service bulletin no. 93 - vulcan air · service bulletin no. 93 original issue: nov. 24, 1995 only...

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SERVICE BULLETIN

No. 93

ORIGINAL ISSUE: Nov. 24, 1995

Only engineering aspects are R.A.I. approved. If inspection, modifications or technical

prescriptions and their relative times of compliance are compulsory for the R.A.I., the sanction

is in the relevant airworthiness directives.

Subject: Inspection of the internal area of the wing box between ribs n° 6 and 8 (engine

nacelle area).

MANDATORY ACTION

1. PLANNING INFORMATION

1.1 MODEL AFFECTED & S/N

All P68 series aircraft up to S/N 400 inclusive.

1.2 REASON

To make suitable inspection holes in the wing underside in proximity of

engine nacelles to allow inspection of the internal area of the wing box

between ribs n° 6 and n° 8 with special attention to the 4 top panel

stringers.

1.3 DESCRIPTION

Some cases of wing top panel stringers crack in the engine nacelle area

have been reported.

PARTENAVIA S.p.A. Service Bulletin N 93 Original Issue: Nov. 24, 1995

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1. PLANNING INFORMATION (Cont.)

1.3 DESCRIPTION (Cont.)

For the above, it is prescribed:

1. To make inspection holes on wing underside in proximity of engine

nacelles within the time of compliance indicated at step a) of para.

1.5 and in accordance with the instructions of para. 2.1.

2. On the internal area of the wing box between ribs n. 6 and n. 8, to

conduct a first inspection according to the time of compliance

indicated at step a) of para. 1.5 and subsequently periodical

inspections according to the times of compliance indicated at step b)

of para. 1.5, in accordance with the instructions of para. 2.2, paying

special attention to the condition of the 4 top panel stringers for

aircraft with modification of step 3. of this paragraph not yet applied

(stringer replacement) and to the condition of the top panel for

aircraft with said modification already applied.

3. If top panel stringers result cracked, to replace them with new “V”

stringers and to check the wing top panel for cracks according to the

instructions of para. 2.3, with special attention to the area in

proximity of dimpled holes used for removed stringer installation.

4. To notify Partenavia, according to step 6. Of para. 2.2, of further

wing structure damages, if any, to agree on actions to be taken for

proper repair.

5. To inspect, according to the times of compliance indicated at step c)

of para. 1,5 and the instructions of para. 2.4, the wing top panel for

cracks, with special attention to the areas in proximity of pre-

modification dimpled holes (see step 3 of this paragraph).

6. To notify Partenavia, according to step 3. Of para. 2.4 of top panel

stringer damages, if any, found after the inspection of step 5 of this

paragraph, to agree on the actions to be taken for proper repair.

1.4 APPROVAL

Letter n. 95-6025/TNA dated 27.11.95 issued by R.A.I.


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1.5 TIME OF COMPLIANCE

a) Hole opening and first inspection referenced in para. 2.1 and 2.2:

- For aircraft with more than 500 flight hours: at the next 100 h

inspection.

- For aircraft with less than 500 flight hours: at 500 h.

b) Subsequent inspections referenced in para. 2.2:

- For aircraft with modification of step 3. Of para. 1.3 not yet

applied: carry out repeating inspections every 300 flight

hours

- For aircraft with modification of step 3. Para. 1.3 already

applied: carry out repeating inspection every 500 flight hours.

c) Inspection referenced in para. 2.4:

- Carry out the inspection at the next 2000 flight hours from the

application of the modification of step 3. Of para. 1.3.

1.6 MANPOWER

For the application of this Service Bulletin the following manhours are

estimated, including the time to access the parts and to restore the aircraft

to its airworthy condition:

a) For hole opening and first inspection referenced in para. 2.1 and

2.2: 12 hours.

b) For each subsequent inspection referenced in para. 2.2: 1 hour.

c) For stringer replacement referenced in para. 2.3: 40 hours.

d) For inspection referenced in para. 2.4: 8 hours.

