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JETSTREAM BRITISH AEROSPACE SERIES 3100 & 3200
SERVICE BULLETIN
BAE SYSTEMS,
PRESTWICK INTERNATIONAL AIRPORT, AYRSHIRE, KA9 2RW, SCOTLAND.
32-JA090240
TRANSMITTAL SHEET This page transmits Revision 1 of Service Bulletin 32-JA090240, pages 1 thru 14.
TITLE: WINGS - INSPECTION OF MAIN UNDERCARRIAGE FITTING.
OVERVIEW OF CHANGE To add additional instructions to gain access to wing tank area.
DETAILS OF CHANGE Page 2, Section 1,K - Additional references added.
Page 7, Section 2,C (3) - Item (a) added.
Page 8, Section 2,C (3) - Items (d) and (e) added.
Page 9, Section 2,E (2) - Items (a), (b), (c), (d) and (e) added.
INSTRUCTIONS FOR INCORPORATION Remove pages 1 thru 18 at original issue.
Add pages 1 thru 14 at Revision 1
INCORPORATION OF THIS REVISION DOES NOT REQUIRE REWORK OF THE MODIFICATION(S) EMBODIED BY EARLIER REVISIONS OF THIS SERVICE BULLETIN.
ORIGINAL ISSUE: 29/04/09 REVISION 01: 18th January 2010 32-JA090240 PAGE 1 OF 1 BAE SYSTEMS (Operations) Limited.
Printed in the U.K.
BRITISH AEROSPACE
JETSTREAM SERIES 3100 & 3200
SERVICE BULLETIN
BAE SYSTEMS,
PRESTWICK INTERNATIONAL AIRPORT, AYRSHIRE, KA9 2RW, SCOTLAND.
32-JA090240 TITLE: WINGS - INSPECTION OF MAIN UNDERCARRIAGE FITTING.
INSPECTION
1. PLANNING INFORMATION A. Effectivity All HP 137 Mk 1, Jetstream series 200, Jetstream series 3100 and Jetstream series 3200 aircraft, which are post modification JM5218 or post modification JM8003.
B. Reason As a result of the fatigue testing programme on the Jetstream fatigue test specimen, cracks have been found on the post modification standard of main undercarriage fitting (part no. 1379133B1/2/3/4). Analysis of this failure indicates that an inspection regime will have to be implemented in order to ensure that the fitting can continue to be used C. Description A Non-Destructive Test Examination is carried out on the main landing gear pivot beam attachment fastener bores.
This service bulletin has an effect on the main landing gear.
The tasks are as follows:
Make aircraft safe for servicing.
Jack aircraft.
Remove main undercarriage legs.
Carry out NDT examination.
Report any cracks or discontinuities.
Install main undercarriage legs.
Test main undercarriage system.
Lower aircraft from jacks.
Amend aircraft records.
ORIGINAL ISSUE: 29/04/09 REVISION 01: 18th January 2010 32-JA090240 PAGE 1 OF 14 BAE SYSTEMS (Operations) Limited.
Printed in the U.K.
BRITISH AEROSPACE
JETSTREAM SERIES 3100 & 3200 D. Manpower 20 manhours.
Mechanical skills are necessary.
E. Material - Cost and Availability None F. Tooling - Price and Availability The equipment necessary to accomplish this service bulletin is listed in Para 2.B. and in report number STR/J32/085 (BAE/MAN/J32/EDD/17).
G. Weight and Balance None.
H. Aircraft Noise Levels Aircraft noise is not affected.
I. Electrical Load Data Not affected.
Software Accomplishment Summary Not applicable.
K. References Aircraft Maintenance Manual, Chapter 32-10-11.
Aircraft Maintenance Manual, Chapter 12-11-28.
Aircraft Maintenance Manual, Chapter 07-10-00.
Report Number: STR/JS32/085.
Service Bulletin 05-JA 010642.
Publications Affected NOTE: The maintenance review board report and maintenance planning document will be reviewed, for possible inclusion of a scheduled maintenance task.
Operators are requested to advise The Project Manager, Airline Maintenance & Publication Services, BAE SYSTEMS, Regional Aircraft, Prestwick International Airport, Ayrshire, KA9 2RW, SCOTLAND, of the accomplishment of this service bulletin.
ORIGINAL ISSUE: 29/04/09 REVISION 01: 18th January 2010 32-JA090240 PAGE 2 OF 14 BAE SYSTEMS (Operations) Limited.
Printed in the U.K
BRITISH AEROSPACE
JETSTREAM SERIES 3100 & 3200 M. Family Tree Of Modification Relationships Not applicable.
