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Service Bulletin 30 April 2020
2000ï32ï082 Page 1 of 5 ATA CHAPTER: 32 LANDING GEAR ï NOSE LANDING GEAR ï REPLACEMENT OF INCORRECT BOLTS
IN THE DOOR MECHANISM OF THE NOSE LANDING GEAR Mod No. ï
1. PLANNING INFORMATION A. EFFECTIVITY
(1) Aircraft:
Aircraft Mfg. Serial No’s SAAB 2000 ï 004 thru ï 063.
Equipped with bolt P/N 7232203ï041, delivered with EASA Form 1 certificate, Form Tracking Number: C29127 and Work Order/Contract/Invoice: 81045396 between June 15 2013 and August 31 2017.
(2) Spares: Bolt P/N 7232203 ï041, delivered with EASA Form 1 certificate, Form Tracking Number: C29127 and Work Order/Contract/Invoice: 81045396 between June 15 2013 and August 31 2017.
B. REASON It has been found that bolts (P/N 7232203ï041), installed in the door mechanism of the nose landing gear, have been incorrectly manufactured.
This incorrect manufacturing can possible cause hydrogen embrittlement and thus, decrease the strength of the bolt.
The bolts connect the nose landing gear doors to the landing gear and a broken bolt will separate the doors from the mechanism. This can affect the extension and retraction of the nose landing gear.
C. DESCRIPTION This Service Bulletin gives instructions for:
ï Inspection/verification if incorrect bolt is installed (LH or RH side of the door mechanism) ï Corrective action (for affected aircraft), replace incorrect bolts.
D. COMPLIANCE Mandatory.
Saab recommends this Service Bulletin to be performed within 12 months from release of this Service Bulletin This Service Bulletin is under EASA consideration for an Airworthiness Directive.
The final compliance terms will be set by the EASA Airworthiness Directive (AD) when issued.
E. APPROVAL The technical content of this Service Bulletin is approved under the authority of DOA nr.
EASA.21J.066.
Service Bulletin 30 April 2020
2000ï32ï082 Page 2 of 5 F. MANPOWER Estimated time to complete this Service Bulletin is:
1 persons required.
Total manhours: 1.5 Elapsed time (hours): 1.5 Labour cost at operators expense.
G. MATERIAL ï COST AND AVAILABILITY Free of charge (for bolts delivered with EASA Form 1 certificate, Form Tracking Number: C29127 and Work Order/Contract/Invoice: 81045396 between June 15 2013 and August 31 2017).
H. TOOLING
(1) Wrench, torque, 10 ï 200 lbf.in or 1 ï 15 Nm range.
I. WEIGHT AND BALANCE None.
J. ELECTRICAL LOAD DATA Not affected.
K. REFERENCES Aircraft Maintenance Manual (AMM) TASK 07 ï10ï00ï582ï807 TASK 07ï10ï00ï582ï808 TASK 32ï00ï00ï400ï801 TASK 32ï30ï00ï720ï801 L. OTHER PUBLICATIONS AFFECTED Not affected.
2. ACCOMPLISHMENT INSTRUCTIONS REF. FIG. 1 A. JOB SET ïUP
(1) Before you start the SB, make sure:
ï The part(s) needed for replacement is available ï The documentation is available.
B. INSPECTION
(1) Verify if any bolt, delivered between June 15 2013 and August 31 2017, with EASA Form 1 certificate, Form Tracking Number: C29127 and Work Order/Contract/Invoice: 81045396, is installed in the aircraft (LH or RH side of the nose landing gear mechanism).
NOTE: It is not possible to do a visual inspection in order to verify if an incorrect bolt is installed. The verification must be done through the aircraft maintenance record.
Service Bulletin 30 April 2020
2000ï32ï082 Page 3 of 5
(a) If an incorrect bolt (5) is installed, continue with step C. (Corrective Action).
(b) If no incorrect bolt (5) is installed, no further action is required. Record this Service Bulletin as implemented.
(c) If it, via the aircraft maintenance records, can not be verified if an incorrect bolt is installed or not, the bolt must be replaced.
C. CORRECTIVE ACTION WARNING: MAKE SURE THAT THE NOSE AND THE MAIN LANDING GEARS ARE IN FULLY
EXTENDED AND LOCKED POSITION AND THAT THE SAFETY PINS ARE CORRECTLY INSTALLED (REF. AMM TASK 32ï00ï00ï400ï801). THE LANDING GEARS CAN RETRACT AND CAUSE INJURY TO PERSONS.
NOTE: The procedure for the LH side is described. The procedure for the RH side is the same.
(1) Make the aircraft safe for maintenance.
(a) On the LH circuit breaker panel 9VU, open, tag and safety the circuit breakers:
LABEL POS C/B HYDRAULIC / PUMP / AUTO Fï9 11ML HYDRAULIC / PUMP / OVRD F ï83 M L HYDRAULIC / LDG / CONTROL F ï77 G A
(b) Lift the aircraft on the three main jacks (Ref. AMM TASK 07 ï10ï00ï582ï807).
(2) Replace the incorrect bolt.
(a) Remove the incorrect bolt 1 Remove and discard the cotter pin (1). Remove the nut (2) and the washer(s) (3) from the bolt (5).
2 Hold the bolt (5) and remove the nut (7) together with the washer (6).
3 Move the link (4) and remove the bolt (5) from the arm (8).
(b) Install the correct bolt 1 Install the bolt (5) to the arm. Make sure the end with the cotter pin hole is facing forward.
2 Install the washer (6) and the nut (7), torque the nut to between 40ï48 lbf.in (4.5ï5.4 Nm).
3 Move the link (4) on to the bolt (5).
4 Install the washer(s) (3) and the nut (2). Tighten the nut (2) to contact and install a new cotter pin (1).
D. JOB CLOSE ïUP
(1) Do the functional test of the extension and retraction of the landing gears (Ref. AMM TASK 32ï30ï00ï720ï801). Check that the NLG doors close simultaneously without twisting the seals.
(2) Lower the aircraft and remove the three main jacks (Ref. AMM TASK 07 ï10ï00ï582ï808).
(3) Remove all the tools and equipment from the work area. Make sure the work area is clean.
Service Bulletin 30 April 2020
2000ï32ï082 Page 4 of 5
3. MATERIAL INFORMATION A. Part needed for corrective action:
Item Part Number Qty Nomenclature Designation Remarks 5 7232203 ï041 AR Bolt LH and/or RH side Note *) NOTE: *) Bolt must not have been delivered between June 15 2013 and August 31 2017 with EASA Form 1 certificate, Form Tracking Number: C29127 and Work Order/Contract/Invoice:
81045396.
Service Bulletin 30 April 2020
2000ï32ï082 Page 5 of 5 Corrective Action ï Replacement of Bolt FIG. 1 1 2 3 4 5 6 7 8 NOTE: