Service Bulletin

12 January 2010

Revision 01, 01 November 2010

340–32–139

Page 1 of 8

ATA CHAPTER: 32

LANDING GEAR – MAIN LANDING GEAR – REPLACEMENT OF THE HARNESS FOR

THE SEPARATION BOLT

Mod No. 3317

1. PLANNING INFORMATION

A. EFFECTIVITY

(1) Aircraft:

Aircraft Mfg. Serial No’s SAAB SF340A – 004 thru – 159.

Aircraft Mfg. Serial No’s SAAB 340B – 160 thru – 459.

NOTE: Service Bulletin 340–32–128 must be incorporated before or in conjunction with this SB.

(2) Spares: Not affected.

B. REASON

This Service Bulletin is issued to introduce a new improved separation bolt harness with a new routing.

Incorporation of this Service Bulletin will give an improved harness installation and thus ensure correct

function of the emergency system for the landing gear system.

C. DESCRIPTION

This Service Bulletin gives instructions for:

– Removal of the old separation bolt harness

– Installation of the new improved separation bolt harness

– Electrical system test of the separation bolt

– Functional test of the landing gear extension and retraction system.

D. COMPLIANCE

Mandatory.

Saab recomends this Service Bulletin to be performed within 12 months from release of first issue of

this SB.

This Service Bulletin is under EASA consideration for an Airworthiness Directive (AD).

The final compliance terms will be set by the EASA Airworthiness Directive when issued.

E. APPROVAL

The technical content of this Service Bulletin is approved under the authority of DOA nr. EASA.21J.066.

F. MANPOWER

Estimated time to complete this Service Bulletin is:

1 persons required.

Total manhours: 10

Elapsed time (hours): 10
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Labour cost at operators expense.

G. MATERIAL – COST AND AVAILABILITY

Price and availability for Mod Kit. No. SAAB 340–32–139–01 will be furnished on request.

H. TOOLING

(1) Faraday cage, quantity 2.

I. WEIGHT AND BALANCE

No Change.

J. ELECTRICAL LOAD DATA

Not affected.

K. REFERENCES

Aircraft Maintenance Manual (AMM) 06–30–00

29–00–00

32–12–05

32–30–00

32–34–15

32–34–20.

Wiring Manual (WM) 20–00–00.

L. OTHER PUBLICATIONS AFFECTED

Aircraft Maintenance Manual (AMM) 32–34–17.

Illustrated Parts Catalog (IPC) 32–30–00.

2. ACCOMPLISHMENT INSTRUCTIONS

CAUTION: BE CAREFUL WHEN YOU DO THE MODIFICATION OF THE HARNESS.

MAKE SURE THAT YOU DO NOT DAMAGE THE EXISTING WIRES WHEN

NEW WIRES ARE INSTALLED. CLEAN AND INSPECT THE AFFECTED

HARNESS WHEN THE MODIFICATION IS COMPLETED. DAMAGES TO THE

WIRES CAN CAUSE SYSTEM MALFUNCTION.

NOTE: All wiring changes are to be performed in accordance with the procedures in the

WM 20–00–00.

NOTE: The color of the lacing cord on the A and the B wire bundles gives the harness class

and identification. The A harness is identified with white lacing cord and the B

harness is identified with red/black lacing cord.

A. JOB SET–UP

WARNING: MAKE SURE THE SAFETY PINS ARE INSTALLED IN THE NOSE LANDING GEAR

AND IN THE MAIN LANDING GEAR. THE LANDING GEAR CAN RETRACT AND

CAUSE INJURY TO PERSONS.

(1) Before you start the SB, make sure:

– The modification kit contains the parts listed in the Service Bulletin

– The local supply items listed in the Service Bulletin are available

– The documentation is available

– The special tools are available.
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(2) De–pressurize the hydraulic system (Ref. AMM 29–00–00).

(3) Open the circuit breakers.

On the LH circuit breaker panel 9VU, open, tag and safety the circuit breaker:

LABEL POS C/B

L LDG EMER RELEAS E–9 1GB

HYDRAULIC / LDG / CONTROL F–7 7GA

HYDRAULIC / PUMP / AUTO F–9 11ML

On the RH circuit breaker panel 10VU, open, tag and safety the circuit breaker:

LABEL POS C/B

R LDG EMER RELEAS L–9 2GB

(4) Open the main landing gear forward doors. Secure doors wide open (Ref. AMM 32–12–05).

(5) Remove access panels 457AL and 467BR (Ref. AMM 06–30–00).

B. REMOVAL

WARNING: THE SEPARATION BOLT IS AN EXPLOSIVE DEVICE. WEAR SAFETY GLASSES

AND EAR PROTECTORS TO PREVENT POSSIBLE INJURY IF THE SEPARATION

BOLT IS ACCIDENTLY DETONATED.

REF. FIG. 1

(1) Remove the LH nacelle separation bolt harness.

(a) Disconnect and cap electrical connector 3GB–P1 from the separation bolt receptacles. Install

faraday cage on receptacle (Ref. AMM 32–34–15).

(b) Remove harness (101) with bushings and the clamps (102). Save the bolts for installation of

the new harness.

