SERD.pdf

SUPPORT EQUIPMENT

RECOMMENDATION

DATA (SERD)

FIGURE 1a

PART I – FUNCTIONAL ANALYSIS

SERD NUMBER SE NOMENCLATURE/PART NO.

130477

REFERENCE STANDARD, EDDY CURRENT

PN: 17G130428-501

CONTRACTOR/CAGE: THE BOEING COMPANY/88277

CONTRACT NO.: F33657-01-C-2002

END ARTICLE IDENT: C-17 AIRCRAFT

PAGE NO.: 1 OF 4

REVISION NO.: ORIGINAL

DATE: 04 JUNE 2002

THE C-17 THE NOSE LANDING GEAR (NLG) WHEEL REQUIRES FREQUENT TIRE CHANGES. THE

CURRENT NLG WHEEL WAS DESIGNED BY ALLIED SIGNAL AND A NEW DESIGN IS BEING INTRO-

DUCED BY MESSIER – BUGATTI. THE NEW DESIGN COMES WITH A DIFFERENT BEAD SEAT CON-

FIGURATION. EXIS TING NON DESTRUCTIVE TEST SUPPORT EQUIPMENT (REFERENCE STANDARD

SERD 130428, PN 17G130428-1 AND PROBE KIT SERD 130427, PN 17G130427-1) DESIGNED FOR

THE ALLIED SIGNAL NLG WHEEL WILL NOT FIT THE NEW MESSIER – BUGATTI DESIGN.

DURING THE LIFE OF THE C-17 AIRCRAFT THE WHEEL MAY EXPERIENCE DAMAGE. THE DAMAGE

RANGES FROM STRUCTURAL FATIGUE TO IMPACT BY A FOREIGN OBJECT, REJECTED TAKE OFF

OR HARD LANDING. THIS DAMAGE IS PRIMARILY DUE TO CRACKS IN THE WHEEL BEAD SEAT

AREA.

DAMAGE ASSESSMENT REQUIRES NONDESTRUCTIVE EVALUATION (NDE) TO DETERMINE THE

EXISTENCE AND EXTENT OF PROBABLE DAMAGE. AN NDE METHOD CURRENTLY EXISTS FOR

THE ALLIED SIGNAL NLG THAT IS CAPABLE OF DETECTING AND MEASURING THE SIZE AND LOCA-

TION OF SUSPECTED DAMAGE FOR THAT WHEEL.

THE BEAD SEAT IS INSPECTED FOR CRACKS WHENEVER THE TIRE IS BROKEN DOWN AND JUST

PRIOR TO RE-ASSEMBLY. THE WHEEL IS INSPECTED USING AN EDDY CURRENT TEST. THIS IN-

SPECTION METHOD USES A SMALL AC COIL TO INDUCE AN ELECTRIC CURRENT INTO THE SUR-

FACE OF THE ALUMINUM WHEEL. THIS INDUCED CURRENT IN TURN CREATES A MAGNETIC FIELD

THAT IS BALANCED AGAINST THE FIELD IN THE COIL. WHEN A CRACK OR CHANGE IN STRUC-

TURE IS PRESENT, THE FIELD IS DISRUPTED AND AN UNBALANCED CONDITION IS DETECTED.

THE INSPECTION IS CAPABLE OF DETECTING FLAWS 0.03-INCH RADIUS AND GREATER WITHOUT

THE REMOVAL OF SURFACE PAINT OR PROTECTIVE SURFACE TREATMENTS. IT CAN BE PER-

FORMED BY HAND TO PROVIDE DETAILED INFORMATION CONCERNING THE INTEGRITY OF THE

NOSE LANDING GEAR WHEEL BEAD SEAT SURFACE.

EDDY CURRENT INSPECTION USES A REFERENCE STANDARD OF THE SAME OR SIMILAR MATE-

RIAL AND CONFIGURATION TO ESTABLISH THE CALIBRATION SENSITIVITY OF THE EDDY CUR-

RENT INSTRUMENT. GENERALLY A SURPLUSED PIECE OF HARDWARE IS MADE INTO A REFER-

ENCE STANDARD TO SUPPORT THE CALIBRATION OF THE EQUIPMENT USED IN THE INSPECTION.

