BAeJETSTREAIW

Se,/es4I'OO

BAE SYSTEMS,

PRESTWICK INTERNATIONAL AIRPORT,

AYRSHIRE, KA92RW,

SCOTlANO.

J41-52-064 I ,

TRANSMITI Al SHEET

This page transmits Original Issue to Inspection Service Bulletin J41-52-064, pages 1 through 5.

TITLE: DOORS -INTRODUCTION OF ULTRASONIC INSPECTION OF THE UPPER AND

lOWER PASSENGER/CREW DOOR PIN GUIDES

INSPECTION

AMENDMENT NUMBER JA090540

ORIGINAL ISSUE: SEP 15/09

BA£ SYSTEMS (Operalions) Limited.

Printed In the U.K,

J41-52-064

PAGE 1 OF 1

8AeJETSTREAJII

Sedes4100

SERVICE . BULLETIN .

BAE SYSTEMS,

PRESTWICK INTERNATIONAL AIRPORT,

AYRSHIRE, KA92RW,

SCOTLAND.

J41-52-064 II

TITLE: DOORS· INTRODUCTION OF ULTRASONIC INSPECTION OF THE UPPER AND

lOWER PASSENGERICREW DOOR PIN GUIDES

INSPECTION

AMENDMENT NUMBER JA090540

1. PLANNING INFORMATION

A. Effectivity

All Jetstream series 4100 aircraft.

B. Reason

Failure of a passenger/crew entry door lower aft pin guide plate has been identified on an

in-service aircraft as a result of exfoliation corrosion.

c. Description

This inspection service bulletin introduces an Ultrasonic NDT inspection which has been

developed to allow corrosion and discontinuities to be identified on both the upper and

lower pin guide plates in situ with some guide blocks removed.

The tasks are as follows:

The passenger doors are opened.

An ultrasonic inspection of the passenger door upper and lower guide plates is done.

The passenger doors are closed.

The aircraft records are amended.

ORIGINAL ISSUE: SEP 15/09

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D. Manpower

2.0 man-hours for NTD inspection.

NOT specialist.

Mechanical and electrical skills are necessary.

E. Material - Cost and availability

Not applicable.

F. Tooling - Price and Availability

Not applicable.

G. Weight and Balance

Not affected.

H. Aircraft Noise

Not affected.

I. Electrical Load Data

Not affected.

J. Software Accomplishment Summary

None.

K. References

- Aircraft maintenance manual Chapter 12-00-00.

lL. Publications Affected

None.

M. Family Tree Of Modification Relationships

Not applicable.

J41·52-064

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N. Approval

The technical content of this inspection service bulletin is the subject of AirvlOrthiness

Directive consultation, and is approved under the authority of Design Organisation

Approval No. EASA.21J.047.

This inspection is to be embodied within 12 months of the original issue date of the

inspection service bulletin. Repeat inspections to be done at 4 year intervals after the

original inspection.

Signed

Date

---

... 0'>" .

................ iJh/1

EASA Part 21 Approval No. EASA.21J.047.

ORIGINAL ISSUE: SEP 15/09

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2. ACCOMPLISHMENT INSTRUCTIONS

WARNING: MAKE SURE THE AIRCRAFT AND THE AIRCRAFT SYSTEMS ARE MADEi

SAFE AS DETAILED IN THE APPLICABLE CHAPTERS OF THE AIRCRAFT I

MAINTENANCE MANUAL.

NOTE: Statements 'AMM' refer to the Jetstream Series 4100 Aircraft Maintenance Manual.

A. Preparation

(1) Open the passenger doors.

(2) Refer to AMM, Chapter 12-00-00. Remove all aircraft electrical power.

(3) Display a warning notice in the flight compartment 'DO NOT APPLY POWER TO

THE AIRCRAFT'.

B. Accomplishment

(1) Refer to Appendix 1. Do an ultrasonic inspection of the passenger door upper and

lower guide plates.

(2) If the component being inspected fails the ULTRASOUND inspection. The

component is to be replaced with a serviceable component before next flight.

C. Aircraft Recovery

(1) Remove warning notice from the flight compartment.

(2) Close the aircraft passenger doors.

(3) Aircraft records.

Add Inspection Service Bulletin number 'J41-52-064' to the aircraft records.