1.7 TOOLING

No special tools are required

1.8 WEIGHT AND BALANCE

Negligible

1.9 ELECTRICAL LOAD DATA

Not Applicable


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1.10 REFERENCES

a) For inspection hole execution:

- Modification scheme R.0298 for P68, P68B, P68C, P68R,

P68 OBS and P68 OBS2 aircraft.

- Modification scheme R.0299 for P68C-TC and P68 OBS-TC

aircraft.

b) For stringer replacement:

- Modification scheme R.0303.

1.11 PUBLICATIONS AFFECTED

Maintenance Manual and Parts Catalog

1.12 UNSAFE CONDITIONS

Non application of this Service Bulletin does not allow to locate damages

of the type described in para. 1.3, which can compromise structural

resistance to acting loads because of an altered panel stability.

1.13 MODIFICATION TO BE CARRIED OUT BY

Partenavia manufacturing plant or maintenance company certified and

qualified for the required operation level.

2. ACCOMPLISHMENT INSTRUCTIONS

2.1 MODIFICATION/FIRST INSPECTION (Ref. Step 1 and 2 of para 1.3)

At the time of compliance of step a) of para. 1.5 carry out the following on

both half-wings:

For P68, P68B, P68C, P68R, P68 OBS and P68 OBS2 aircraft:

Make inspection holes according to the attached modification scheme

R.0298, using the following kits:

- Kit n° 68-073/1 for aircraft up to S/N 87 inclusive,

- Kit n° 68-073/2 for aircraft from S/N 88 to 400 inclusive.

For P68C-TC and P68 OBS-TC aircraft:

a) Record the occurred application of this bulletin with reference to

step 1. Of para. 1.3 on the aircraft log book.


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2. ACCOMPLISHMENT INSTRUCTIONS (Cont.)

2.1 MODIFICATION/FIRST INSPECTION (Cont.)

b) Carry out the first inspection of the internal area of the wing box

between ribs n. 6 and 8 according to the instructions of para. 2.2.

NOTES

1. The execution of inspection holes does not require removal of any

elements affected by the modification.

2. All surfaces exposed during the job must be treated with Alodine

1200 (spec. MIL-C-5541) by brush application and then, within 48

hours, with epoxy finish paint (spec. MIL-P-23377).

2.2 FIRST INSPECTION and REPEATING INSPECTION (Ref. Step 2. of

para. 1.3)

According to the time of compliance of step a) and b) of para. 1.5 inspect

the internal area of both half-wing boxes between ribs. N. 6 and 8, as per

the following instructions:

Instructions:

1. Remove the inspection cover located on the underside cowling of

the engine nacelle.

2. Through the opening of step 1, remove the inspection cover

located on the wing underside panel between ribs n. 6 and n. 7.

3. Through the double hole of steps 1 and 2, inspect the wing box

internal area between ribs n. 6 and n. 8 for cracks/breaks,

deformations or evidence of damages, with special attention to the

4 top panel stringers for aircraft with modification of step 3. Of para.

1.3 (stringer replacement) not yet applied and to the top panel for

aircraft with said modification already applied. The use of a

swinging mirror and a lamp shall ease the inspection operation in

the box areas more distant from the access hole.

4. If no damages are found, reinstall the inspection covers previously

removed and record the occurred application of this bulletin with

reference to step 2 of para. 1.3 on the aircraft log book.


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2.2 FIRST INSPECTION and REPEATING INSPECTION (Cont.)

5. If cracks are found on wing top panel stringers on aircraft with

modification of step. 3. of para. 1.3 (stringer replacement) not yet

applied, proceed as follows: Notify the inspection result to

Partenavia and replace stringers as per modification scheme R.

0303, using kit 68-073/3 for P68, P68B, P68C, P68R, P68 OBS,

P68 OBS2 aircraft and kit 68-073/4 for P68C-TC and P68 OBS-TC

aircraft, according to the instructions of para. 2.3.