BOTH THE MAIN LANDING GEAR WHEEL REFERENCE STANDARD (SERD 130423, PN 17G130423 -1) AND THE NOSE LANDING GEAR WHEEL REFERENCE STANDARD (SERD 130428, PN 17G130428 -1)

ARE FABRICATED FROM ALLIED SIGNAL C-17 WHEELS. THEY WERE DESIGNED TO INSPECT THE

BEAD SEAT AREA. THE NEW NOSE WHEELS DESIGNED BY MESSIER-BUGATTI HAVE A DIFFERENT

BEAD SEAT DESIGN REQUIRING A CHANGE IN THE EDDY CURRENT PROBE AND REFERENCE

STANDARD PROFILE.

PART NO.: 17G133427-501

CONTRACTOR/CAGE: THE BOEING COMPANY/88277

SERD NO.: 130477

PAGE NO.: 2 OF 4

REVISION NO.: ORIGINAL

DATE: 04 JUNE 2002

PART I FUNCTIONAL ANALYSIS (CONTINUED)

A MEANS IS REQUIRED AT THE INTERMEDIATE AND DEPOT LEVELS OF MAINTENANCE, TO PER-

FORM EDDY CURRENT INSPECTION OF MESSIER-BUGATTI NOSE LANDING GEAR WHEELS. THE

MEANS MUST PROVIDE A WAY OF CALIBRATING THE EDDY CURRENTS EQUIPMENT USED FOR

TESTING.

THE MEANS WILL BE USED IN CONJUNCTION WITH THE EDDYSCOPE (PN NORTEC19EII) CON-

TAINED IN THE METAL FLAW DETECTOR (PN 19EIISPO3196, SERD 130430). IT IS ALSO USED IN CONJUNCTION WITH THE EDDY CURRENT PROBE KIT (PN 17G133476-1, SERD 130476) TO PRO-

VIDE PROPER CALIBRATION OF THE INSTRUMENT SYSTEM.

PART II - RECOMMENDED SOLUTION

THE NEWLY DEVELOPED CONTRACTOR FURNISHED EDDY CURRENT REFERENCE STANDARD

P/N 17G130428-501 OR EQUIVALENT IS RECOMMENDED TO SATISFY THE REQUIREMENTS OF

THE PART I - FUNCTIONAL ANALYSIS. THE REFERENCE STANDARD CONSISTS OF AN INDIVIDUAL

SECTION OF A NLG WHEEL HALF THAT HAS BEEN MACHINED (EDM) WITH NOTCHES TO REPRE-

SENT ARTIFICIAL FLAWS.

THE BASIC COMPONENTS REQUIRED TO PERFORM AN NDE INSPECTION CONSIST OF THE ED-

DYSCOPE (NORTEC19EII), AN EDDY CURRENT PROBE KIT, AND THE NLG EDDY CURRENT REF-

ERENCE STANDARD. THE REFERENCE STANDARD CONTAINS 0.03” RADIUS NOTCHES THAT ARE

DETECTABLE BY THE EDDYSCOPE AND PROBE KIT.

NOTES:

A. SE DESCRIPTION

SIZE: 12" L X 12" W X 9" H

WEIGHT: 25 LB

MATERIAL: ALUMINUM.

COLOR: GRAY

OPERATING TEMPERATURE -40? F TO 150? F

B. MIL-HDBK-300 WAS UTILIZED IN THE SELECTION OF THE SE DOCUMENTED HEREIN. NO ITEM

PRESENTLY IN GOVERNMENT INVENTORY WILL FULFILL THE ABOVE NOTED REQUIREMENTS.

B. THIS ITEM WILL BE DEVELOPED UNDER THE PIP (PROJECT IMPLEMENTATION PLAN) 2001-533.

FUNCTION:

SETUP THE EDDYSCOPE FOR AN NDT INSPEC-

TION OF NLG WHEELS CONSTRUCTED OF

FORGED ALUMINUM.

OPERATION:

1. TURN ON INSTRUMENT, ALLOW WARM UP

TIME AND CONNECT PROBE.

2. ALLOW TIME FOR AUTOMATIC SETUP.

3. POSITION PROBE ON "GOOD" AREA OF THE

STANDARD.