N. Approval A threshold inspection of the main undercarriage fitting should be made at 41,000 landings with a repeat inspection every 27,000 landings. Any aircraft in excess of 39,000 landings must inspect within a period of 2000 landings.
NOTE: The accumulated landings for the main undercarriage fitting should be evaluated using Para 2.A.
The technical content of this service bulletin is the subject of EASA Airworthiness Directive consultation, and is approved under the authority of Design Organisation Approval No. EASA.21J.047.
Signed Date 18/1/1o EASA Part 21 Approval EASA.21J.047.
ORIGINAL ISSUE: 29/04/09 REVISION 01: 18" January 2010 32-JA090240 PAGE 3 OF 14 BAE SYSTEMS (Operations) Limited.
Printed in the U.K.
BRITISH AEROSPACE JETS 00100
PAGE LEFT INTENTIONALLY BLANK ORIGINAL ISSUE: 29/04/09 REVISION 01: 18th January 2010 32-JA090240 PAGE 4 OF 14 BAE SYSTEMS (Operations) Limited.
Printed in the U.K.
BRITISH AEROSPACE
JETSTREAM SERIES 3100 & 3200
2. ACCOMPLISHMENT INSTRUCTIONS
DUPLICATE INSPECTION
WHENEVER ANY PART OF THIS SYSTEM IS DISMANTLED, ADJUSTED, REPAIRED OR
RENEWED, DETAILED INVESTIGATION MUST BE MADE ON COMPLETION TO ENSURE
THAT DISTORTION, TOOLS, RAGS OR ANY OTHER LOOSE ARTICLES OR FOREIGN
MATTER SUCH AS COULD IMPEDE THE FREE MOVEMENT AND SAFE OPERATION OF
THE SYSTEM ARE NOT PRESENT AND THAT THE SYSTEMS AND INSTALLATIONS IN THE WORK AREA ARE CLEAN.
WHENEVER ANY PART OF EITHER THE MAIN OR ANY OTHER ASSOCIATED SYSTEM
IS DISMANTLED, ADJUSTED, REPAIRED OR RENEWED, THAT PART OF THE SYSTEM
THAT HAS BEEN DISTURBED SHALL BE SUBJECTED TO A DUPLICATE INSPECTION
FOR SECURITY OF LOCKING DEVICES, FULL AND FREE MOVEMENT, DIRECTION AND
TENSION CHECKS AND, FOR AIRCRAFT ON THE BRITISH REGISTER, THE
COMPLETION OF THIS WORK SHALL BE CERTIFIED IN ACCORDANCE WITH THE BRITISH CIVIL AIRWORTHINESS REQUIREMENTS, SECTION A, CHAPTER A6-2 OR IN
THE CASE OF AIRCRAFT NOT ON THE BRITISH REGISTER, THE EQUIVALENT NATIONAL STANDARD.
WARNING: MAKE SURE THE AIRCRAFT AND THE AIRCRAFT SYSTEMS ARE MADE
SAFE AS DETAILED IN THE APPLICABLE CHAPTERS OF THE AIRCRAFT MAINTENANCE MANUAL.
NOTE: Abbreviations used in the accomplishment instructions of this service bulletin are:
AMM - Aircraft Maintenance Manual.
A. Evaluation
(1) If the actual service life of the main undercarriage fitting is unknown, the aircraft records should be investigated to determine if the component has been replaced in-service. If there is no evidence contained in the aircraft records to indicate that the fitting has been replaced, operators are to assume that the component has accumulated the same number of landings as the airframe.
Where the main undercarriage fitting has been replaced in-service with a new component, operators are to assume that the fitting has accumulated the same number of landings as the airframe since the replacement was installed.
For instances where the main undercarriage fitting has been replaced in-service with a used component and the history of the component is known, operators are to assume that the fitting has accumulated a total number of landings equal to the same number of landings as the airframe since the replacement component was installed plus the number of landings accumulated by the fitting prior to installation on the aircraft. If there is any uncertainty over the integrity of the history of the part then the fitting should be assumed to have reached the inspection threshold and therefore should be inspected by NDT.
ORIGINAL ISSUE: 29/04/09 REVISION 01: 18th January 2010 32-JA090240 PAGE 5 OF 14 BAE SYSTEMS (Operations) Limited.
Printed in the U.K.
BRITISH AEROSPACE
JETSTREAM SERIES 3100 & 3200 For instances where the main undercarriage fitting has been replaced in-service with a used component, and the history of the component is unknown, operators are to assume that the fitting has reached the inspection threshold and therefore should be inspected by NDT.