(c) Remove ground wires at connector 3GB–J1A from ground point 570VN.

(d) Disconnect connector 3GB–J1:A from 3GB–P1:A.

(e) Discard the harness (101) and the clamps (102).

(2) Remove the RH nacelle separation bolt harness.

(a) Disconnect and cap electrical connector 4GB–P1 from the separation bolt receptacles. Install

faraday cage on receptacle (Ref. AMM 32–34–15).

(b) Remove harness (101) with bushings and the clamps (102). Save the bolts for installation of

the new harness.

(c) Remove ground wires at connector 4GB–J1A from ground point 670VN.

(d) Disconnect connector 4GB–J1:A from 4GB–P1:A.

(e) Discard the harness (101) and the clamps (102).

C. INSTALLATION

REF. FIG. 1

(1) Install the new separation bolt harnesses to the LH nacelle.

(a) Remove faraday cage from the separation bolt receptacle.
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(b) Install a heat shrinkable sleeve with length 6 in (150 mm) to the harness (1), do not shrink

at this time.

(c) Install the harness (1) and connect the connector 3GB–J1A to the connector 3GB–P1A and

the connector 3GB–P1 to the separation bolt receptacle.

(d) Install the heat shrinkable sleeve over the connector 3GB and shrink into position using a heat

gun.

(e) Install ground wires at connector 3GB–J1A to ground point 570VN.

(f) Install the clamp (2) and the two bolts. Do not tighten the bolt that holds the clamp (2) at this

time.

(g) Make sure that the length from the front face of the connector 3GB–P1 to the clamp (2) is

approximately 11.4 in (290 mm). Adjust if necessary.

(h) Tighten the bolt that holds the clamp (2).

(i) Strap the harness (1), make sure that sufficient clearance between the harness, the

connectors, the landing gear mechanism and the nacelle structure is obtained.

(j) Seal the grounding point 570VN with sealant MIL–S–8802 or equivalent.

(2) Install the new separation bolt harnesses to the RH nacelle.

(a) Remove faraday cage from the separation bolt receptacle.

(b) Install the heat shrinkable sleeve with length 6 in (150 mm) to the harness (1), do not shrink

at this time.

(c) Install the harness (1) and connect the connector 4GB–J1A to the connector 4GB–P1A and

the connector 4GB–P1 to the separation bolt receptacle.

(d) Install the heat shrinkable sleeve over the connector 4GB and shrink into position using a heat

gun.

(e) Install ground wires at connector 4GB–J1A to ground point 670VN.

(f) Install the clamp (2) and the two bolts. Do not tighten the bolt that holds the clamp (2) at this

time.

(g) Make sure that the length from the front face of the connector 4GB–P1 to the clamp (2) is

approximately 11.4 in (290 mm). Adjust if necessary.

(h) Tighten the bolt that holds the clamp (2).

(i) Strap the harness (1), make sure that sufficient clearance between the harness, the

connectors, the landing gear mechanism and the nacelle structure is obtained.

(j) Seal the grounding point 670VN with sealant MIL–S–8802 or equivalent.

D. JOB CLOSE–UP

(1) Close the circuit breakers.

On the LH circuit breaker panel 9VU, remove the tag and close the circuit breaker:

LABEL POS C/B

L LDG EMER RELEAS E–9 1GB

HYDRAULIC / LDG / CONTROL F–7 7GA

HYDRAULIC / PUMP / AUTO F–9 11ML

On the RH circuit breaker panel 10VU, remove the tag and close the circuit breaker:
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LABEL POS C/B

R LDG EMER RELEAS L–9 2GB

(2) Do the electrical system test of the separation bolt (Ref. AMM 32–34–20).

(3) Do the functional test of the landing gear extension and retraction system (Ref. AMM 32–30–00).

Make sure that there is no interference between the MLG up–lock switch and the new harness

installed.

(4) Close the main landing gear forward doors (Ref. AMM 32–12–05).

(5) Install access panels 457BR and 467BR (Ref. AMM 06–30–00).

3. MATERIAL INFORMATION

A. Modification Kit No SAAB 340–32–139–01 contains:

Item Part Number Qty Nomenclature Designation Remarks

1 7292520–691 2 Harness – –

2 M85052/1–6 2 Clamp – –

B. Local supply

Item Part Number Qty Nomenclature Designation Remarks

– MIL–S–8802 AR Sealant 570/670VN –

– MS3367–1

O/T

MS3367–1–0

AR Strap – –

– Viton–E 1”

O/T

RW–200–E 1”

12 in

(300mm)

Shrinkable Sleeve 3GB/4GB –

NOTE: Equivalent materials can be used for listed items, Ref. SRM 51–33–00.

C. Removal

Item Part Number Qty Nomenclature Designation Remarks

101 7292520–678 2 Harness – –

102 MS21919WDG10 4 Clamp – –
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01101

102 102 02

SEPARATION BOLT

REF.

A30643

Separation Bolt Harness – Removal/Installation

FIG. 1
Service Bulletin

Date Month Year

Revison X, Date Month Year

340–XX–XXX

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