NOTE: Operators are requested to advise The Publications Control Team, Aircraft

Maintenance and 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.

3. MATERIAL INFORMATION

Not applicable_

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4. CONTINUED AIRWORTHINESS

A. Continued Airvvorthiness Instructions

There are no continued ailworthiness instructions applicable to this service bulletin.

B. Scheduled Maintenance

None.

C. Removal Procedures

None.

D. Installation Procedures

None.

E Test Procedures

None.

F. Trouble Shooting

None.

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APPENDIX 1

PASSENGER DOOR - UPPER AND LOWER GUIDE PLATES

SSI NUMBER: None

1. INSTRUCTION REFERENCE

BAEIMAN/J41/ULT/3

2. SAFETY PRECAUTIONS

All relevant local safety procedures must be observed.

3. PROCEDURE

A. Application

This instruction is applicable to Jetstream series 4100.

B.

C.

Component to be Examined (Ref. Fig. 1) I

(1) Passenger door, upper and lower, guide plates fitted to the forward and aft

. door frames.

Purpose of Examination

(1) To detect a split in a component, caused by exfoliation corrosion, flus~ with

the upper surface of its base It is anticipated that a split is detected when its

area is approximately 0.12 in.2(78mm2) or greater.

D. Equipment Required

The following equipment was used during the development of this inspection

instruction and found to be acceptable,

(1 )

(2)

(3)

(4)

Instrument

Probe:

lead:

Coupling Media:

Epoch Ltfrom Olympus NOT Ltd.

Krautkramer 5MHz frequency, 10mm diarpeter,

o degree contact probe Part number K5Ki from

GE Inspection Technologies (Ref. Fig. 3).

Standard lema to microdot connectors

Part number lCM-74~4 from Olympus NOT ltd.

Ultragel I! from Diagnostic Sonar Ltd.

NOTE: Any comparable ultrasonic equipment may be used provided it satisfies the

requirements of this instruction.

ORIGINAL ISSUE: SEP 15/09

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E_ Preparation

Refer to the Aircraft Maintenance Manual (AMM) for preparation of the following items:

(1) Aircraft

(a) Remove the stainless steel guides as shown in figure 1 from the

upper and lower guide plates on both the forward and aft door frames.

(2) Component

(a) Ensure that the surface of the scan area is clean and smooth.

(b) Visually check the area of inspection for any obvious damage prior to

inspection.

F. Examination Procedure

(1) InstrumentCalibration

Table 1

Initial settings Refer to manufacturer's instructions

Gain As required dB

Range 1.000 in.

Velocity 0.2517 in/lJS (6394 m/s)

Zero o ~S

Pulser Half Wave +

Energy Med

Damping 500

Transmission Pulse Echo

Reject 0%

Angle o degrees

Gates Position as shown in figure 2

Set gate 1 to trigger the alarm above gate

threshold

Alarm

Set gate 2 to trigger the alarm below gate

threshold

(2) Sensitivity Settings

- --- --- - -. --'Ea)-···- ..P-ositiofl t-he-ini-tial-pulse-at- zer-o-sl1 the- tir-nebase.

(b) Place the probe on the component as shown in fig-ure 2, and set the

backwall echo to 8 on the timebase.

(c) Adjust the instrument's gain so the amplitude of the backwall echo is

100 per cent full screen height.

(d) Re~check the sensitivity setting on each door guide prior to inspection.

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(3) Inspection Procedure

(a) Place the probe on the surface of the component within the area of inspection

and scan the hatched area shown in figure 2_

(b) Monitor the amplitude of the backwall echo at 8 on the timebase, and also

look for possible fault indications at approximately 6 on the timebas8.

(e) Ensure that the upper and lower guide plates on the forward and aft door

frames are inspected.

NOTE: As the probe is scanned across the cross drilled holes the backwall echo will

reduce below the alarm trigger threshold. This is not a fault indication.

G. Interpretation

(1) A split in the component caused by exfoliation corrosion is likely to occur

flush with the upper surface of its base. This will cause a decrease in the

backwa!l echo. It may also produce a fault signal at approximately 6 Qnthe

timebase.

H. Accept I Reject Criteria (Ref. Fig. 3)

(1) The following shall be considered as evidence of exfoliation corrosion:

(a) Any decrease in the backwaJlecho below 60 per cent full screen

height.