B. Equipment
(1) The following equipment was used during the development of this inspection and found to be acceptable:
(a) Instrument: Elotest B1 v4 phase analysis eddy current instrument with B1- RS connector from Rohmann (UK) Ltd.
(b) Rotor: Mini rotor from Rohmann (UK) Ltd.
(c) Probe 1: 3/8 in. diameter probe to fit the mini rotor part no. MRRP-RUK-1-0.375 in (9.53 mm) - 2 in. (50.8 mm) from Rohmann (UK) Ltd.
Probe 2: ½ in. diameter probe to fit the mini rotor part no. MRRP-RUK-1-0.5 in. (12.7 mm) - 2 in. (50.8 mm).
from Rohmann (UK) Ltd.
Probe 3: 7/8 in. diameter probe to fir the mini rotor part no. MRRP-RUK-1-0.875 in. (22.23 mm) - 2 in. (50.8 mm).
from Rohmann (UK) Ltd.
(d) Lead: RK-2-N/1 from Rohmann (UK) Ltd.
(e) Calibration Standard: Aluminium alloy calibration block for rotating (dynamic) eddy currents, cross drilled hole type (refer to NTM Part 6, 20-00-00).
NOTE: Any comparable eddy current equipment may be used provided it satisfies the requirements of this instruction, and is capable of resolving the reference hole in the calibration standard at the required level of sensitivity.
ORIGINAL ISSUE: 29/04/09 REVISION 01: 18th January 2010 32-JA090240 PAGE 6 OF 14 BAE SYSTEMS (Operations) Limited.
Printed in the U.K.
BRITISH AEROSPACE
JETSTREAM SERiES 3100 & 3200 C. Preparation.
(1) Instrument calibration:
Initial Settings: Refer to manufacturers instructions.
Alarm: Off Frequency: Set to 500 kHz Gain: Set to produce required sensitivity Pre-amp: 30 dB Y spread: 0 dB X spread: 0 dB Filter: Band: Set to Dynamic High pass: Set to 500Hz Low pass: Set to 2.5kHz Bandwidth Limiter: Set to Off Dot Position: Reference figure 2
(2) Sensitivity settings:
(a) Select spot display (Y/X).
(b) Using the appropriate probe, adjust the instrument to produce a vertical signal from the 1/16 in. (1.58 mm) diameter cross drilled hole in the calibration standard.
(c) Select time base display (Y/T).
(d) Set signal from 1/16 in. (1.58 mm) diameter hole to 100 per cent full screen height (FSH).
(e) Select spot display (Y-X).
(T) Set the signal from the 1/16 in. (1.58 mm) diameter hole to 30 degrees anticlockwise.
(3) Make aircraft safe for servicing:
(a) Defuel the aircraft in accordance with AMM Chapter 12-11-28.
(D) Refer to AMM 07-10-00, raise aircraft on jacks.
ORIGINAL ISSUE: 29/04/09 REVISION 01: 18th January 2010 32-JA090240 PAGE 7 OF 14 BAE SYSTEMS (Operations) Limited.
Printed in the U.K.
BRITISH AEROSPACE
JETSTREAM SERIES 3100 & 3200
(c) Refer to AMM 32-10-11, remove main undercarriage leg.
(d) Remove the fuel cell access panels W25 and W26 from the LH and RH main landing gear bays. Retain panels and bolts.
(e) Ref Fig 1. Remove sealant from the undercarriage leg pivot beam nuts and bolt heads to be inspected.
Remove the bolts for inspection.
D. Accomplishment
(1) Make certain the main undercarriage leg pivot beam fastener bores are clean and free from burrs:
(a) Refer to Figure 1 and visually check the inspection areas for any obvious damage prior to inspection.
(2) Inspection procedure:
(a) Select spot (Y/X) display.
(D) Insert the probe into the first bore to be inspected and scan the full length of the bore.
(c) By careful manipulation, maximise and observe any signals.
(d) Make sure that the sensitivity is reset for each different probe used, and that operations (a) to (b) are repeated for each fastener bore to be inspected.
A large signal indicating the presence of mechanical damage is produced in each 7/8 in. (22.23 mm) diameter bore at the point where it is intersected by another 7/16 in. (11.11 mm) diameter fastener bore (Ref.
Figure 1). This mechanical signal is caused by the intersecting fastener bore and should not be reported.
(3) Interpretation:
(a) Interpret signals by reference to Figure 3.
(b) Select time base (Y/T) display to ascertain the amplitude and direction of any signal.