6. In case of further damages to wing structure (ribs, spars and skin

panels) in the area covered by this bulletin, ground the aircraft and

notify the inspection result to Partenavia, which shall supply the

necessary instructions for proper repair.

In said notification, report also:

• Aircraft type

• Aircraft S/N

• Aircraft total flight hours.

2.3 REPAIR/INSPECTION (Ref. Step 3. Of para. 1.3)

In case of cracks on wing top panel stringers (step 5 of para. 2.2), carry

out the following on both half-wings:

a) Replacement of wing top panel stringers with new “V” stringers, P/N

R.0303-2/12, as per modification scheme R.0303, using kit 68-

073/3 for P68, P68B, P68C, P68R, P68 OBS, P68 OBS2 aircraft

and kit 68-073/4 for P68C-TC and P68 OBS-TC aircraft.

b) Inspect the wing top panel in the area between ribs n. 6 and n. 8

for cracks, with special attention in proximity of dimpled holes used

for removed stringer installation.

Instructions:

1. Access the external surface of the wing top panel in the area

between ribs n. 6 and n. 8, carrying out the following (ref. dwg

R.0303):


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2.3 REPAIR/INSPECTION (Cont.)

For P68, P68B, P68C, P68R, P68 OBS, P68 OBS2 aircraft:

a) Remove top and side cowlings of the engine nacelle.

b) De-rivet and remove the top fairing of the engine nacelle.


a) Remove top cowlings of the engine nacelle.

b) De-rivet and remove the central panel P/N 1.2219-1, of the top

fairing of the engine nacelle.

2. Through the double hole on engine nacelle and wing underside of

step 1. and 2. of para. 2.2, and acting from the external side,

unrivet and remove the wing top panel stringers.

3. Using a 10x magnifying lens, check the wing top panel between

ribs n. 6 and n. 8 for cracks, with special attention to the areas in

proximity of dimpled holes left void after stringer removal of step 2.

4. In case of cracks on wing top panel, ground the aircraft and notify

the inspection result to Partenavia, which shall supply the


5. In case of no cracks on wing top panel, install new “V” stringers P/N

R.0303-2/12 on said panel as per modification scheme R.0303. For

proper drilling, use drilling jig P/N R.0303-14A included in the kit.

NOTES

1. For P68C-TC and P68 OBS-TC aircraft, before installing new

stringers, plug pre-modification dimpled holes, with 3.2 mm dia.

blind rivets as per modification scheme R.0303.

2. All Surfaces exposed during the job must be treated with Alodine

1200 (spec. MIL-C-5541) by brush application and subsequently,

within 48 hours, with finish epoxy paint (spec. MIL-P-23377).

6. Reinstall the top fairing of the necelle as before (ref. Modification

scheme R.0303).

7. Reinstall inspection covers and engine cowlings previously

removed.

8. Record the occurred application of this bulletin with reference to

step 3. of para. 1.3 on the aircraft log book.


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2.4 INSPECTION (Ref. Step 5. Of para. 1.3)

At times of compliance of step c) of para. 1.5, on both half-wings inspect

the wing top panel in the area between ribs n. 6 and n. 8 for cracks as per

the following instructions:

Instructions:

1. Access the external surface of the wing top panel in the area

between ribs n. 6 and n. 8, carrying out the following (ref. dwg

R.0303):

For P68, P68B, P68C, P68R, P68 OBS and P68 OBS2 aircraft:

a) Remove top and side cowlings of the engine nacelle.

b) De-rivet and remove the top fairing of the engine nacelle.


a) Remove the top cowlings of the engine nacelle.

b) De-rivet and remove the central panel P/N 1.2219-1 of the

top fairing of the engine nacelle.