(b) Any fault signal above 10 per cent full screen height.

(c) If evidence of exfoliation corrosion is found in steps (a) or (b). Then

the component being inspected is to be replaced with a serviceable

component before next flight.

1. Examination Standard

(1)

NOTE:

All corrosion and discontinuity indications are to be recorded in the relevant

aircraft documentation and the appropriate BAE SYSTEMS approved rJpair I

rectification taken. I

The word discontinuity is a generic term for faults such as cracks, corrosion

and mechanical damage.

J. Reporting Procedure

(1) Report all cracks I discontinuities to:

Fleet Data Department (Building 37)

BAE SYSTEMS

Regional Aircraft

Prestwick Intemational Airport

Ayrshire

Scotland KA9 2RW.

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(2) Also sendthefollowinginformation:

(a) Aircraft constructionnumber

(b) Aircraft registration

(c) Flyinghours and numberof landings

(d) SB number

(e) Location I area or length of the crack or discontinuity j per cent FSH.

K. Additional Information

(1) Ensure all test equipmentis removedfrom the aircraft on completion

of work.

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eoM"" /

STNNLESS STEEL GUICE ----l

UPPER GUIDE PLAT,E

STAINLESS STEEL"""" GUIDE

FLOOR LEVEL

LOWER GUIDE PL.ATE

GUIDE PLATES FinED TO AFT DOOR FRAME SHOWN

GUIDE PLATES FinED TO FORWARD DOOR FRAME ARE SIMIL.AR

Location of Passenger Door Upper and Lower Guide Plates

Figure 1

ORIGINAL ISSUE: SEP 15/09

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CROSS DRILLED

-HOLES

POSITION PROBE AT THIS POINT

TO SET 8ACKWALLECHO

LOWER GUIDE PLATE

UPPER GUIDE PLATE

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GUIDE PLATES FITTED TO AFT DOOR FRAME SHOWN

GUIDE PLATES FITTED TO FORWARD DOOR FRAME ARE SIMILAR

Scan Areas - Upper and Lower Guide Plates

Figure 2

ORIGINAL ISSUE: SEP 15/09

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lYPlCAL

EXFQlAiJ(rIl

CQRROSlON

EO<} I

BACKWAll ECHO

-

•••••

"

L l1lIL

"Xl

80

60

40

20

o

o 2 3

•

5 6 7

•

9 10

GATE 2 THRESHOLD

SET AT 60 PER CENT

FULL SCREEN HEIGHT

GATE 1 THRESHOLD

SET AT 10 PER CENT

FULL SCREEN HEIGHT

0.35"

(9119119)

I

I

0.43"

(11rrm)

rl

~=r

U

0.31"'

(8mm)

0.39"

(1Orrm)

Krautkramer 5MHz, 0 degree contact probe

Part number K5K from GE lnsoectian

TypicaJ Screen Display and Ultrasonic Probe

Figure 3

ORIGINAL ISSUE: SEP 15/09

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BAE SYSTEMS

ACCOMPLISHMENT REPORT

I SERVICE BULLETIN NUMBER 1 J_4_1-_5_2_-0_6_4 _

TITLE: DOORS -INTRODUCTION OF ULTRASONIC INSPECTION OF THE UPPER AND

LOWER PASSENGER/CREW DOOR PIN GUIDES

TO: THE PUBLICATIONS CONTROL TEAM,

AIRCRAFT MAINTENANCE & PUBLICATION SERVICES,

BAE SYSTEMS,

PRESTWICK INTERNATIONAL AIRPORT,

AYRSHIRE, KA9 2RW,

SCOTLAND.

Telephone:

Fax:

E-mail:

(01292) 675207

(01292) 675704

RAPublications@baesystems.com

PLEASE BE ADVISED THAT THE ABOVE SERVICE BULLETIN HAS BEEN EMBODIED ON

AIRCRAFT CONSTRUCTORS NUMBER(S):

WE REQUEST THE APPROPRIATE REVISIONS TO APPLICABLE MANUALS.

NAME: .

SIGNED: .

COMPANY: .

DATE: . .

SERVICE BULLETIN COMMENTS/FEEDBACK

Please report any non-technical comments or inaccuracies regarding this service bulletin to the

above address.

BAE SYSTEMS (Operations) limited.

Printed In the U.K.