(4) Accept / Reject criteria:
Vertical signals over 20 per cent FSH that can not be attributed to probe handling or material interfaces shall be considered as a crack.
ORIGINAL ISSUE: 29/04/09 REVISION 01: 18th January 2010 32-JA090240 PAGE 8 OF 14 BAE SYSTEMS (Operations) Limited.
Printed in the U.K.
BRITISI L AEROSPACE
JETSTREAM SERIES 7100 & 3200
(b) Signals greater than 40 per cent FSH, irrespective of signal angle, that can not be attributed to probe handling or material interfaces shall be investigated and reported.
NOTE 1: When reporting a crack or discontinuity, select time base (Y/T) display to ascertain its amplitude and direction.
NOTE 2: The word discontinuity is a generic term for faults such as cracks, corrosion and mechanical damage.
E. Recovery
(1) Repair:
(a) Repair any cracks or discontinuities found in accordance with the SRM or contact BAE SYSTEMS Repair Design Office for an approved repair scheme. Make aircraft safe for servicing.
(2) Reinstall:
(a) Ref Fig. 1. Replace bolts removed for inspection.
(b) Bolts are to be torque loaded initially to 70% value whilst sealant is in the freshly mixed condition and finally torque loaded to :
200 to 280 Ibf.in. for 3/8in. dia. bolts.
500 to 650 Ibf.in. for 1/2in. dia. bolts.
(c) Apply sealant over bolt heads and nuts.
(d) Replace panels removed to gain access.
NOTE: All fuel tank areas to be sealed in accordance with Service Bulletin 57-JA 841000.
(e) Refer to AMM 32-10-11, replace main undercarriage leg.
(f) Refer to AMM 07-10-00, lower and remove jacks.
Refuel the aircraft in accordance with AMM Chapter 12-11-28 and carry out leak checks particularly at points disturbed and resealed.
(3) Aircraft records:
(a) Add service bulletin number 32-JA090240 Rev 1 to the aircraft records.
All crack and discontinuity indications are to be recorded in the relevant aircraft documentation, and the appropriate BAE SYSTEMS approved repair/rectification taken.
(4) Reporting procedure:
ORIGINAL ISSUE: 29/04/09 REVISION 01: 18 January 2010 32-JA090240 PAGE 9 OF 14 BAE SYSTEMS (Operations) Limited.
Printed in the U.K.
BRITISH AEROSPACE JET SEE A200
(a) Report all cracks discontinuities to:
Fleet Data Department (Building 37)
BAE SYSTEMS Regional Aircraft Prestwick International Airport Ayrshire Scotland KA9 2RW
(b) Also send the following information:
1 Aircraft construction number.
Aircraft registration.
Flying hours and number of landings.
4 SB number.
Location and area or length of crack or discontinuity percent FSH.
NOTE: Operators are reminded of the necessity to inform The Project Manager, Airline Maintenance & Publication Services, BAE SYSTEMS, Prestwick, of the accomplishment of this service bulletin in order to obtain the necessary revisions for the affected manuals, see paragraph 1.K. Publications Affected, of this bulletin.
F. MATERIAL INFORMATION
(1) None.
ORIGINAL ISSUE: 29/04/09 REVISION 01: 18h January 2010 32-JA090240 PAGE 10 OF 14 BAE SYSTEMS (Operations) Limited.
Printed in the U.K.
PITISH AEROSPA
JETSTREAM SERIES 3100 & 3200 MAIN
UNDERCARRIAGE
FITTING (REF)
MAIN LANDING
GEAR LEG (REF) FWD
INSPECT
0.875in (22.23mm) DIA BORE
0.437in (11.11mm) DIA
BORE INTERSECTS BORE TO BE INSPECTED.
SIGNALS CAUSED BY
THIS BORE LEFT SHOWN
SHOULD NOT RIGHT SIMILAR
BE REPORTED (DETAIL REMOVED
FOR CLARITY)
INSPECT
0.375in (9.53mm) DIA INSPECT BORE INSPECT 0.375in (9.53mm) DIA
0.5in (12.7mm) DIA BORE BORE NOTE:
IT IS REQUIRED THAT THE MAIN
UNDERCARRIAGE LEG IS REMOVED
VIEW LOOKING VIEW LOOKING WHEN CARRYING OUT THIS INSPECTION
FORWARD AFT J3200004 Area of Inspection - Main Landing Gear Pivot Beam Figure 1 ORIGINAL ISSUE: 29/04/09 REVISION 01: 18th January 2010 32-JA090240 PAGE 11 OF 14 BAE SYSTEMS (Operations) Limited.
Printed in the U.K.