4. ADJUST INSTRUMENT IN ACCORDANCE WITH

THE 1C-17A-36 MANUAL.

5. POSITION PROBE ON THE REQUIRE REFER-

ENCE NOTCH OF THE STANDARD.

6. ADJUST INSTRUMENT IN ACCORDANCE WITH

THE 1C-17A-36 MANUAL.

7. PLACE PROBE ON GOOD AREA OF THE LRU

AND NULL INSTRUMENT.

8. FINE ADJUST METAL FLAW DETECTOR DIS-

PLAY.

9. SCAN SUSPECTED DAMAGE AREA OF LRU.

SE DESCRIPTION:

SIZE: 12” L X12” W X 9” H

WEIGHT: 25 LB.

MATERIAL: ALUMINUM

FINISH: GRAY

OPER TEMP: -40? F TO 150? F

ITEM NO: 130477

MAINTENANCE LEVEL

CONCEPT ONLY ORGANIZATIONAL INTERMEDIATE DEPOT

X

THE BOEING COMPANY NAME: REFERENCE STANDARD, EDDY CURRENT PAGE: 3 OF 4

PART NO:

17G130428-501

BEAD SEAT

PROBE POSITION

FOR SCANNING

BEAD SEAT

REFERENCE STANDARD

TUBE WELL

SUPPORT EQUIPMENT RECOMMENDATION DATA (SERD)

Form Revision Date: 14 Nov 2001

DATE

04 JUNE 2002

33c

PAGE

33e

MODEL DESIGNATION AND NAME OF END ARTICLE

3. C-17 AIRCRAFT

1. CONTRACTOR

THE BOEING COMPANY

88277

2. CONTRACT NO.

F33657-01-C-2002

26.INSTAL.

SIGNIF

REV NO.

ORIGINAL

33d

4. NOMENCLATURE

REFERENCE STANDARD, EDDY CURRENT

23 CALIBRATION

NO

28. CRITICAL

ENG ___ PROC ___

27. ARTICLE REQUIRING SUPPORT 34. NATIONAL STOCK NUMBER 33a/33b 21.

ITEM 27a ML/MC 27b PART # & NOMEN 27c CMRS CAGE MATCH

NO.

C20536000 ASSY

A36031 INNER

A36032 OUTER

FSC NCB NIIN PART OR DRAWING NO. CODE

130477 I

NLG WHEEL

NO 6635 NC Z02-2732 CAGE: 88277 (BOEING)

PN: 17G130428-501

25. SMR

CODE

30. REASON FOR DELETION

/SUPERSEDE DATA

12. PROPOSED

SOURCE

36. EST. DATE

1ST ARTICLE

37. EST PROD

LEAD TIME

32. DATE OF

APPROVAL

DATE

REQ’D

DEV. COST

38. (EST)

END ITEM

EFFECTIVITY

PFOFFU CFE SEE NOTE 4 SEE NOTE 4 SEE NOTE 5

C-17A

1 & UP

REMARKS: 1. LCN: C0909 2. WCC: 3170 3. T.O: 1C-17A-4-4

4. THE ESTIMATED LEAD TIME FOR PROTOTYPE SE DEVELOPMENT IS 13 MONTHS AND 11 MONTHS FOR A PRODUCTION UNIT.

5. THIS ITEM WILL BE DEVELOPED UNDER THE PIP 2001-533 (PROJECT IMPLEMENTATION PLAN).

31.

39/44 ORGANIZATIONAL REQUIREMENTS 41.TOTAL 40.UNIT 42.TOTAL 43.TOTAL

LOM O I UDM TRC ENR FLT

TEST

ATC

TRNG

45 DAY/16

A/C DEPLOY

RECOM’D

QTY

COST

(EST) ORDER COST

(EST)

AIR

VEHICLES

1 1 $3,000

DELTA

FOR 32

AIR

VEHICLES

Distribution authorized to US Government agencies only.

Test & Evaluation 1989 Other requests for this document must be referred to ASC/YC(SS)

DESTRUCTION NOTICE – Destroy by any method that will prevent dis-closure of contents or reconstruction of the document

FIGURE 1b