Commercial 

Airplanes DC8

Service Bulletin

ALERT

Number: DC8-57A103

Original Issue: May 05, 2010

ATA System: 5710

SUBJECT: WINGS - Wing Structure - Inspect/Repair Left and Right Wing Center Spar Lower Spar

Cap at Stations Xrs=168.00, Xrs=251.00 and Xrs=358.00

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persons from specific countries. The controller of this data has the individual responsibility to abide by all export

laws.

ECCN: 9E991

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Unpublished Work - All Rights Reserved

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This document includes proprietary information owned by The Boeing Company and/or one or more third parties.

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2.0
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BLANK PAGE
Table of Contents

Summary ...................................................... 5

1. PLANNING INFORMATION ........................................ 9

A. Effectivity ................................................ 9

1. Airplanes ............................................. 9

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

1. Existing Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

2. Data supplied with this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . . . . . . 34

3. Installation Drawings Used in the Preparation of this Service Bulletin . . . . . . . . . . . . 34

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 37

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 37

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 48

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 49

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 51

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 51

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52

FIGURE 1: INSPECT THE LEFT AND RIGHT WING CENTER SPAR - EDDY CURRENT, HIGH

FREQUENCY INSPECTION METHOD . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56

FIGURE 2: INSPECT THE LEFT AND RIGHT WING CENTER SPAR -EDDY CURRENT, LOW FREQUENCY

INSPECTION METHOD . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 60

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BLANK PAGE
Commercial 

Airplanes DC8

Service Bulletin

ALERT

Summary Number: DC8-57A103

Original Issue: May 05, 2010

ATA System: 5710

SUBJECT: WINGS - Wing Structure - Inspect/Repair Left and Right Wing Center Spar Lower Spar

Cap at Stations Xrs=168.00, Xrs=251.00 and Xrs=358.00

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH

1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OWNER.

CONCURRENT REQUIREMENTS

None.

BACKGROUND

Boeing has been advised that cracks in the center spar lower cap and in some cases, the web of the spar, have

been found at stations Xrs=168.00, Xrs=251.00 and Xrs=358.00. These cracks originate in the most inboard

fastener hole of the access opening doublers. A total of 12 cracks have been found in airplanes with between

26,121 and 50,136 landings, and appear to be consistent with fatigue cracks. This service bulletin provides

instructions to inspect these areas to determine if these cracks are present, and accomplish a repair, if required.

If not corrected, these cracks can compromise the structural integrity of the wing structure.

ACTION

OPTION 1

1. This service bulletin provides instructions to conduct an Eddy Current, High Frequency Inspection in the

area of the inboard fastener of the access opening doubler on the left and right wing center spar lower cap

in three specfic areas to locate any cracks, and do as follows:

CONDITION 1 (No Crack Found)

a. Repetitively inspect for cracks at specific intervals.

CONDITION 2 (Crack Found at Station Xrs=168.00, Left and/or Right Wing)

a. Repairs the crack.

b. Inspects the repair at specific intervals.

c. Repetitively inspects the non-repaired locations at specific intervals.

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CONDITION 3 (Crack Found at Station Xrs=251.00, Left and/or Right Wing)

a. Repairs the crack.

b. Inspects the repair at specific intervals.

c. Repetitively inspects the non-repaired locations at specific intervals.

CONDITION 4 (Crack Found at Station Xrs=358.00, Left and/or Right Wing)

a. Repairs the crack.

b. Inspects the repair at specific intervals.

c. Repetitively inspects the non-repaired locations at specific intervals.

OPTION 2

1. This service bulletin provides instructions to conduct an Eddy Current, Low Frequency Inspection of the

center spar lower cap in three specific areas of the left and right wing center spar to locate any cracks, and

do as follows:

CONDITION 1 (No Crack Found)

a. Repetitively inspect for cracks at specific intervals.

CONDITION 2 (Crack Found at Station Xrs=168.00, Left and/or Right Wing)

a. Repairs the crack.

b. Inspects the repair at specific intervals.

c. Repetitively inspects the non-repaired locations at specific intervals.

CONDITION 3 (Crack Found at Station Xrs=251.00, Left and/or Right Wing)

a. Repairs the crack.

b. Inspects the repair at specific intervals.

c. Repetitively inspects the non-repaired locations at specific intervals.

CONDITION 4 (Crack Found at Station Xrs=358.00, Left and/or Right Wing)

a. Repairs the crack.

b. Inspects the repair at specific intervals.

c. Repetitively inspects the non-repaired locations at specific intervals.

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ALERT ALERT
EFFECTIVITY

All DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, DC-8-43, DC-8-51, DC-8-52,

DC-8-53, DC-8-55, DC-8-61, DC-8-61F, DC-8-62, DC-8-62F, DC-8-63, DC-8-63F, DC-8-71, DC-8-71F, DC-8-72,

DC-8-72F, DC-8-73, DC-8-73F, DC-8F-54, DC-8F-55 Airplanes. Refer to Paragraph 1.A.1., Airplanes, for the

list of affected airplanes.

COMPLIANCE

Refer to Paragraph 1.E., Compliance.

Federal Aviation Administration (FAA) Airworthiness Directive 2008-25-05 is related to this service bulletin.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the inspection and/or repair procedures given in this service

bulletin.

MANPOWER

Refer to Paragraph 1.G., Manpower.

MATERIAL INFORMATION

Operator Supplied Parts/Materials.

Refer to Paragraph 2.A., Material - Price and Availability

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Commercial 

Airplanes DC8

Service Bulletin

ALERT

Number: DC8-57A103

Original Issue: May 05, 2010

ATA System: 5710

SUBJECT: WINGS - Wing Structure - Inspect/Repair Left and Right Wing Center Spar Lower Spar

Cap at Stations Xrs=168.00, Xrs=251.00 and Xrs=358.00

THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH

1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO

THE NEW OWNER.

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

This service bulletin is for the airplanes shown below.

GROUP CONFIGURATION DESCRIPTION

1 - DC-8 airplanes in PSE population 'D'

2 - DC-8 airplanes in PSE population 'E'

Airplane Models:

DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8-32, DC-8-33, DC-8-41, DC-8-42, DC-8-43,

DC-8-51, DC-8-52, DC-8-53, DC-8-55, DC-8-61, DC-8-61F, DC-8-62, DC-8-62F, DC-8-63,

DC-8-63F, DC-8-71, DC-8-71F, DC-8-72, DC-8-72F, DC-8-73, DC-8-73F, DC-8F-54, DC-8F-55

Fuselage Num- Group

ber

1 1

10 1

100 - 109 1

11 1

110 - 119 1

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Fuselage Num- Group

ber

12 1

120 - 129 1

13 1

130 - 139 1

14 1

140 - 149 1

15 1

150 - 159 1

16 1

160 - 169 1

17 1

170 - 179 1

18 1

180 - 189 1

19 1

190 - 199 1

2 1

20 1

200 - 209 1

21 1

210 - 219 1

22 1

220 - 229 1

23 1

230 - 239 1

24 1

240 - 249 1

25 1

250 - 259 1

26 1

260 - 269 1

27 1

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Fuselage Num- Group

ber

270 - 279 1

28 1

280 - 289 1

29 1

290 - 297 1

298 2

299 1

3 1

30 1

300 - 306 1

307 2

308 1

309 2

31 1

310 - 318 1

319 2

32 1

320 - 321 1

322 - 323 2

324 - 329 1

33 1

330 - 332 1

333 2

334 1

335 2

336 - 339 1

34 1

340 - 346 1

347 - 348 2

349 1

35 1

350 - 359 1

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Fuselage Num- Group

ber

36 1

360 1

361 2

362 - 369 1

37 1

370 - 375 1

376 - 377 2

378 1

379 2

38 1

380 - 389 1

39 1

390 - 399 1

4 1

40 1

400 - 406 1

407 2

408 - 409 1

41 1

410 - 416 1

417 2

418 - 419 1

42 1

420 - 426 1

427 - 428 2

429 1

43 1

430 - 436 1

437 - 438 2

439 1

44 1

440 - 442 1

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Fuselage Num- Group

ber

443 2

444 - 449 1

45 1

450 - 457 1

458 2

459 1

46 1

460 - 462 1

463 2

464 1

465 2

466 1

467 2

468 1

469 2

47 1

470 - 479 1

48 1

480 - 486 1

487 2

488 - 489 1

49 1

490 1

491 2

492 - 499 1

5 1

50 1

500 - 508 1

509 2

51 1

510 - 515 1

516 2

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Fuselage Num- Group

ber

517 - 519 1

52 1

520 - 522 1

523 2

524 - 529 1

53 1

530 - 534 1

535 2

536 - 538 1

539 2

54 1

540 - 541 1

542 2

543 - 545 1

546 2

547 - 549 1

55 1

550 1

551 2

552 - 553 1

554 - 555 2

556 1

56 - 59 1

6 1

60 - 69 1

7 1

70 - 79 1

8 1

80 - 89 1

9 1

90 - 99 1

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ALERT ALERT
2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

Boeing has been advised that cracks in the center spar lower cap and in some cases, the web of the

spar, have been found at stations Xrs=168.00, Xrs=251.00 and Xrs=358.00. These cracks originate in

the most inboard fastener hole of the access opening doublers. A total of 12 cracks have been found

in airplanes with between 26,121 and 50,136 landings, and appear to be consistent with fatigue cracks.