2. Using a 10x magnifying lens, check the wing top panel between

ribs n. 6 and n. 8 for cracks, with special attention to the area in

proximity of dimpled holes used for removed stringer installation.

3. In case of cracks on wing top panel, ground the aircraft and notify

the inspection result to Partenavia, which shall supply the


In the notification, indicate also:

• Aircraft type

• Aircraft S/N

• Aircraft total flight hours

• Flight hours from the application of the modification of

step 3. of para. 1.3.

4. In case of no crack, reinstall the top fairing of the engine nacelle as

before (ref. modification scheme R.0303) and reinstall the engine

cowlings previously removed.

5. Record the occurred application of this bulletin with reference to

step 5. Of para. 1.3 on the aircraft log book.


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3. MATERIAL INFORMATION

3.1 REQUIRED MATERIAL

For the modification of para. 2.1 (inspection hole execution)

a) For aircraft up to S/N 87 inclusive:

KIT 68-073/1

ITEM P/N DESCRIPTION Q.TY

1 1.2141-1 FRAME ASSY 2

2 1.2141-3 INSPECTION COVER 2


4 1.2141-4 FRAME ASSY 2

5 AN 526-632-R7 SCREW 32

6 AVDEL 4807-0407 BLIND RIVET 40

7 NAS 1097AD3-4 RIVET 24

8 DWG R.0298 MODIFICATION SCHEME 1

b) For aircraft from S/N 88 up to S/N 400 inclusive:

KIT 68-073/2


1 1.2141-1 FRAME ASSY 2



4 1.2141-4 FRAME ASSY 2

5 AN 526-632-R7 SCREW 32

7 NAS 1097AD3-4 RIVET 64

8 (*) MODIFICATION SCHEME 1

(*) R.0298 applicable to P68B, P68C, P68R, P68 OBS and P68 OBS2 aircraft

R.0299 applicable to P68C-TC and P68 OBS-TC aircraft


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3. MATERIAL INFORMATION (Cont.)

3.1 REQUIRED MATERIAL (Cont.)

For the repair of para. 2.3 (stringer replacement)

a) For P68, P68B, P68C, P68R, P68 OBS, P68 OBS2 aircraft:

KIT 68-073/3


1 R.0303-2 LH Stringer 4

2 R.0303-12 RH Stringer 4

3 MS20470 AD3-4 Rivet 224

4 AVDEL 4801-0409 Blind Rivet 4


6 (*) Rivet 20

7 (**) Rivet 20

8 R.0303-14A Backdrill tools 1

9 DWG R.0303 Repair scheme 1

(*) MS20426AD3-5 for a/c up to S/N 87 inclusive (Fiberglass Fairing)

NAS1097AD3-3 for a/c from S/N 88 inclusive (Light Alloy Fairing)

(**) MS20426AD4-7 for a/c up to S/N 87 Inclusive (Fiberglass Fairing)

NAS1097AD4-5 for a/c from S/N 88 inclusive (Light Alloy Fairing)

b) For P68C-TC and P68 OBS-TC aircraft:

KIT 68-073/4


1 R.0303-2 LH Stringer 4

2 R.0303-12 RH Stringer 4

3 MS20470 AD3-4 Rivet 224


5 MS20470 AD4-5 Rivet 68

6 R.0303-14A Backdrill tools 1

7 DWG R.0303 Repair scheme 1

NOTE

When ordering the kit, advise aircraft type and S/N.

3.2 MATERIAL AVAILABILITY

The kit are available within 15 days of the order date.


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3. MATERIAL INFORMATION (Cont.)

3.3 MATERIAL COST

Kit 68-073/1: 175 USD

Kit 68-073/2: 175 USD

Kit 68-073/3: 175 USD

Kit 68-073/4: 125 USD

NOTE: Due to fluctuation of the USA currency, the price above

mentioned is subject to change without notice


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service bulletin no. 93 - vulcan air · service bulletin no. 93 original issue: nov. 24, 1995 only...

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