# •**~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 A i rcraft , all serial numbers. 

### 1.2 CONCURRENT REQUIREMENTS Nil 

### 1.3 REASON The hose that connects the oi l pressure transducer to the engine has been found to be not fire resistant. 

### 1.4 DESCRIPTION This service bul l etin provides instructions for replacement of the oil pressure transducer hose and associated interface fitt i ng at the engine end of the hose . 

### 1.5 COMPLIANCE With i n the next 50 flying hours or by 30th Apr i l 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 Negl ig ible 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

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# DiAlPHA AVIATION 

# SERVICE BULLETIN 2 Material Information 2.1 MATERI ALS IDENTIFICATION Part Number !**Descri~tion** 

## I 124J003-3CR·0144 I I H ose Assembly 60·28-121 · 001 i 

## I Rest ri ctor fitting AN8 16-30 

## I N ipple



## - AN910·1 0 I Coupling I I

. 

### ----·--·- These compo n ents are available from Alpha Aviation Ltd. 

### 2.2 OTHER PUBLICATIONS AFFECTED Nil 

### 2.3 SPECIAL TOOLING Nil 

## 3 Accomplishme nt Instructions 3.1 At The Engine Oil Pressu re Ports : 

# I Quanti ty i 

## I 

# I 1 

### i I 

# I 1 1 

## I I 1 

# J I 1 ! I 

### J

Figure 3·1 shows t he engine oil pressure ports. These are designated Port A and Po rt B. Perform the followi ng operati ons: a) Remove the existing hose from the existing fitt i ng in Port A and then remove an d discard the exist i ng fitting i n Port A. b) Remove the plug installed in Port Band install this plug in port A. c) Install restrictor fitt ing 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 124J003-3C R-0 144 onto the restrictor fitting as shown in fig ure 3.1. The "stra ight" fitting end o f the hose is attached at th i s position. 

### 3.2 A t The Oil Pressure Transducer: Figure 3- 2 shows the oi l pressure transducer. This component is mounted on the f irewall. Perform t h e fo ll owing operat ions: a) Remove the existing hose from the transducer port and discard. b) Install coup ling part number AN9 10- 1D and nipple part number AN 816 -30 onto the tran sducer as shown in figure 3 . 2. Torqu e 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 ) Orien t the hose to ensure adequate clearance from the f i rewall structure and then t i ghten 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 eng i ne and check for freedom from leakage and correct funct i on of the o il pressure gauge . Note: B l eeding of the li ne may be requ i red for correct functi on. b) Certify complian ce of this service bulletin in the a i rcraft l og book.

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age 2of 4**~** 

# o<AlPHA AVIATION 

# SERVICE BULLETIN AA-SB-79-001 REPLACEMENT OF OIL PRESSURE TRANSDUCER LINE 1 P lanning Information 1.1 EFFECTIVITY A lpha R2000 Series Aircraft S/N 001 to 378 A l pha HR20 0 Seri es Aircraft, all serial numbe rs. 

### 1.2 CONCURRENT REQUIREMENTS Nil 

### 1.3 REASO N The hose that connects the oil pressure transducer to the engine has been found to be not fire resistant. 

### 1.4 DESCR I PTI ON This service bul l etin provi des i nstructions for replacement of the oil pre ssure transducer hose a nd associated interface fitting at the engine end of the hose. 

### 1. 5 COMPLIANCE W ithin the next 50 flying hours or by 30111 Apr i l 2012 , wh ichever occurs first. 

### 1.6 APPROVAL By delegated authority (Alph a Aviat ion Concept Ltd, 0075990 ) GOA AA/60/11 05 

### 1.7 WEIGHT AND BALANCE Negligible effect on a i rcraft we ight 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

DE S 16 V e r 1 : 1.06 . 05 Re v ision 0 , F

eb 20 12 AA · SB· 79· 001 Page 1 o f4

### 2 2 . 1



### 2.2
2.3 

## 3 3.1 

# DiAlPHA AVIATION 

# SERVICE BULLETIN Material Information M ATER I ALS I DENTIFICATION Part Number Description I 

## I 124J003-3C R-0144 Hose Assembly 

# I 60- 28 - 121-001 Restrictor fitting 

# I AN816 -30 Nipple I I 

### L AN910- 10 Coup li ng Th e se components are avai lable from Alph a Aviation Ltd. OTHER PUBLICATIONS AFFECTED 

### N i l SPECIAL TOO LING 

### N i l**Accom~llshment** 

### Instru ctions 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 follow ing operations: a) Remove the existing hose f rom the existing fitting in Port A and then remove and discard the existing fitting in Port A. b) Remove the plug installed i n Port B and install th is plug in port A. c) Install restrictor fitting part number 60 -28-121 - 001 in port B. Torque tighten to 50-65 i n-pound (5.6 - 7.3 Nm) d) Loose install hose part number 1 24J003 -3CR-0144 onto the restrictor f itting as shown in figure 3.1. The "straight" fitting end of the hose is attached at this positio n. 

### 3.2 At The Oil Pressure Transd u cer: 

### Figure 3-2 shows the oil pressure transducer. This component is mounted on the firewall. Perform the follow in g operations: a) Remove the existing hose f rom the transducer port and discard. b) I nstall coupling part number AN91 0-1 D and nipple part number AN 816-30 onto t he 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-0 1 44 onto the AN 816 -30 nipple as shown in

figure 3.2. The "45 o" 

### fitting end of the h ose 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 wit h 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 l eakage and correct function of the oil pressure gauge . Note: Bleeding of the l ine may be required for correct function. b) Certify compliance of this s ervice bulletin in the aircraft log book.

DES 16 Ver 1 : 1.06.05 Revision 0, Feb 2012 AA SB 79·001 P.3ge2of4**~** 

# D<'ALPHA AVIATION 

# SERVICE BULLETIN

Port B Plug removal. (3.1 (b)) Restrictor f i tting p/n 60 -2 8 - 121 -001 installation . (3.1 (c)) Port A F itti ng removal (3.1 (a )) Plug installat ion . (3.1 (b))



### Figure 3-2 : Installations at oil pressure transducer

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# 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· 7 9-00 1 Page4 of4