This service bulletin provides instructions to inspect these areas to determine if these cracks are present,

and accomplish a repair, if required. If not corrected, these cracks can compromise the structural

integrity of the wing structure.

D. Description

OPTION 1 (Eddy Current, High Frequency Inspection)

1. This service bulletin provides instructions to conduct an Eddy Current, High Frequency Inspection

in the area of the inboard fastener of the access opening doubler on the left and right wing center

spar lower cap in three specfic areas to locate any cracks, and do as follows:

CONDITION 1 (No Crack Found)

a. Repetitively inspect for cracks at specific intervals.

CONDITION 2 (Crack Found at Station Xrs=168.00, Left and/or Right Wing)

a. Repairs the crack.

b. Inspects the repair at specific intervals.

c. Repetitively inspects the non-repaired locations at specific intervals.

CONDITION 3 (Crack Found at Station Xrs=251.00, Left and/or Right Wing)

a. Repairs the crack.

b. Inspects the repair at specific intervals.

c. Repetitively inspects the non-repaired locations at specific intervals.

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ALERT ALERT
CONDITION 4 (Crack Found at Station Xrs=358.00, Left and/or Right Wing)

a. Repairs the crack.

b. Inspects the repair at specific intervals.

c. Repetitively inspects the non-repaired locations at specific intervals.

OPTION 2 (EDDY CURRENT, LOW FREQUENCY INSPECTION)

1. This service bulletin provides instructions to conduct an Eddy Current, Low Frequency Inspection

of the center spar lower cap in three specific areas of the left and right wing center spar to locate

any cracks, and do as follows:

CONDITION 1 (No Crack Found)

a. Repetitively inspect for cracks at specific intervals.

CONDITION 2 (Crack Found at Station Xrs=168.00, Left and/or Right Wing)

a. Repairs the crack.

b. Inspects the repair at specific intervals.

c. Repetitively inspects the non-repaired locations at specific intervals.

CONDITION 3 (Crack Found at Station Xrs=251.00, Left and/or Right Wing)

a. Repairs the crack.

b. Inspects the repair at specific intervals.

c. Repetitively inspects the non-repaired locations at specific intervals.

CONDITION 4 (Crack Found at Station Xrs=358.00, Left and/or Right Wing)

a. Repairs the crack.

b. Inspects the repair at specific intervals.

c. Repetitively inspects the non-repaired locations at specific intervals.

The work in this service bulletin is done in the maintenance zone(s) given below.

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ALERT ALERT
Group 1:

Affected Maintenance Zones

Model Zone

DC-8-11, DC-8-12, DC-8-21, 117, 123

DC-8-31, DC-8-32, DC-8-33,

DC-8-41, DC-8-42, DC-8-43,

DC-8-51, DC-8-52, DC-8-53,

DC-8-55, DC-8-61, DC-8-61F,

DC-8-62, DC-8-62F, DC-8-63,

DC-8-63F, DC-8-71, DC-8-71F,

DC-8-72, DC-8-73, DC-8-73F,

DC-8F-54, DC-8F-55

Group 2:

Affected Maintenance Zones

Model Zone

DC-8-62, DC-8-62F, DC-8-63, 117, 123

DC-8-72, DC-8-72F

E. Compliance

TABLE 1, GROUP 1, OPTION 1 (EDDY CURRENT, HIGH FREQUENCY INSPECTION (ETHF) - INSPECT CENTER SPAR CAP

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

20,000 total landingsInspect the area of the

inboard fastener of the

access opening doubler

on the left and right wing

center spar lower cap at

stations Xrs=168.00,

Xrs=251.00 and

Xrs=358.00 for cracks

using Eddy Current, High

Frequency Inspection in

accordance with Work Instructions, Paragraph

3.B.

All Airplanes

or

3,000 landings

from the original issue date of this

service bulletin

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ALERT ALERT
TABLE 1, GROUP 1, OPTION 1 (EDDY CURRENT, HIGH FREQUENCY INSPECTION (ETHF) - INSPECT CENTER SPAR CAP

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

Inspect the area of the 6,000 landings

inboard fastener of the

access opening doubler

on the left and right wing

center spar lower cap at

stations Xrs=168.00,

Xrs=251.00 and

Xrs=358.00 for cracks

using Eddy Current, High

Frequency Inspection in

accordance with Work Instructions, Paragraph

3.B.

Condition 1

No Crack(s) Found

Repair crack(s) in accor- Before further flight

dance with Work Instructions, Paragraph 3.B.

Option 1(ETHF)

Condition 2

Crack Found at Station Xrs

= 168.00, Left and/or Right

Wing AND

Inspect the non-repaired 6,000 landings

area of the inboard fastener of the access opening

doubler on the left and

right wing center spar

lower cap at stations

Xrs=168.00, Xrs=251.00

and Xrs=358.00 for

cracks using Eddy Current, High Frequency Inspection in accordance

with Work Instructions,

Paragraph 3.B.

AND

Within 15,200 2,100 landings

landings after repair

Inspect the repair at station Xrs =168.00 left

and/or right wing using

the inspection defined in

DC-8 SID, Volume II,

Chapter 57-10-06,

Method 101 for the length

of the repair.

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ALERT ALERT
TABLE 1, GROUP 1, OPTION 1 (EDDY CURRENT, HIGH FREQUENCY INSPECTION (ETHF) - INSPECT CENTER SPAR CAP

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

Before further

flight.

Repair crack(s) in accordance with Work Instructions, Paragraph 3.B.Condition 3

Crack Found at Station Xrs

= 251.00, Left and/or Right

Wing AND

Inspect the non-repaired 6,000 landings

area of the inboard fastener of the access opening

doubler on the left and

right wing center spar

lower cap at stations

Xrs=168.00, Xrs=251.00

and Xrs=358.00 for

cracks using Eddy Current, High Frequency Inspection in accordance

with Work Instructions,

Paragraph 3.B.

AND

Within 15,200 2,100 landings

landings after repair

Inspect the repair at station Xrs= 251.000 left

and/or right wing using

the inspection defined in

DC-8 SID, Volume II,

Chapter 57-10-06,

Method 101 for the length

of the repair.

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ALERT ALERT
TABLE 1, GROUP 1, OPTION 1 (EDDY CURRENT, HIGH FREQUENCY INSPECTION (ETHF) - INSPECT CENTER SPAR CAP

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

Repair crack(s) in accor- Before further flight

dance with Work Instructions, Paragraph 3.B.

Condition 4

Crack Found at Station Xrs

= 358.00 Left and/or Right

Wing AND

Inspect the non-repaired 6,000 landings

area of the inboard fastener of the access opening

doubler on the left and

right wing center spar

lower cap at stations

Xrs=168.00, Xrs=251.00

and Xrs=358.00 for

cracks using Eddy Current, High Frequency Inspection in accordance

with Work Instructions,

Paragraph 3.B.

AND

Within 7,600 land- 1,400 landings

ings after repair

Inspect the repair at station Xrs=358.00 left

and/or right wing using

the inspections defined in

DC-8 SID, Volume II,

Chapter 57-10-16,

Method 101, for the

length of the repair, and

DC-8 SID, Volume II,

Chapter 57-10-16,

Method 104 at the end of

the spar cap repair at the

end four fasteners.

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BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT
TABLE 2, GROUP 1, OPTION 2 (EDDY CURRENT, LOW FREQUENCY INSPECTION (ETLF)) - INSPECT CENTER SPAR CAP

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

20,000 total landingsInspect the left and right

wing center spar lower

cap at stations

Xrs=168.00, Xrs=251.00

and Xrs=358.00 for

cracks in the spar cap

using Eddy Current, Low

Frequency in accordance

with Work Instructions,

Paragraph 3.B.

