) Install restrictor fitting part number 60·28-121·001 in port B. Torque tighten to 50-65 in-pound 

(5.6 - 7.3 Nm) 

d) Loose install hose part number 124J003-3CR-0144 onto the restrictor fitting as shown in figure 

3.1. The "straight" fitting end of the hose is attached at this position. 

3.2 At The Oil Pressure Transducer: 

Figure 3-2 shows the oil pressure transducer. This component is mounted on the firewall. 

Perform the following operations: 

a) Remove the existing hose from the transducer port and discard. 

b) Install coupling part number AN910-1 D and nipple part number AN 816-30 onto the transducer 

as shown in figure 3.2. Torque tighten to 50·65 in-pound (5.6 - 7.3 Nm) 

c) Loose install hose part number 124J003-3CR-0144 onto the AN 816-30 nipple as shown in 

figure 3.2. The "45° " fitting end of the hose is attached at this position. 

d) Orient the hose to ensure adequate clearance from the firewall structure and then tighten at 

at both ends of the hose with torque of 50- 65 in-pound (5.6 - 7.3 Nm) 

3.3 Post Installation Actions. 

a) Run the engine and check for freedom from leakage and correct function of the oil pressure 

gauge. Note: Bleeding of the line may be required for correct function. 

b) Certify compliance of this service bulletin in the aircraft log book. 

DES 16 Ver 1: I 06.05 Revision 0, Feb 2012 AA·SB-79-001 

Page 2of 4 
~ 

o<AlPHA AVIATION 

SERVICE BULLETIN 

AA-SB-79-001 

REPLACEMENT OF OIL PRESSURE TRANSDUCER LINE 

1 Planning Information 

1.1 EFFECTIVITY 

Alpha R2000 Series Aircraft S/N 001 to 378 

Alpha HR200 Series Aircraft, all serial numbers. 

1.2 CONCURRENT REQUIREMENTS 

Nil 

1.3 REASON 

The hose that connects the oil pressure transducer to the engine has been found to be not fire 

resistant. 

1.4 DESCRIPTION 

This service bulletin provides instructions for replacement of the oil pressure transducer hose and 

associated interface fitting at the engine end of the hose. 

1.5 COMPLIANCE 

Within the next 50 flying hours or by 30111 April 2012, whichever occurs first. 

1.6 APPROVAL 

By delegated authority (Alpha Aviation Concept Ltd, 0075990) GOA AA/60/11 05 

1.7 WEIGHT AND BALANCE 

Negligible effect on aircraft weight and balance. 

1.8 REFERENCES 

R2000 and HR200 Illustrated Parts Catalogue 

APEX R2000 Service Manual 

APEX HR200 Service Manual 

1.9 OTHER PUBLICATIONS AFFECTED 

Nil 

DES 16 Ver 1: 1.06.05 Revision 0, Feb 2012 AA·SB·79·001 

Page 1 of4 
2 

2.1 

2.2 

2.3 

3 

3.1 

DiAlPHA AVIATION 

SERVICE BULLETIN 

Material Information 

MATERIALS IDENTIFICATION 

Part Number Description 

I 

I 124J003-3CR-0144 Hose Assembly 

I 60-28-121-001 Restrictor fitting 

I AN816-30 Nipple I 

I 

L AN910-10 Coupling 

These components are available from Alpha Aviation Ltd. 

OTHER PUBLICATIONS AFFECTED 

Nil 

SPECIAL TOOLING 

Nil 

Accom~llshment Instructions 

At The Engine Oil Pressure Ports: 

Quantity I 

I 

I 

I 

Figure 3-1 shows the engine oil pressure ports. These are designated Port A and Port B. 

Perform the following operations: 

a) Remove the existing hose from the existing fitting in Port A and then remove and discard the 

existing fitting in Port A. 

b) Remove the plug installed in Port B and install this plug in port A. 

c) Install restrictor fitting part number 60-28-121-001 in port B. Torque tighten to 50-65 in-pound 

(5.6 - 7.3 Nm) 

d) Loose install hose part number 124J003-3CR-0144 onto the restrictor fitting as shown in figure 

3.1. The "straight" fitting end of the hose is attached at this position. 

3.2 At The Oil Pressure Transducer: 

Figure 3-2 shows the oil pressure transducer. This component is mounted on the firewall. 

Perform the following operations: 

a) Remove the existing hose from the transducer port and discard. 

b) Install coupling part number AN91 0-1 D and nipple part number AN 816-30 onto the transducer 

as shown in figure 3.2. Torque tighten 10 50-65 in-pound (5.6- 7.3 Nm) 

c) Loose install hose part number 124J003-3CR-0144 onto the AN 816-30 nipple as shown in 

figure 3.2. The "45 o" fitting end of the hose is attached at this position. 

d) Orient the hose to ensure adequate clearance from the firewall structure and then tighten at 

at both ends of the hose with torque of 50 - 65 in-pound (5.6 - 7.3 Nm) 

3.3 Post Installation Actions. 

a) Run the engine and check for freedom from leakage and correct function of the oil pressure 

gauge. Note: Bleeding of the line may be required for correct function. 

b) Certify compliance of this service bulletin in the aircraft log book. 

DES 16 Ver 1: 1.06.05 Revision 0, Feb 2012 AA SB 79·001 

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D<'ALPHA AVIATION 

SERVICE BULLETIN 

Port B 

Plug removal. (3.1 (b)) 

Restrict or fitting p/n 60-28-121 -001 

installation. (3.1 (c)) Port A 

Fitting removal (3.1 (a)) 

Plug installation. (3.1 (b)) 

Figure 3-2 : Installations at oil pressure transducer 

DES 16 Vor 1: 1.06.05 RevisionO. Feb2012 AA-SB-79 001 
DES 16 Vert : 1.06.05 

< 

O<'AlPHA AVIATION 

SERVICE BULLETIN 

Contact Information: 

~ 

O(ALPHA AVIATION 

59 Hautapu Road 

RD 1 

Cambridge 3493 

NEW ZEALAND 

Phone: + 64 7 827 0528 Fax: + 64 7 929 2878 

Web: www .alphaaviation.co.nz 

Revision 0, Feb 2012 AA-SB· 79-00 1 

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