Piper SB 552: Revision A, text

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Page 1Open in PDF

(OVER) Date: August 3, 2018 (S)

SERVICE

BULLETIN NO. 552A

PIPER CONSIDERS

COMPLIANCE MANDATORY Piper Aircraft, Inc.

2926 Piper Drive Vero Beach, FL, U.S.A. 32960 ATA/JASC: 5700 Service Bulletin (SB) 552A supersedes SB 552 in its entirety. Aircraft that were previously made compliant with SB 552 are in compliance with SB 552A.

SUBJECT: WING SPAR CARRY THROUGH ASSEMBLY

INSPECTION REASON FOR REVISION: SB 552A clarifies that all affected PA-36 models within the serial number range must comply with this service bulletin, regardless of powerplant configuration.

MODELS AFFECTED: SERIAL NUMBERS AFFECTED:

PA-36-285 Pawnee Brave 36-7360001 through 36-7560003 * PA-36-300 Pawnee Brave 36-7360001 through 36-7560003 * * NOTE: Affected aircraft that must comply with this service bulletin have the original Spar Carry Through Assembly, Piper part number (P/N) 97370-000, installed. This is physically identified by the presence of a 0.25 inch thick aluminum strap located as shown in Figure 1.

NOTE: All of the affected aircraft were delivered from the factory with a TIARA 6-285 engine. However, some of the affected aircraft may have been subsequently modified by replacing the factory-installed engine with an Avco Lycoming 300 horsepower IO-540-K1G5 engine per Piper Kit P/N 761-134. This service bulletin is applicable and mandatory for all PA-36 series Pawnee Brave models within the affected serial number range, regardless of powerplant configuration.

COMPLIANCE TIME:

• Affected aircraft with less than 2,000 hours total operation time: inspect at 2,000 hours of operation, and at each 100 hours of operation thereafter

• Affected aircraft with 2,000 hours or more total operation time: inspect within the next 25 hours of operation, and at each 100 hours of operation thereafter NOTE: The special repetitive inspection requirements of this service bulletin may be discontinued subsequent to replacement of the subject spar carry through assembly with a new Spar Carry Through Assembly, Piper P/N 76824-002.

APPROVAL: The engineering aspects of this service document have been shown to comply with the applicable Federal Aviation Regulations and are FAA approved.

Page 2Open in PDF

SERVICE BULLETIN NO. 552A PAGE 2 of 4 PURPOSE: Extensive fatigue testing of PA-36 Pawnee Brave wing structure has produced inspection, repair and, if required, replacement, guidelines applicable to the early configuration Wing Spar Carry Through Assembly, Piper P/N 97370-000. This service bulletin provides inspection details, repair procedures and, if required, wing spar carry through assembly replacement criteria applicable to the above referenced affected aircraft.

INSTRUCTIONS:

NOTE: The part numbering convention used by Piper has changed over the years. A part number that includes a dash number with a few leading zeros is equivalent to the same part number with a dash number having one or no zeros. For example, part number 12345-007 is equivalent to both 12345-07 and 12345-7. All three part numbers identify the same part.

1. Inspection (refer to attached illustration to locate specific areas/items referenced below)

a. Remove belly panel (aft of hopper) and lower wing fairings to gain access to spar carry through.·

b. Prior to cleaning the spar carry through assembly, carefully inspect the upper and lower spar cap vertical leg to spar web attachment areas, especially in the two outboard bays of the carry through.

c. Observe closely for signs of rivet failure, rivet or bolt loosening and/or spar cap vertical leg to spar web separation or “working” (movement).

1) Loosening or “working” (movement) is generally indicated by a build-up of black material between and around the surfaces that are loosening/working in relation to each other.

2) Complete rivet failure is indicated if the head or tail of the rivet is loose or has separated.