All Airplanes

or

3,000 landings

from the original issue date of this

service bulletin

Inspect the left and right 1,750 landings

wing center spar lower

cap at stations

Xrs=168.00, Xrs=251.00

and Xrs=358.00 for

cracks in the spar cap

using Eddy Current, Low

Frequency in accordance

with Work Instructions,

Paragraph 3.B.

Condition 1

No Crack(s) Found

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BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT
TABLE 2, GROUP 1, OPTION 2 (EDDY CURRENT, LOW FREQUENCY INSPECTION (ETLF)) - INSPECT CENTER SPAR CAP

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

Repair crack(s) in accor- Before further flight

dance with Work Instructions, Paragraph 3.B.

Crack Found at Station Xrs

= 168.00, Left and/or Right

Wing

AND

Inspect the non-repaired 1,750 landings

left and right wing center

spar lower cap at stations

Xrs=168.00, Xrs=251.00

and Xrs=358.00 for

cracks in the spar cap

using Eddy Current, Low

Frequency in accordance

with Work Instructions,

Paragraph 3.B.

AND

Within 15,200 2,100 landings

landings after repair

Inspect the repair at station Xrs=168.00 left

and/or right wing using

the inspection defined in

DC-8 SID, Volume II,

Chapter 57-10-06,

Method 101 for the length

of the repair.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: May 05, 2010

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22 of 62

BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT
TABLE 2, GROUP 1, OPTION 2 (EDDY CURRENT, LOW FREQUENCY INSPECTION (ETLF)) - INSPECT CENTER SPAR CAP

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

Repair crack(s) in accor- Before further flight

dance with Work Instructions, Paragraph 3.B.

Crack Found at Station Xrs

= 251.00, Left and/or Right

Wing

AND

Inspect the non-repaired 1,750 landings

left and right wing center

spar lower cap at stations

Xrs=168.00, Xrs=251.00

and Xrs=358.00 for

cracks in the spar cap

using Eddy Current, Low

Frequency in accordance

with Work Instructions,

Paragraph 3.B.

AND

Within 15,200 2,100 landings

landings after repair

Inspect the repair at station Xrs=251.00 left

and/or right wing using

the inspection defined in

DC-8 SID, Volume II,

Chapter 57-10-06,

Method 101 for the length

of the repair.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: May 05, 2010

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23 of 62

BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT
TABLE 2, GROUP 1, OPTION 2 (EDDY CURRENT, LOW FREQUENCY INSPECTION (ETLF)) - INSPECT CENTER SPAR CAP

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

Repair crack(s) in accor- Before further flight

dance with Work Instructions, Paragraph 3.B.

Condition 4

Crack Found at Station

358.00 Left and/or Right

Wing AND

Inspect the non-repaired 1,750 landings

left and right wing center

spar lower cap at stations

Xrs=168.00, Xrs=251.00

and Xrs=358.00 for

cracks in the spar cap

using Eddy Current, Low

Frequency in accordance

with Work Instructions,

Paragraph 3.B.

AND

Within 7,600 land- 1,400 landings

ings after repair

Inspect the repair at station Xrs=358.00 left

and/or right wing using

the inspections defined in

DC-8 SID, Volume II,

Chapter 57-10-16,

Method 101, for the

length of the repair, and

DC-8 SID, Volume II,

Chapter 57-10-16,

Method 104 at the end of

the spar cap repair at the

end four fasteners.

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Original Issue: May 05, 2010

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BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT
TABLE 3, GROUP 2, OPTION 1 (EDDY CURRENT, HIGH FREQUENCY INSPECTION (ETHF) ) - INSPECT CENTER SPAR CAP

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

20,000 total landingsInspect the area of the

inboard fastener of the

access opening doubler

on the left and right wing

center spar lower cap at

stations Xrs=168.00,

Xrs=251.00 and

Xrs=358.00 for cracks

using Eddy Current, High

Frequency Inspection in

accordance with Work Instructions, Paragraph

3.B.

All Airplanes

or

3,000 landings

from the original issue date of this

service bulletin

Inspect the area of the 6,000 landings

inboard fastener of the

access opening doubler

on the left and right wing

center spar lower cap at

stations Xrs=168.00,

Xrs=251.00 and

Xrs=358.00 for cracks

using Eddy Current, High

Frequency Inspection in

accordance with Work Instructions, Paragraph

3.B.

Condition 1

No Crack(s) Found

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Original Issue: May 05, 2010

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25 of 62

BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT
TABLE 3, GROUP 2, OPTION 1 (EDDY CURRENT, HIGH FREQUENCY INSPECTION (ETHF) ) - INSPECT CENTER SPAR CAP

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

Repair crack(s) in accor- Before further flight

dance with Work Instructions, Paragraph 3.B.

Condition 2

Crack Found at Station

X=rs 168.00, Left and/or

Right Wing AND

Inspect the non-repaired 6,000 landings

area of the inboard fastener of the access opening

doubler on the left and

right wing center spar

lower cap at stations

Xrs=168.00, Xrs=251.00

and Xrs=358.00 for

cracks using Eddy Current, High Frequency Inspection in accordance

with Work Instructions,

Paragraph 3.B.

AND

Within 43,000 5,300 landings

landings after repair

Inspect the repair at station Xrs= 168.00 left

and/or right wing using

the inspection defined in

DC-8 SID, Volume II,

Chapter 57-10-06,

Method 101 for the length

of the repair.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: May 05, 2010

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26 of 62

BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT
TABLE 3, GROUP 2, OPTION 1 (EDDY CURRENT, HIGH FREQUENCY INSPECTION (ETHF) ) - INSPECT CENTER SPAR CAP

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

Before further

flight.

Repair crack(s) in accordance with Work Instructions, Paragraph 3.B.Condition 3

Crack Found at Station Xrs

= 251.00, Left and/or Right

Wing AND

Inspect the non-repaired 6,000 landings

area of the inboard fastener of the access opening

doubler on the left and

right wing center spar

lower cap at stations

Xrs=168.00, Xrs=251.00

and Xrs=358.00 for

cracks using Eddy Current, High Frequency Inspection in accordance

with Work Instructions,

Paragraph 3.B.

AND

Within 43,000 5,300 landings

landings after repair

Inspect the repair at station Xrs=251.00 left

and/or right wing using

the inspection defined in

DC-8 SID, Volume II,

Chapter 57-10-06,

Method 101 for the length

of the repair.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: May 05, 2010

DC8-57A103

27 of 62

BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT
TABLE 3, GROUP 2, OPTION 1 (EDDY CURRENT, HIGH FREQUENCY INSPECTION (ETHF) ) - INSPECT CENTER SPAR CAP

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

Repair crack(s) in accor- Before further flight

dance with Work Instructions, Paragraph 3.B.

Condition 4

Crack Found at Station Xrs

= 358.00 Left and/or Right

Wing AND

Inspect the non-repaired 6,000 landings

area of the inboard fastener of the access opening

doubler on the left and

right wing center spar

lower cap at stations

Xrs=168.00, Xrs=251.00

and Xrs=358.00 for

cracks using Eddy Current, High Frequency Inspection in accordance

with Work Instructions,

Paragraph 3.B.

AND

Within 21,600 4,100 landings

landings after repair

Inspect the repair at station Xrs=358.00 left

and/or right wing using

the inspections defined in

DC-8 SID, Volume II,

Chapter 57-10-16,

Method 101, for the

length of the repair, and

DC-8 SID, Volume II,

Chapter 57-10-16,

Method 104 at the end of

the spar cap repair at the

end four fasteners.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: May 05, 2010

DC8-57A103

28 of 62

BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT
TABLE 4, GROUP 2, OPTION 2 (EDDY CURRENT, LOW FREQUENCY INSPECTION (ETLF))- INSPECT CENTER SPAR CAP

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

20,000 total landingsInspect the left and right

wing center spar lower

cap at stations

Xrs=168.00, Xrs=251.00

and Xrs=358.00 for

cracks in the spar cap

using Eddy Current, Low

Frequency Inspection in

accordance with Work Instructions, Paragraph

3.B.

All Airplanes

or

3,000 landings

from the original issue date of this

service bulletin

Inspect the left and right 1,750 landings

wing center spar lower

cap at stations

Xrs=168.00, Xrs=251.00

and Xrs=358.00 for

cracks in the spar cap

using Eddy Current, Low

Frequency in accordance

with Work Instructions,

Paragraph 3.B.

Option 2 (Eddy Current,

Low Frequency Inspection

(ETLF))

Condition 1

No Crack(s) Found

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Copyright © Unpublished Work - See page 1 for details.

