Piper SB 1318: Revision B, text

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Page 1Open in PDF

Date: June 7, 2018 (S)

SERVICE

BULLETIN NO. 1318B

PIPER CONSIDERS

COMPLIANCE MANDATORY Piper Aircraft, Inc.

2926 Piper Drive Vero Beach, FL, U.S.A. 32960 (OVER) ATA/JASC: 5330 Service Bulletin (SB) 1318B supersedes SB 1318A in its entirety. For aircraft that were previously made compliant with Part I of SB 1318A, then Part I, Step 2, must be completed to be in compliance with Part I of SB 1318B. Aircraft that were previously made compliant with Part II of SB 1318A are in compliance with SB 1318B.

SUBJECT: FUSELAGE STATION 144.25 RIVET REPLACEMENT REASON FOR REVISION: SB 1318B adds a requirement to Part I to install a temporary airspeed limitations placard.

MODELS AFFECTED: SERIAL NUMBERS AFFECTED:

PA-46-600TP M600 4698004 through 4698041 COMPLIANCE TIME:

Part I. Temporary Operating Limitations: Upon receipt; prior to next flight. Part I is to remain in effect until the aircraft is made compliant with Part II of this service bulletin.

Part II. Rework: To coincide with the next regularly scheduled maintenance event, but not to exceed the next 100 hours time in service. Compliance with Part II will remove the temporary operating limitations imposed by Part I of this service bulletin.

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

PURPOSE: Part I of this service bulletin imposes temporary operating limitations.

Part II mandates the inspection of a select number of rivets common to the cockpit canopy above the left and right cockpit side windows, and, based on those findings, the installation of one of two kits, one kit per side.

Page 2Open in PDF

SERVICE BULLETIN NO. 1318B PAGE 2 of 7 SAFETY INTENT: A specific area of the cockpit canopy on affected aircraft may include rivets that were not installed in conformance to type design. If aircraft with this condition are operated at the limitations stated in the current revision of the pilot’s operating handbook, it could result in an understrength condition. Additionally, aircraft operated in this condition may not have the fatigue strength required to achieve the published structural life limit of the fuselage.

The safety intent of this service bulletin is to improve the safety margin of the airframe at the affected area:

For short-term mitigation, accomplishing the instructions in Part I of this service bulletin reduces loading on the airframe.

For long-term mitigation, accomplishing the instructions in Part II of this service bulletin restores the airframe to original type design strength.

INSTRUCTIONS:

NOTE: Some steps in these instructions are identified as “required for compliance” (RC). If this service bulletin is mandated by an airworthiness directive (AD), the steps identified as RC must be done to comply with the AD. Steps not identified as RC are recommended and may be deviated from, done as a part of other actions, or done with accepted methods different from those given in this service bulletin, if the RC steps can be done and the airplane can be put back in a serviceable condition.

Part I. Temporary Operating Limitations NOTE: The limitations provided in the attached temporary page, and the related instrument panel placard, are precautionary until the aircraft is made compliant with Part II of this service bulletin.

1. RC – Cut out and insert the temporary page from Figure 1 into the current PA-46-600TP Pilot’s Operating Handbook (POH) VB–2366, after the existing page 2-2.

NOTE: SB 1318B, Figure 1, is the same as SB 1318A, Figure 1, “POH VB-2366 Temporary Page.” Both are acceptable for use in compliance with Part I of this service bulletin.

2. RC – Temporary Placard

a. Order one (1) Placard – Flight Limitations, Piper part number (P/N) 46G110013-701, per aircraft.

Alternatively, it is permissible to either 1) fabricate a placard or 2) utilize one of the placards in Figure 2:

1) Fabricate a placard from locally sourced materials, subject to the constraints listed below.

• The size of the placard shall be no greater than one (1) inch high by 2.75 inches wide (1 x 2 3/4).

• The layout of the text shall agree with the example fabricated placard in Figure 2.

• The colors used shall be either white text on a matte black background, or black text on a white background.

• The font size shall be nine points (9 pt.) or larger.

• The text shall be comprised of all upper case (capital) letters.

• The typeface shall be chosen for its legibility. Examples include Alternate Gothic #2, Arial, Calibri, and Helvetica.