3) Be sure to record specific details concerning any damage found.

d. Clean the spar carry through assembly – use normal precautions for cleaning possible contaminated areas.

e. Inspect for any signs of spar web buckling in the outboard bays.

f. Inspect the lower spar cap and attached aluminum strap for cracks or damage. Inspect carefully for cracks at the bottom of the aluminum strap in line with the two inboard attachment bolts of the (P/N 97713-002) forged steel fittings (see Figure 1 for detail).

g. Be sure damage (if any) details are carefully recorded.

h. If no damage (as described above) is found, prepare aircraft for return to service and make appropriate log book compliance entry. No further action is required at this time – re-inspect per above at subsequent 100 hour operational intervals (refer to Note under Compliance Time, above).

2. Damage Evaluation/Repair Procedure

a. If evidence of damage in any one or more of the areas described in Steps 1.b. and/or 1.f., above, is found, the spar carry through assembly must be replaced before further operation with new Spar Carry Through Assembly, P/N 76824-002.

NOTE: Main wing spar attachment bolt assemblies, P/N 553-173 (77245-000) (four per aircraft) are not reusable and must be replaced when the spar carry through assembly is replaced.

b. If evidence of slight working of the rivets and/or bolts is found, but no complete rivet failure, buckling of the spar web or cracks in the lower spar cap or attached aluminum strap has occurred, repair affected areas as follows:

1) Replace existing MS20470AD-5 Rivets as required (refer to Figure 1 for rivet locations) with MS20470AD-6 rivets.

2) Replace bolt(s) according to Table 1 (refer to Figure 1 for bolt locations).

3) Following the above repairs, prepare aircraft for return to service and make the appropriate logbook compliance entry. Spar Carry Through Assembly, P/N 97370-00, may continue in service, subject to repetitive 100 hour inspections (refer to Note under Compliance Time, above).

Page 3OCROpen in PDF

SERVICE BULLETIN NO. 552A PAGE 3 of 4 AN4C-7A Bolts AN4C-10A Bolts (Top and Bottom)

LOOKING AFT ASSEMBLY BOTTOM VIEW SPAR WEB AN4C-11A Bolts AN5-11A Bolts (Top and Bottom) MS20470AD-5 Rivets (Top and Bottom) Plane of Possible Cracks in Aluminum Strap VIEW B-B → A Extruded Spar Upper Cap Upper Spar Cap Vertical Leg Spar Web Lower Spar Cap Vertical Leg Extruded Spar Lower Cap Aluminum Strap Forged Steel Fitting P/N 97713-002

VIEW A-A ASSEMBLY END VIEW Figure 1 Spar Carry Through Assembly

Page 4Open in PDF

SERVICE BULLETIN NO. 552A PAGE 4 of 4 MATERIAL REQUIRED: Per aircraft:

• If required, per Instructions, Step 2.a, one (1) each: Wing Spar Carry Through Assembly, Piper Part No. 76824-002

• If required per Instructions: four (4) each, Main Wing Spar Attachment Bolt Assembly, Piper P/N 553-173 (77245-000)

• Rivets, MS20470-AD6, quantity as required, per Instructions, Step 2.b.2) (procure locally)

• If required, per Table 1, quantity as required (procure locally):

• Bolt, NAS6205-12Y

• Bolt, NAS6204-12Y

• Bolt, NAS6204-10Y

• Bolt, NAS6204-8Y AVAILABILITY OF PARTS: Y our Piper Approved Service Center; locally procured – rivets and bolts EFFECTIVITY DATE: This service bulletin is effective upon receipt.

SUMMARY: Please contact your Piper Approved Service Center to make arrangements for compliance with this service bulletin in accordance with the compliance time indicated.

NOTE: Please notify the factory of any address/ownership corrections. Changes should include aircraft model, serial number, and current owner’s name and address.

Corrections and/or changes should be directed to:

PIPER AIRCRAFT, INC.

Att’n: Customer Service 2926 Piper Drive Vero Beach, FL 32960 or:

CustomerService@piper.com Please include in subject line: “Aircraft ownership update” TABLE 1

EXISTING BOLT NEW BOLT TYPE DRILL SIZE REAM TO AN5-11A NAS6205-12Y Q 0.3438/ 0.3433 AN4C-11A NAS6204-12Y I 0.2813/ 0.2808 AN4C-1OA NAS6204-10Y I 0.2813/ 0.2808 AN4C-7A NAS6204-8Y I 0.2813/ 0.2808