Original Issue: May 05, 2010

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29 of 62

BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT
TABLE 4, GROUP 2, OPTION 2 (EDDY CURRENT, LOW FREQUENCY INSPECTION (ETLF))- INSPECT CENTER SPAR CAP

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

Repair crack(s) in accor- Before further flight

dance with Work Instructions, Paragraph 3.B.

Option 2 (ETLF)

Condition 2

Crack Found at Station Xrs

= 168.00, Left and/or Right

Wing AND

Inspect the non-repaired 1,750 landings

left and right wing center

spar lower cap at stations

Xrs=168.00, Xrs=251.00

and Xrs=358.00 for

cracks in the spar cap

using Eddy Current, Low

Frequency in accordance

with Work Instructions,

Paragraph 3.B.

AND

Within 43,000 5,300 landings

landings after repair

Inspect the repair at station Xrs= 168.00 left

and/or right wing using

the inspection defined in

DC-8 SID, Volume II,

Chapter 57-10-06,

Method 101 for the length

of the repair.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: May 05, 2010

DC8-57A103

30 of 62

BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT
TABLE 4, GROUP 2, OPTION 2 (EDDY CURRENT, LOW FREQUENCY INSPECTION (ETLF))- INSPECT CENTER SPAR CAP

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

Repair crack(s) in accor- Before further flight

dance with Work Instructions, Paragraph 3.B.

Condition 3 (ETLF)

Crack Found at Station Xrs

= 251.00, Left and/or Right

Wing AND

Inspect the non-repaired 1,750 landings

left and right wing center

spar lower cap at stations

Xrs=168.00, Xrs=251.00

and Xrs=358.00 for

cracks in the spar cap

using Eddy Current, Low

Frequency in accordance

with Work Instructions,

Paragraph 3.B.

AND

Within 43,000 5,300 landings

landings after repair

Inspect the repair at station Xrs= 251.00 left

and/or right wing using

the inspection defined in

DC-8 SID, Volume II,

Chapter 57-10-06,

Method 101 for the length

of the repair.

BOEING PROPRIETARY -

Copyright © Unpublished Work - See page 1 for details.

Original Issue: May 05, 2010

DC8-57A103

31 of 62

BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT
TABLE 4, GROUP 2, OPTION 2 (EDDY CURRENT, LOW FREQUENCY INSPECTION (ETLF))- INSPECT CENTER SPAR CAP

Repeat Interval

(Not to Exceed)

Compliance Time

(Whichever Occurs Later)

Condition Action

Repair crack(s) in accor- Before further flight

dance with Work Instructions, Paragraph 3.B.

Condition 4 (ETLF)

Crack Found at Station Xrs

= 358.00 Left and/or Right

Wing AND

Inspect the non-repaired 1,750 landings

left and right wing center

spar lower cap at stations

Xrs=168.00, Xrs=251.00

and Xrs=358.00 for

cracks in the spar cap

using Eddy Current, Low

Frequency in accordance

with Work Instructions,

Paragraph 3.B.

AND

Within 21,600 4,100 landings

landings after repair

Inspect the repair at station Xrs=358.00 left

and/or right wing using

the inspections defined in

DC-8 SID, Volume II,

Chapter 57-10-16,

Method 101, for the

length of the repair, and

DC-8 SID, Volume II,

Chapter 57-10-16,

Method 104 at the end of

the spar cap repair at the

end four fasteners.

F. Approval

This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified

in this service bulletin comply with the applicable regulations and are FAA approved. This service

bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as

modified by other approved Boeing changes.

If an airplane has a non-Boeing modification or repair that affects a component or system also affected

by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval

before incorporating this service bulletin.

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BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT
In addition, the Manager of the FAA Los Angeles Aircraft Certification Office approves the action (i.e.

inspection or repair) defined in this service bulletin as an alternative method of compliance to the

requirements of paragraphs (i), (i)(1), (i)(2), (j)(1) and (j)(2) and (l) of AD 2008-25-05 with respect to

PSEs 57.08.013/014 and 57.08.035/036. All provisions of AD 2008-25-05 that are not specifically

referenced in the above statement remain fully applicable and must be complied with.

G. Manpower

The table below shows an estimate of the task hours necessary to do this inspection for each airplane.

This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator

task hour data if necessary. The estimate does not include lost time. These are some examples of lost

time:

• Time to adjust to the workplace

• Time to schedule the work

• Time to inspect the work

• Time to cure the materials

• Time to make the parts

• Time to find the tools.

Option 1

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 16.0 8.0

Inspect 1 6.0 6.0

Close Access 2 8.0 4.0

TOTAL FOR EACH AIRPLANE 30.0 18.0

NOTE: Task hours for the repair(s), if required, are not included. Operator's are to estimate the task

hours required based on inspection results.

Option 2

Task Number of Persons Task Hours Elapsed Hours

Inspect 1 6.0 6.0

TOTAL FOR EACH AIRPLANE 6.0 6.0

NOTE: Task hours for the repair(s), if required, are not included. Operator's are to estimate the task

hours required based on inspection results.

H. Weight and Balance Changes

Weight and balance changes affected by incorporation of this service bulletin are contingent upon the

changes to each particular airplane. Weight data is to be computed by the operator by weighing parts

removed and parts installed during this change. Necessary revisions should be made to the appropriate

airplane weight and balance report.

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BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT
I. Electrical Load Data

Not changed.

J. References

1. Existing Data

a. Aircraft Maintenance Manual (AMM) 28-00-0.

b. Nondestructive Testing Standard Practice Manual (NDTSPM) Part 06-10-01.001.

c. Structural Repair Manual (SRM) 51.

d. Supplemental Inspection Document (SID), Volume II, Chapter 57-10-06, 57-10-16.

e. FAA Airworthiness Directive 2008-25-05.

2. Data supplied with this Service Bulletin

No data is supplied with this service bulletin. To obtain the data necessary to support this service

bulletin submit a data request to:

Data and Services Management

MS D800-0019

3855 Lakewood Boulevard

Long Beach, California 90846

Phone: (562) 593-6996

Fax: (562) 593-2001

E-mail: dse.boecom@boeing.com

a. Drawings:

Drawing No Title Sheet DCN/REV ADCN

WING REPAIR - CENTER SPAR CAP AND DWG - D

WEB, DC-8 Xrs = 251.00 SERVICE REWORK DRAWING

SR08570005

SPAR, CENTER, LOWER, WING -DBLR DWG - B

INSTL Xrs =358.000 SERVICE REWORK

DRAWING

SR08570015

WING REPAIR - CENTER SPAR CAP AND DWG - B

WEB, Xrs = 168.00 SERVICE REWORK

DRAWING

SR08570022

3. Installation Drawings Used in the Preparation of this Service Bulletin

Document Number Title Change

SPAR ASSEMBLY - WING, CENTER AS

SPAR

5613192

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BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT
This drawing was used to prepare this service bulletin. This drawing is not necessary to make the

specified changes, and is not supplied with this service bulletin. This drawing may not be applicable

to all airplane configurations or operators.

K. Publications Affected

1. Publications:

None.

2. Damage Tolerance Based Structural Inspections:

Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue

Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the

Maintenance Program. This service bulletin affects FCS. DTI requirements for the structure affected

are contained in Paragraph 1.E., Compliance of this service bulletin.

L. Interchangeability and Intermixability of Parts

Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

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BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT
BOEING PROPRIETARY -

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Original Issue: May 05, 2010

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36 of 62

BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT

BLANK PAGE
2. MATERIAL INFORMATION

A. Material - Price and Availability

None.

B. Industry Support Information

Boeing warranty remedies are not available for the inspection and/or repair procedures given in this

service bulletin.

C. Parts Necessary For Each Airplane

1. Kits/Parts

None.

2. Parts and Materials Supplied by the Operator

NOTE: Parts required are based on inspection results, and should be established by operator.