2) Print and cut out either of the example placards from Figure 2. Print the placard at the actual size.

For these alternatives, the printing material and adhesive used (e.g.: double-sided tape; clear, single-sided tape; or a suitable adhesive-backed material) is at the discretion of the owner/operator. The placard must be installed securely with none of its text concealed.

b. Install the placard onto the cockpit instrument panel in the location shown in Figure 3.

3. RC – Make a logbook entry documenting compliance with Part I of this service bulletin.

Page 3Open in PDF

SERVICE BULLETIN NO. 1318B PAGE 3 of 7 Figure 1 POH VB-2366 Temporary Page ISSUED: June 17, 2016 REPORT: VB-2366 2-2a/2-2bREQUIRED UNTIL SB 1318A PART II COMPLIED WITH.

2.3 AIRSPEED LIMITATIONS

SPEED KCAS KIAS MACH Vmo Mmo Maximum Operating Limit Speed Below 24,330 ft.

Above 24,330 ft.

230 ---- 232 ---- ----

0.55 Do not exceed this speed in any operation Vo Maximum Operating Maneuvering Speed 6000 LB 3750 LB 151 119 153 121 ---- ---- Do not make full or abrupt control movements above this speed.

Vfe Maximum Flaps Extended Speed T/O LND 145 108 147 112 ---- ---- Do not exceed this speed at the given flap setting Vle Maximum Landing Gear Extended Speed ---- 168 170 ---- Do not exceed this speed with the landing gear extended Vloe Vlor Maximum Landing Gear Operating Speed Extension Retraction 168 128 170 130 ---- ---- Do not operate the landing gear above this speed For PA-46-600TP airplanes serial numbers 4698004 through 4698041, the airspeed limitations on this page supersede the airspeed limitations on VB-2366 page 2-2 dated June 17, 2016.

These limitations are imposed by Piper Service Bulletin 1318A Part I and must remain in effect until the airplane is made compliant with Piper Service Bulletin 1318A Part II.

When the airplane is compliant with Piper Service Bulletin 1318A Part II, this page may be removed.

WARNING SECTION 2 PA-46-600TP LIMITATIONS Cut a straight path through the aligned crop marks.

PRINTING: to ensure correct size, for print scale choose 100% dimensions or “Actual Size.”🖨🖨 Cut a straight path through the aligned crop marks.

Page 4Open in PDF

SERVICE BULLETIN NO. 1318B PAGE 4 of 7 P/N 46G110013-701 TEMP. AIRSPEED LIMITATIONS REF SB1318 LATEST REV.

46G110013-701 Vmo Mmo 232 KIAS

0.55 M BELOW 24,330 ft ABOVE 24,330 ft TEMP. AIRSPEED LIMITATIONS V MO 232 KIAS BELOW 24,330 FT M MO 0.55 M ABOVE 24,330 FT REF. SB 1318, LATEST REVISION APPROX.

1.0 APPROX. 2.50

EXAMPLE FABRICATED PLACARD Figure 2 P/N 46G110013-701 and an Example of a Fabricated Temporary Placard 46F24A001 46F24A016-A 46G11A001-F Sh5

NXXXXX

STALL WARN

ICE SCHEDULE (PRESS OFF)

DETAIL B

PLACARD P/N 46G110013-701

SEE DETAIL B Figure 3 Instrument Panel – Temporary Placard Installation

Page 5Open in PDF

SERVICE BULLETIN NO. 1318B PAGE 5 of 7 Part II. Rework At a minimum, 16 rivets (eight per side) shall be replaced on each aircraft to comply with this service bulletin. A modification may be required as well as the rivet replacements. Two kits are available, one for either condition. One of either kit shall be required, per side, as determined by the results of the inspection included in the following steps.

NOTE: The instructions that follow apply to both the left and right sides of the fuselage.

NOTE: Some paint removal is required. Use guidance from Piper PA-46-600TP M600 Airplane Maintenance Manual, P/N 767-617, Section 20-20-00; and FAA Advisory Circular AC 43.13-1B CHG 1, Chapter 6.