SERVICE REWORK DRAWING SR08570005, STATION Xrs=251.00, LEFT WING

Part Number/Speci- Name QTY Material Size Notes

fication

SR08570005-3 Doubler 1 .063 x 29.00 x 32.00 Inches (a)

SR08570005-5 Doubler 1 .063 x 5.00 x 20.00 Inches (a)

1/4 x 5.00 x 34.00 Inches, Grain (b)

lengthwise

SR08570005-7 Plate 1

SR08570005-9 Angle 1 31.00 Inches (d) (g)

SR08570005-11 Strap 1 .160 x 2.00 x 35.00 Inches (a)

SR08570005-13 Stiffener 1 2.00 x 4.00 x 29.00 Inches (c)

SR08570005-15 Filler 1 .063 x 2.00 x 5.00 Inches (a)

5/16 x 2.00 x 5.00 Inches, Grain (b)

lengthwise

SR08570005-17 Filler 1

SR08570005-19 Strap 1 .063 x 1.00 x 30.00 Inches (a)

SR08570005-21 Splice 2 .063 x 6.00 x 7.00 Inches (a)

HL328-8 Pin 27 - (e) (h)

MS21042L4 Nut 18 -

3D0006-3 Nut 33 - (f)

3D0006-4 Nut 9 - (f)

HLT428-6 Pin 335 - (e) (h)

HLT425-6 Pin 112 (e) (h)

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BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT
SERVICE REWORK DRAWING SR08570005, STATION Xrs=251.00, LEFT WING

Part Number/Speci- Name QTY Material Size Notes

fication

HL328-6 Pin 83 - (e) (h)

HL329-6 Pin 18 - (e) (h)

NAS1252-10L Washer 515 -

NAS1252-416L Washer 18 -

MS21042L3 Nut 515 -

ALUMINIUM CLAD SHEET, 7075-T6, MATERIAL PER QQ-A-250/13 TEMPER

T-6

(a)

ALUMINIUM PLATE 7075-T651, MATERIAL PER QQ-A-250/12 TEMPER T651(b)

ALUMINIUM BAR, 7075-T7351, MATERIAL PER QQ-A-229/9 TEMPER

T7351

(c)

(d) Part Number 60-3362 Angle, Aluminium Alloy, 7075-T76511

(e) Can be purchased from: Hi-Shear Corporation CAGE

2600 Skypark Drive 73197

Torrance, California 90505

(f) Can be purchased from: The Boeing Company 81205

7755 East Marginal Way South

Seattle, Washington 98108-4002

(g) Can be purchased from: Transtar Metals Corporation 3YWN1

DBA Castle Metals Aerospace

970 West 190th Street Suite 700

Torrance, California 90502

(h) Grip length to be determined on installation.

SERVICE REWORK DRAWING SR08570005, STATION Xrs=251.00, RIGHT WING

Part Number/Speci- Name QTY Material Size Notes

fication

SR08570005-3 Doubler 1 .063 x 29.00 x 32.00 Inches (a)

SR08570005-5 Doubler 1 .063 x 5.00 x 20.00 Inches (a)

1/4 x 5.00 x 34.00 Inches, Grain (b)

lengthwise

SR08570005-8 Plate 1

SR08570005-10 Angle 1 31 Inches (d) (g)

SR08570005-12 Strap 1 .160 x 2.00 x 35.00 Inches (a)

SR08570005-14 Stiffener 1 2.00 x 4.00 x 29.00 Inches (c)

SR08570005-15 Filler 1 .063 x 2.00 x 5.00 Inches (a)

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BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT
SERVICE REWORK DRAWING SR08570005, STATION Xrs=251.00, RIGHT WING

Part Number/Speci- Name QTY Material Size Notes

fication

5/16 x 2.00 x 5.00 Inches, Grain (b)

lengthwise

SR08570005-18 Filler 1

SR08570005-19 Strap 1 .063 x 1.00 x 30.00 Inches (a)

SR08570005-21 Splice 2 .063 x 6.00 x 7.00 Inches (a)

HL328-8 Pin 27 - (e) (h)

MS21042L4 Nut 18 -

3D0006-3 Nut 33 - (f)

3D0006-4 Nut 9 - (f)

HLT428-6 Pin 335 - (e) (h)

HLT425-6 Pin 112 - (e) (h)

HL328-6 Pin 83 - (e) (h)

HL329-6 Pin 14 - (e) (h)

NAS1252-10L Washer 515 -

NAS1252-416L Washer 18 -

MS21042L3 Nut 515 -

ALUMINIUM CLAD SHEET, 7075-T6, MATERIAL PER QQ-A-250/13 TEMPER

T-6

(a)

ALUMINIUM PLATE 7075-T651, MATERIAL PER QQ-A-250/12 TEMPER T651(b)

ALUMINIUM BAR, 7075-T7351, MATERIAL PER QQ-A-229/9 TEMPER

T7351

(c)

(d) Part Number 60-3362 Angle, Aluminium Alloy, 7075-T76511

(e) Can be purchased from: Hi-Shear Corporation CAGE

2600 Skypark Drive 73197

Torrance California 90505

(f) Can be purchased from: The Boeing Company 81205

7755 East Marginal Way South

Seattle, Washington 98108-4002

(g) Can be purchased from: Transtar Metals Corporation 3YWN1

DBA Castle Metals Aerospace

970 West 190th Street Suite 700

Torrance, California 90502

(h) Grip length to be determined on installation.

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ALERT ALERT
SERVICE REWORK DRAWING SR08570015, STATION XRS=358.00, LEFT WING

Part Number/Speci- Name QTY Material Size Notes

fication

SR08570015-3 Strap 1 .100 x 1.45 x 35.00 Inches (a)

3.00 x 7.00 x 30.00 Inches, Grain (b)

lengthwise

SR08570015-5 Angle 1

SR08570015-7 Spacer 1 .08 x 1.00 x 30.00 Inches (b)

SR08570015-9 Fitting 1 6.00 Inches (c) (g)

SR08570015-11 Aft Tee 1 24.00 Inches (d) (g)

SR08570015-13 Strap 1 .150 x 5.00 x 36.00 Inches (a)

SR08570015-15 Fwd Tee 1 24.00 Inches (d) (g)

SR08570015-17 Shim 2 .187 x 2.00 x 19.00 Inches (a)

SR08570015-19 Shim 1 .063 x 2.00 x 19.00 Inches (a)

SR08570015-21 Stiffener 1 1.75 x 2.00 x 34.00 Inches (e)

SR08570015-23 Splice 1 .150 x 8.00 x 10.00 Inches (a)

SR08570015-25 Splice 1 .150 x 8.00 x 10.00 Inches (a)

SR08570015-27 Shim 1 .150 x 2.00 x 5.00 Inches (a)

SR08570015-29 Angle 1 13.00 Inches (f) (g)

HLT425-6-10 Pin 12 - (h)

HLT425-6-11 Pin 14 - (h)

HLT425-6-12 Pin 48 - (h)

HLT425-6-13 Pin 23 - (h)

HLT425-6-4 Pin 1 - (h)

HLT425-6-8 Pin 1 - (h)

HLT425-6-9 Pin 8 - (h)

HLT425-8-12 Pin 1 - (h)

HLT425-8-8 Pin 1 - (h)

HLT428-6-10 Pin 15 - (h)

HLT428-6-11 Pin 10 - (h)

HLT428-6-13 Pin 18 - (h)

HLT428-6-4 Pin 2 - (h)

HLT428-6-5 Pin 42 - (h)

HLT428-6-6 Pin 37 - (h)

HLT428-6-7 Pin 36 - (h)

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ALERT ALERT
SERVICE REWORK DRAWING SR08570015, STATION XRS=358.00, LEFT WING

Part Number/Speci- Name QTY Material Size Notes

fication

HLT428-6-8 Pin 12 - (h)

HLT428-6-9 Pin 36 - (h)

HLT428-6-10 Pin 4 - (h)

HLT428-6-11 Pin 10 - (h)

HLT428-6-13 Pin 2 - (h)

HLT428-8-3 Pin 16 - (h)

HLT428-8-4 Pin 4 - (h)

HLT428-8-7 Pin 4 - (h)

HL328-6-3 Pin 13 - (h)

HL328-6-4 Pin 45 - (h)

HL328-6-5 Pin 12 - (h)

HL328-6-6 Pin 18 (h)

HL328-6-7 Pin 36 (h)

HL328-6-8 Pin 5 (h)

HL328-6-9 Pin 1 (h)

MS20470AD8-9 Rivet 14

MS21042-L3 Nut 372

MS21042-L4 Nut 42

NAS1252-10L Washer 372

NAS1252-416L Washer 42

3D0006-3 Nut Assy 73 (g)

ALUMINIUM CLAD SHEET, 7075-T6, MATERIAL PER QQ-A-250/13 TEMPER

T-6

(a)

ALUMINIUM PLATE 7075-T651, MATERIAL PER QQ-A-250/12 TEMPER T651(b)

(c) Make from S1285512- extrusion

(d) Make from S2640548- extrusion

ALUMINIUM BAR, 7075-T7351, MATERIAL PER QQ-A-229/9 TEMPER

T7351

(e)

(f) Make from S2931482- extrusion

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ALERT ALERT
(g) Can be purchased from: The Boeing Company 81205

7755 East Marginal Way South

Seattle, Washington 98108-4002

(h) Can be purchased from: Hi-Shear Corporation CAGE

2600 Skypark Drive 73197

Torrance California 90505

SERVICE REWORK DRAWING SR08570015, STATION XRS=358.00, RIGHT WING

Part Number/Speci- Name QTY Material Size Notes

fication

SR08570015-3 Strap 1 .100 x 1.45 x 35.00 Inches (a)

3.00 x .70 x 30.00 Inches, Grain (b)

lengthwise

SR08570015-6 Angle 1

SR08570015-7 Spacer 1 .080 x 1.00 x 30.00 Inches (b)

SR08570015-10 Fitting 1 6.00 Inches (c) (g)

SR08570015-12 Aft Tee 1 24.00 Inches (d) (g)

SR08570015-13 Strap 1 .150 x 5.00 x 36.00 Inches (a)

SR08570015-16 Fwd Tee 1 24.00 Inches (d) (g)

SR08570015-17 Shim 2 .187 x 2.00 x 19.00 Inches (a)

SR08570015-19 Shim 1 .063 x 2.00 x 19.00 Inches (a)

SR08570015-22 Stiffener 1 1.75 x 2.00 x 34.00 Inches (e)

SR08570015-23 Splice 1 .150 x 8.00 x 10.00 Inches (a)

SR08570015-25 Splice 1 .150 x 8.00 x 10.00 Inches (a)

SR08570015-27 Shim 1 .150 x 2.00 x 5.00 Inches (a)

SR08570015-29 Angle 1 13.00 Inches (f) (g)

HLT425-6-10 Pin 12 - (h)

HLT425-6-11 Pin 14 - (h)

HLT425-6-12 Pin 48 - (h)

HLT425-6-13 Pin 23 - (h)

HLT425-6-4 Pin 1 - (h)

HLT425-6-8 Pin 1 - (h)

HLT425-6-9 Pin 8 - (h)

HLT425-8-12 Pin 1 - (h)

HLT425-8-8 Pin 1 - (h)

HLT428-6-10 Pin 15 - (h)

HLT428-6-11 Pin 10 - (h)

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BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT
SERVICE REWORK DRAWING SR08570015, STATION XRS=358.00, RIGHT WING

Part Number/Speci- Name QTY Material Size Notes

fication

HLT428-6-13 Pin 18 - (h)

HLT428-6-4 Pin 2 - (h)

HLT428-6-5 Pin 42 - (h)

HLT428-6-6 Pin 37 - (h)

HLT428-6-7 Pin 36 - (h)

HLT428-6-8 Pin 12 - (h)

HLT428-6-9 Pin 36 - (h)

HLT428-6-10 Pin 4 - (h)

HLT428-6-11 Pin 10 - (h)

HLT428-6-13 Pin 2 - (h)

HLT428-8-3 Pin 16 - (h)

HLT428-8-4 Pin 4 - (h)

HLT428-8-7 Pin 4 - (h)

HL328-6-3 Pin 13 - (h)

HL328-6-4 Pin 45 - (h)

HL328-6-5 Pin 12 - (h)

HL328-6-6 Pin 18 (h)

HL328-6-7 Pin 36 (h)

HL328-6-8 Pin 5 (h)

HL328-6-9 Pin 1 (h)

MS20470AD8-9 Rivet 14

MS21042-L3 Nut 372

MS21042-L4 Nut 42

NAS1252-10L Washer 372

NAS1252-416L Washer 42

3D0006-3 Nut Assy 73 (g)

ALUMINIUM CLAD SHEET, 7075-T6, MATERIAL PER QQ-A-250/13 TEMPER

T-6

(a)

ALUMINIUM PLATE 7075-T651, MATERIAL PER QQ-A-250/12 TEMPER T651(b)

(c) Make from S1285512- extrusion

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ALERT ALERT
(d) Make from S2640548- extrusion

ALUMINIUM BAR, 7075-T7351, MATERIAL PER QQ-A-229/9 TEMPER

T7351

(e)

(f) Make from S2931482- extrusion

(g) Can be purchased from: The Boeing Company CAGE

7755 East Marginal Way South 81205

Seattle, Washington 98108-4002

(h) Can be purchased from: Hi-Shear Corporation 73197

2600 Skypark Drive

Torrance California 90505

SERVICE REWORK DRAWING SR08570022, STATION 168.00, LEFT WING

Part Number/Speci- Name QTY Material Size Notes

fication

SR08570022-3 Strap 1 .100 x 2.00 x 8.00 (a)

3.00 x 7.00 x 31.00 Inches, Grain (b)

lengthwise

SR08570022-5 Angle 1

.080 x 1.00 x 11.00 Inches, Grain (b)

lengthwise

SR08570022-7 Strap 1

SR08570022-9 Corner Seal 1 1.75 x 2.00 x 6.00 Inches (c)

SR08570022-11 Aft Tee 1 34.00 Inches (d) (f)

SR08570022-13 Doubler 1 .160 x 6.00 x 36.00 Inches (a)

SR08570022-15 Fwd Tee 1 34.00 Inches (d) (f)

SR08570022-17 Shim 2 .190 x 2.00 x 28.00 Inches (a)

SR08570022-19 Shim 1 .063 x 2.00 x 28.00 Inches (a)

SR08570022-21 Angle 1 1.00 x 2.00 x 5.00 Inches (b)

SR08570022-23 Splice 1 .160 x 7.00 x 8.00 Inches (a)

SR08570022-25 Splice 1 .160 x 6.00 x 7.00 Inches (a)

SR08570022-27 Strap 1 .100 x 2.00 x 20.00 Inches (a)

SR08570022-29 Angle 1 13.00 Inches (e) (f)

SR08570022-31 Filler 1 .190 x 4.00 x 4.00 Inches (a)

SR08570022-33 Filler 1 .125 x 1.00 x 5.00 Inches (a)

SR08570022-35 Strap 1 .080 x 1.00 x 19.00 Inches (a)

HLT425-6-10 Pin 8 (g)

HLT425-6-11 Pin 16 (g)

HLT425-6-12 Pin 16 (g)

HLT425-6-13 Pin 43 (g)

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BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT
SERVICE REWORK DRAWING SR08570022, STATION 168.00, LEFT WING

Part Number/Speci- Name QTY Material Size Notes

fication

HLT425-6-14 Pin 20 (g)

HLT425-6-5 Pin 1 (g)

HLT425-6-9 Pin 2 (g)

HLT425-8-13 Pin 1 (g)

HLT425-8-9 Pin 2 (g)

HLT428-6-10 Pin 8 (g)

HLT428-6-11 Pin 4 (g)

HLT428-6-13 Pin 20 (g)

HLT428-6-4 Pin 2 (g)

HLT428-6-5 Pin 33 (g)

HLT428-6-6 Pin 112 (g)

HLT428-6-7 Pin 22 (g)

HLT428-6-8 Pin 17 (g)

HLT428-6-9 Pin 44 (g)

HLT428-8-10 Pin 4 (g)

HLT428-8-11 Pin 9 (g)

HLT428-8-13 Pin 1 (g)

HLT428-8-4 Pin 3 (g)

HLT428-8-5 Pin 2 (g)

HLT428-8-6 Pin 5 (g)

HLT428-8-7 Pin 16 (g)

HL328-6-3 Pin 59 (g)

HL328-6-4 Pin 45 (g)

HL328-6-5 Pin 22 (g)

HL328-6-6 Pin 19 (g)

HL328-6-7 Pin 41 (g)

HL328-6-8 Pin 16 (g)

HL328-6-9 Pin 3 (g)

MS20470AD8-9D Rivet 58

MS21042-L3 Nut 503

MS21042-L4 Nut 43

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BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT
SERVICE REWORK DRAWING SR08570022, STATION 168.00, LEFT WING

Part Number/Speci- Name QTY Material Size Notes

fication

NAS1252-10L Washer 503

NAS1252-416L Washer 43

3D0006-3 Nut Assy 72 (f)

ALUMINIUM CLAD SHEET, 7075-T6, MATERIAL PER QQ-A-250/13 TEMPER

T-6

(a)

ALUMINIUM PLATE 7075-T651, MATERIAL PER QQ-A-250/12 TEMPER T651(b)