1. RC – Locate the canopy area above both cockpit side windows, which is shown in Figure 4, Detail A.

2. RC – The topcoat of paint will likely obscure the rivet pattern shown. If necessary, locally remove paint to the depth required to gain visual access to the rivet heads. The removal of paint to the bare metal is not required.

3. RC – At each of the eight (8) rivets specified, per side: measure the edge distance (ED) from the center of the rivet to the edge of the skin, as shown in Figure 4, Detail A.

• If the ED for each rivet meets or exceeds 0.30 inches, only the replacement of the rivets is required. Order and install Rivet Replacement Kit, Piper Part Number (P/N) 88623-701, Revision A.

• If the ED for any of the rivets is less than 0.30 inches, modification to the airframe and rivet replacement is required. Order and install Canopy Modification Kit, Piper P/N 88624-701, Revision A.

NOTE: Rivet Replacement Kit, Piper P/N 88623-701, Revision A, contains the parts and instructions to replace the specified rivets on one side. Canopy Modification Kit, Piper P/N 88624-701, Revision A, contains parts and instructions to modify the canopy structure (including rivet replacement) on one side.

4. Remove any temporary pages that may have been placed in the current PA-46-600TP POH, VB–2366, and any temporary placards that may have been installed on the instrument panel, as part of compliance with Part I of this service bulletin.

5. RC – Make a logbook entry documenting compliance with Part II of this service bulletin.

Page 6Open in PDF

SERVICE BULLETIN NO. 1318B PAGE 6 of 7 Figure 4 Canopy Rivet Inspection

SEE DETAIL A

LEFT SIDE SHOWN (RIGHT SIDE OPPOSITE) FS

144.25 FS

144.25 FWD UP FWD

DETAIL A SKIN P/N 82317

MEASURE THE ED FOR THESE EIGHT (8) RIVETS

RIVETS FOR REFERENCE ONLY EDGE

DISTANCE (ED)

Page 7Open in PDF

SERVICE BULLETIN NO. 1318B PAGE 7 of 7 MATERIAL REQUIRED: For Part I:

• One (1) Placard – Flight Limitations, Piper P/N 46G110013-701, or equivalent

• Attached, POH VB-2366 Temporary Page, Figure 1.

For Part II: Order only one combination of kits shown below, as determined in Part II, Step 3, of this service bulletin, per aircraft:

• Two (2) Rivet Replacement Kits, Piper P/N 88623-701, Revision A

• Two (2) Canopy Modification Kits, Piper P/N 88624-701, Revision A

• One (1) each: Rivet Replacement Kit, Piper P/N 88623-701, Revision A; Canopy Modification Kit, Piper P/N 88624-701, Revision A AVAILABILITY OF PARTS: Y our Piper Approved Service Center EFFECTIVITY DATE: This service bulletin is effective upon receipt.

SUMMARY: Applicable factory participation is limited to new aircraft in warranty at the time of compliance. Factory participation will remain in effect for a period of time not to exceed 180 days from the date of this service bulletin.

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”

Page 8Open in PDF

Service Bulletin No. 1318B DATE: June 7, 2018

BULLETIN SUPPLEMENT - PROCEDURAL OPERATING INFORMATION MATERIAL ALLOWANCE: For Part I:

One (1) Placard – Flight Limitations, Piper P/N 46G110013-701, or equivalent For Part II: For aircraft in warranty only, one combination of kits shown below, as determined in Part II, Step 3, of this service bulletin, per aircraft:

• Two (2) Rivet Replacement Kits, Piper P/N 88623-701, Revision A

• Two (2) Canopy Modification Kits, Piper P/N 88624-701, Revision A

• One (1) each: Rivet Replacement Kit, Piper P/N 88623-701, Revision A; Canopy Modification Kit, Piper P/N 88624-701, Revision A LABOR ALLOWANCE: For aircraft in warranty only, contact Piper for labor allowances.

Piper Customer Service:

(+1) 772-299-2141 or CustomerService@piper.com Normal business hours are Monday through Friday, 7:30 am to 4:30 pm (Eastern).

DISPOSITION OF PARTS IN STOCK: N/A DISPOSITION OF PARTS REPLACED: D