(c) ALUMINIUM BAR, 7075-T6, MATERIAL PER QQ-A-225/9 TEMPER T6

(d) Make from S1641827 extrusion

(e) Make from S2931482T extrusion

(f) Can be purchased from: The Boeing Company CAGE

7755 East Marginal Way South 81205

Seattle, Washington 98108-4002

(g) Can be purchased from: Hi-Shear Corporation 73197

2600 Skypark Drive

Torrance California 90505

SERVICE REWORK DRAWING SR08570022, STATION 168.00, RIGHT WING

Part Number/Speci- Name QTY Material Size Notes

fication

SR08570022-3 Strap 1 .100 x 2.00 x 8.00 (a)

3.00 x 7.00 x 31.00 Inches, Grain (b)

lengthwise

SR08570022-6 Angle 1

.080 x 1.00 x 11.00 Inches, Grain (b)

lengthwise

SR08570022-7 Strap 1

SR08570022-10 Corner Seal 1 1.75 x 2.00 x 6.00 Inches (c)

SR08570022-12 Aft Tee 1 34.00 Inches (d) (f)

SR08570022-13 Doubler 1 .160 x 6.00 x 36.00 Inches (a)

SR08570022-16 Fwd Tee 1 34.00 Inches (d) (f)

SR08570022-17 Shim 2 .190 x 2.00 x 28.00 Inches (a)

SR08570022-19 Shim 1 .063 x 2.00 x 28.00 Inches (a)

SR08570022-21 Angle 1 1.00 x 2.00 x 5.00 Inches (b)

SR08570022-23 Splice 1 .160 x 7.00 x 8.00 Inches (a)

SR08570022-25 Splice 1 .160 x 6.00 x 7.00 Inches (a)

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BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT
SERVICE REWORK DRAWING SR08570022, STATION 168.00, RIGHT WING

Part Number/Speci- Name QTY Material Size Notes

fication

SR08570022-27 Strap 1 .100 x 2.00 x 20.00 Inches (a)

SR08570022-29 Angle 1 13.00 Inches (e) (f)

SR08570022-31 Filler 1 .190 x 4.00 x 4.00 Inches (a)

SR08570022-33 Filler 1 .125 x 1.00 x 5.00 Inches (a)

SR08570022-35 Strap 1 .080 x 1.00 x 19.00 Inches (a)

HLT425-6-10 Pin 8 (g)

HLT425-6-11 Pin 16 (g)

HLT425-6-12 Pin 16 (g)

HLT425-6-13 Pin 43 (g)

HLT425-6-14 Pin 20 (g)

HLT425-6-5 Pin 1 (g)

HLT425-6-9 Pin 2 (g)

HLT425-8-13 Pin 1 (g)

HLT425-8-9 Pin 2 (g)

HLT428-6-10 Pin 8 (g)

HLT428-6-11 Pin 4 (g)

HLT428-6-13 Pin 20 (g)

HLT428-6-4 Pin 2 (g)

HLT428-6-5 Pin 33 (g)

HLT428-6-6 Pin 112 (g)

HLT428-6-7 Pin 22 (g)

HLT428-6-8 Pin 17 (g)

HLT428-6-9 Pin 44 (g)

HLT428-8-10 Pin 4 (g)

HLT428-8-11 Pin 9 (g)

HLT428-8-13 Pin 1 (g)

HLT428-8-4 Pin 3 (g)

HLT428-8-5 Pin 2 (g)

HLT428-8-6 Pin 5 (g)

HLT428-8-7 Pin 16 (g)

HL328-6-3 Pin 59 (g)

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BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT
SERVICE REWORK DRAWING SR08570022, STATION 168.00, RIGHT WING

Part Number/Speci- Name QTY Material Size Notes

fication

HL328-6-4 Pin 45 (g)

HL328-6-5 Pin 22 (g)

HL328-6-6 Pin 19 (g)

HL328-6-7 Pin 41 (g)

HL328-6-8 Pin 16 (g)

HL328-6-9 Pin 3 (g)

MS20470AD8-9D Rivet 58

MS21042-L3 Nut 503

MS21042-L4 Nut 43

NAS1252-10L Washer 503

NAS1252-416L Washer 43

3D0006-3 Nut Assy 72 (f)

ALUMINIUM CLAD SHEET, 7075-T6, MATERIAL PER QQ-A-250/13 TEMPER

T-6

(a)

ALUMINIUM PLATE 7075-T651, MATERIAL PER QQ-A-250/12 TEMPER T651(b)

(c) ALUMINIUM BAR, 7075-T6, MATERIAL PER QQ-A-225/9 TEMPER T6

(d) Make from S1641827 extrusion

(e) Make from S2931482T extrusion

(f) Can be purchased from: The Boeing Company CAGE

7755 East Marginal Way South 81205

Seattle, Washington 98108-4002

(g) Can be purchased from: Hi-Shear Corporation 73197

2600 Skypark Drive

Torrance California 90505

3. Parts Modified and Reidentified

The parts shown below are changed as shown in this service bulletin. The quantity (QTY) is the

number of parts changed on each airplane.

Existing Part QTY Name New Part Number Notes

Number

3616951-1 1 Tee SR08570005-13 (a)

3616951-2 1 Tee SR08570005-14 (a)

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BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT
Existing Part QTY Name New Part Number Notes

Number

(a) Make the change in accordance with Service Rework Drawing SR08570005.

4. Parts Removed and Not Replaced

None.

D. Parts Necessary to Change Spares

None

E. Special Tooling - Price and Availability

None.

F. Special Tooling Necessary to do this Service Bulletin

No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance

and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine

operator tool supply to make sure all necessary tools are available.

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BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT

BLANK PAGE
3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

WARNING: IF ELECTRICAL POWER IS APPLIED TO THE AIRPLANE, MAKE SURE YOU OBEY

ALL PRECAUTIONS WHILE YOU DO WORK. IF YOU DO NOT OBEY THE

PRECAUTIONS, DEATH OR INJURY TO PERSONS, AND DAMAGE TO THE AIRPLANE

CAN OCCUR.

CAUTION: ELECTRICALLY GROUND THE AIRPLANE. THIS WILL HELP TO PREVENT DAMAGE

TO THE AIRPLANE OR EQUIPMENT.

CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,

METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE

DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR

OTHER ELECTRICAL DAMAGE.

NOTE: 1. The instructions identified in Paragraph 3.B., Work Instructions, and the Figure(s)

give the recommended sequence of steps. The sequence of steps to do this service

bulletin can be changed.

2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for

definition of the acronyms.

3. Equivalent parts are listed in the AEPL, Drawing 7595071.

4. Use the approved fastener and process material substitutions, in accordance with

DC-8 SRM Chapter 51.

5. If the length of any fastener specified in this service bulletin does not meet the

installation standards in DC-8 SRM Chapter 51, then a fastener of the same

specification, or an approved substitute, with a length which meets the installation

standards in DC-8 SRM Chapter 51 may be used.

6. A 1/8-inch thick stack of the same type washers called for in this service bulletin is

the maximum thickness which may be used under fastener head or nut to counteract

accumulation of tolerances.

EXCEPTION: When the available fastener length increments are greater than

1/16-inch, a 3/16-inch thick stack of the same type washers may be used.

7. Unless shown differently, these dimensions and tolerances are used:

– Linear dimensions are in inches

– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus

or minus 0.03 inch.

– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch

– Angular tolerance is plus or minus 2 degrees

– Hole dimensions for standard solid rivets are in DC-8 SRM Chapter 51.

– Torque limits to tighten nuts and bolts are in DC-8 SRM Chapter 51.

8. Obey all of the warnings and cautions given in the specified manual sections.

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BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT
9. A Detailed Inspection is defined as: An intensive examination of a specific item,

installation, or assembly to detect damage, failure, or irregularity. Available lighting

is normally supplemented with a direct source of good lighting at an intensity deemed

appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be

necessary. Surface cleaning and elaborate procedures may be required.

10. A General Visual Inspection is defined as: A visual examination of an interior or

exterior area, installation or assembly to detect obvious damage, failure or irregularity.

This level of inspection is made from within touching distance unless otherwise

specified. A mirror may be necessary to enhance visual access to all exposed surfaces

in the inspection area. This level of inspection is made under normally available

lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may

require removal or opening of access panels or doors. Stands, ladders or platforms

may be required to gain proximity to the area being checked.

11. These work instructions refer to procedures included in other Boeing documents.

When the words "refer to" are used and the operator has an accepted alternative

procedure, the accepted alternative procedure can be used. When the words "in

accordance with" are included in the instruction, the procedure in the Boeing document

must be used.

B. WORK INSTRUCTIONS

Option 1 (Eddy Current, High Frequency)

1. Make the left and right wing fuel tanks safe for entry. Refer to DC-8 AMM 28-00-0 as an accepted

procedure.

2. Gain access to the areas to be inspected by opening the access panels as follows:

Access Panel Location

505B Left/Right Wing, Upper Surface

505C Left/Right Wing, Upper Surface

506B Left/Right Wing, Upper Surface

580D Internal Access Door

560D Internal Access Door

3. Do an Eddy Current, High Frequency Inspection in the area around the indicated fasteners of the

access opening doubler on the left and right wing center spar lower cap in accordance with the

instructions in Figure 1 and establish the following condition(s).

NOTE: It is possible to have more than one condition on an individual airplane.

CONDITION 1 (No Crack(s) Found)

a. Go to work step 4

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BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT
CONDITION 2 (Crack Found at Station Xrs=168.00, Left and/or Right Wing)

a. Repair crack in accordance with Service Rework Drawing SR08570022.

b. Go to work step 4.

CONDITION 3 (Crack found at station Xrs=251.00, Left and/or Right Wing)

a. Repair crack in accordance with Service Rework Drawing SR08570005.

b. Go to work step 4.

CONDITION 4 (Crack Found at Station Xrs=358.00, Left and/or Right Wing)

a. Repair crack in accordance with Service Rework Drawing SR08570015.

b. Go to work step 4.

4. Install removed access panels.

5. Put the airplane back in serviceable condition.

6. Do repetitive inspections of the non-repaired center spar lower cap of the left and right wing center

spar, and any repairs if installed, at intervals defined in Paragraph 1.E., Compliance.

Option 2 (Eddy Current, Low Frequency)

1. Do an Eddy Current, Low Frequency Inspection of the center spar lower cap of the left and right

wing center spar at the locations shown in Figure 2 to establish the following condition(s):

NOTE: It is possible to have more than one condition on an individual airplane.

CONDITION 1 (No Crack(s) Found)

a. Go to work step 2.

CONDITION 2 (Crack Found at Station Xrs=168.00, Left and/or Right Wing)

a. Make the left and/or right wing fuel tanks safe for entry. Refer to DC-8 AMM 28-00-0 as an

accepted procedure.

b. Gain access to the area(s) to be repaired by opening the applicable access panels as follows:

Access Panel Location

505B Left/Right Wing, Upper Surface

505C Left/Right Wing, Upper Surface

506B Left/Right Wing, Upper Surface

580D Internal Access Door

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BOEING SERVICE BULLETIN DC8-57A103

ALERT ALERT
Access Panel Location

560D Internal Access Door

c. Repair crack in accordance with Service Rework Drawing SR08570022.

d. Install removed access panels.

e. Put the airplane back in serviceable condition.

f. Go to work step 2.

CONDITION 3 (Crack Found at Station Xrs=251.00, Left and/or Right Wing)

a. Make the left and/or right wing fuel tanks safe for entry. Refer to DC-8 AMM 28-00-0 as an

accepted procedure.

b. Gain access to the area(s) to be repaired by opening the applicable access panels as follows:

Access Panel Location

505B Left/Right Wing, Upper Surface

505C Left/Right Wing, Upper Surface

506B Left/Right Wing, Upper Surface

580D Internal Access Door

560D Internal Access Door

c. Repair crack in accordance with Service Rework Drawing SR08570005.

d. Install removed access panels.

e. Put the airplane back in serviceable condition.

f. Go to work step 2.

CONDITION 4 (Crack Found at Station Xrs=358.00, Left and/or Right Wing)

a. Make the left and/or right wing fuel tanks safe for entry. Refer to DC-8 AMM 28-00-0 as an

accepted procedure.

b. Gain access to the area(s) to be repaired by opening the applicable access panels as follows:

Access Panel Location

505B Left/Right Wing, Upper Surface

505C Left/Right Wing, Upper Surface

506B Left/Right Wing, Upper Surface

580D Internal Access Door

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Access Panel Location

560D Internal Access Door

c. Repair crack in accordance with Service Rework Drawing SR08570015.

d. Install removed access panels.

e. Put the airplane back in serviceable condition.

f. Go to work step 2.

2. Do repetitive Eddy Current, Low Frequency Inspections of the non-repaired center spar lower cap

of the left and right wing at the locations shown in Figure 2, and any repairs if installed, at intervals

defined in Paragraph 1.E., Compliance.

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FIGURE 1: INSPECT THE LEFT AND RIGHT WING CENTER SPAR - EDDY CURRENT, HIGH FREQUENCY

INSPECTION METHOD

(SHEET 1 OF 4)

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FIGURE 1: INSPECT THE LEFT AND RIGHT WING CENTER SPAR - EDDY CURRENT, HIGH FREQUENCY

INSPECTION METHOD

(SHEET 2 OF 4)

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FIGURE 1: INSPECT THE LEFT AND RIGHT WING CENTER SPAR - EDDY CURRENT, HIGH FREQUENCY

INSPECTION METHOD

(SHEET 3 OF 4)

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The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

Step Action Station Notes

Perform a High Frequency Eddy Current surface inspection of the spar cap

adjacent to the indicated fastener in the left and right wings. Scan around

the fastener looking for cracks originating at fastener hole and propagating

radially from the fastener hole. Scan using the instructions found in the

Nondestructive Testing Standard Practice Manual (NDTSPM) 06-10-01.001

(HFET - Procedure 1). Use Calibration Method "K" and Scan Method "44."

1 Inspect Xrs = 168.00

Perform a High Frequency Eddy Current surface inspection of the spar cap

adjacent to the indicated fastener in the left and right wings. Scan around

the fastener looking for cracks originating at fastener hole and propagating

radially from the fastener hole. Scan using the instructions found in the

Nondestructive Testing Standard Practice Manual (NDTSPM) 06-10-01.001

(HFET - Procedure 1). Use Calibration Method "K" and Scan Method "44."

2 Inspect Xrs = 251.00

Perform a High Frequency Eddy Current surface inspection of the spar cap

adjacent to the indicated fastener in the left and right wings. Scan around

the fastener looking for cracks originating at fastener hole and propagating

radially from the fastener hole. Scan using the instructions found in the

Nondestructive Testing Standard Practice Manual (NDTSPM) 06-10-01.001

(HFET - Procedure 1). Use Calibration Method "K" and Scan Method "44."

3 Inspect Xrs = 358.00

FIGURE 1: INSPECT THE LEFT AND RIGHT WING CENTER SPAR - EDDY CURRENT, HIGH FREQUENCY

INSPECTION METHOD

(SHEET 4 OF 4)

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FIGURE 2: INSPECT THE LEFT AND RIGHT WING CENTER SPAR -EDDY CURRENT, LOW FREQUENCY

INSPECTION METHOD

(SHEET 1 OF 3)

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FIGURE 2: INSPECT THE LEFT AND RIGHT WING CENTER SPAR -EDDY CURRENT, LOW FREQUENCY

INSPECTION METHOD

(SHEET 2 OF 3)

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The step numbers shown below agree with the numbers shown in the circle symbols in the figure. Do an Eddy

Current, Low Frequency Inspection of the left and right wings through the skin into the spar cap to confirm intact

center spar lower cap. Inspections should start at the bulkhead stations and continue to wing stations as follows:

Step Action Station Notes

Do an Eddy Current, Low Frequency Inspection of the left and right wings

through the skin into the spar cap to confirm intact center spar lower cap.

Inspect a minimum of 7 inches inboard from noted bulkhead station. Inspect

per Supplemental Inspection Document (SID) Volume II, PSE 57.08.013/014

using chapter 57-10-06 Sequence 1, Method 1.

1 Inspect Xrs = 168.00

Do an Eddy Current, Low Frequency Inspection of the left and right wings

through the skin into the spar cap to confirm intact center spar lower cap.

Inspect a minimum of 7 inches inboard from noted bulkhead station. Inspect

per Supplemental Inspection Document (SID) Volume II, PSE 57.08.013/014

using chapter 57-10-06 Sequence 1, Method 1.

2 Inspect Xrs = 251.00

Do an Eddy Current, Low Frequency Inspection of the left and right wings

through the skin into the spar cap to confirm intact center spar lower cap.

Inspect a minimum of 7 inches inboard from noted bulkhead station. Inspect

per Supplemental Inspection Document (SID) Volume II, PSE 57.08.35/036

using chapter 57-10-16 Sequence 1, Method 1.

3 Inspect Xrs = 358.00

FIGURE 2: INSPECT THE LEFT AND RIGHT WING CENTER SPAR -EDDY CURRENT, LOW FREQUENCY

INSPECTION METHOD

(SHEET 3 OF 3)

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ALERT ALERT