P.68 SERIES. SERVICE BULLETIN No. 95 Rev. 2 (Supersedes all the previous issues)

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1 VulcanAir S.p.A. Via G. Pascoli, Casoria (NA) Italy Tel.: Fax: P.68 SERIES Approved by the Vulcanair Design Organisation The technical content of this document is approved under the authority of DOA No. EASA.21J.009. Operator obligations with regards to inspections, modifications and/or other technical directives and their times of compliance are laid out in the relative Airworthiness Directives. SERVICE BULLETIN No. 95 Rev. 2 (Supersedes all the previous issues) Design Organisation Approval No. AS-SB/11/020 dated 01 June 2011 RECOMMENDED SUBJECT: Modification of Flight Control transmission layout 1. GENERAL 1.1 AIRCRAFT APPLICABILITY P.68 Series aircraft up to and including S/N 400. NOTE Revision 2 of this Service Bulletin has been issued to modify items quantity of Kit No B in accordance with Service Instruction SI 56 latest revision. No additional work is required for aircraft that have already embodied the previous revisions of this Service Bulletin. This Service Bulletin issued also in Italian language up to its revision 1 is now issued only in English language. 1.2 SCOPE Modification of the Flight Control cable transmission layout for rudder, elevators and ailerons by substituting and repositioning some of the control circuit pulleys. This is necessary to optimise control function through a more effective cable/pulley coupling in basis of the results obtained from theoretical studies and fatigue testing. Control function optimization will permit the inspection intervals prescribed by Service Bulletin No.75 Rev. 2 to be increased. New Inspection intervals for the P.68 series aircraft are laid down in Service Bulletin No.75 Rev. 3. Rev. 2 dated 31 May 2011 Page 1 of 13

2 1.3 DESCRIPTION From theoretical and experimental analyses effected on the flight control cable transmission system in order to discover the causes of control cable fraying, it was found that this phenomenon was due to a less than ideal cable/pulley coupling. The problem was more frequent in certain areas of the rudder, stabilator and aileron control circuits. Modification of the control circuit layout for the control surfaces in these areas was therefore considered necessary. RUDDER The rudder circuit needs to be modified in the following three areas: 1. The pulleys positioned under the floor panels alongside frame No.3 on both sides of the circuit are substituted by pulley types MS B. 2. The second rudder circuit modification only involves aircraft fitted with a photogrammetry hatch. Both the original right hand circuit pulleys positioned alongside frames 6 and 7 that allow the cable to make the necessary double turn to go around the hatch positioned in the underbelly, are substituted by greater diameter MS pulleys. To avoid the risk of the new configuration pulleys protruding into the hatch area and consequently interfering with installed sensor equipment it was considered necessary to move both pulleys forward. The first is mounted on supports positioned forward of frame N 6 and the second is mounted on two plates positioned between the rear of frame N 6 and the photogrammetry hatch forward wall. 3. The third modification, also applicable to aircraft equipped with the photogrammetry hatch, involves the aluminium pulleys positioned between frames 9 and 10 that re-align the cable after its deviation around the hatch. These pulleys are also replaced with greater diameter MS pulleys. STABILATOR The part of the stabilator layout that requires modification involves the right hand side of the circuit. The pulley positioned between frames 6 and 7 that takes the cable around the photogrammetry hatch is replaced with a MS version, positioned co-axially with those of the same type utilised for the rudder control circuit. The stabilator circuit pulley is mounted on a support fixed between the forward face of the upper plate that acts as a support for the rudder circuit pulley and the hatch forward wall. AILERONS Modification of the aileron circuit involved elimination of the bronze cable guide positioned alongside frame No.8 and installation of a MS B type pulley having a more suitable diameter with respect to the control cable. The modification, which is applicable only to aircraft fitted with the photogrammetry hatch, has not resulted in any relevant variation in system structure. Rev. 2 dated 31 May 2011 Page 2 of 13

3 1.4 WORK COMPLETION At operator s discretion. 1.5 MANHOURS Manhours for application of this Service Bulletin are estimated to be around 70 hours for aircraft without the photogrammetry hatch and around 120 hours for aircraft with the hatch installed. This includes the time to access the components and the time necessary to restore the aircraft to an airworthy condition. 1.6 SPECIAL TOOLS No special tools are required. 1.7 WEIGHT AND BALANCE Not Applicable 1.8 ELECTRICAL LOAD Not Applicable 1.9 REFERENCES Service Instruction No.56 Repair Scheme: R.0307 Hatch Installation in fuselage underbelly Forward of Frame 3. R.0308 Hatch Installation in fuselage underbelly Rear of Frame 3. R.0309 Mod. P68/03 Inst. Modification of station at Frame 3 R.0310 Mod. P68/03 Inst. Modification of station between Frame 6 and Hatch. R.0311 Mod. P68/03 Inst. Modification of station between Frames 9 and 10 R.0312 Mod. P68/03 Inst. Modification of station at Subframe 8 R.0313 Mod. P68/03 Modification of inspection hatch in fuselage floor 1.10 AIRCRAFT DOCUMENTATION Maintenance Manual Parts Catalogue 1.11 MAINTENANCE FACILITIES Work may be carried out by VulcanAir S.p.A. or by a Service Station authorised to carry out maintenance at the required level. Rev. 2 dated 31 May 2011 Page 3 of 13

4 2. WORK INSTRUCTIONS Refer to Service Instruction No.56 latest revision for work instructions relative to the modification procedure. In addition, with a view to standardising primary and secondary flight control cable inspection intervals, including those fitted to aircraft not affected by this bulletin, carry out an inspection as per paragraph 2.1 of service Bulletin No.75 Rev. 3 and apply the following criteria: Only cables with all strands intact that show no sign of wear and/or corrosion are acceptable. 3. MATERIAL INFORMATION Kit applicability for Partenavia P.68 Series aircraft is laid down in the following table: S/N 001 to S/N 015 S/N 016 to S/N 207 S/N 208 To S/N 388 excluding S/N 384 AIRCRAFT TYPE NO PHOTOGRAMMETRY HATCH(*) KIT N P B /1 P68B B /3 P68C P68C-TC B /3 P68 Observer A /6 P68 Observer-TC P68 Observer WITH PHOTOGRAMMETRY HATCH (*) KIT N B / / / B / / / B / / / A / / / A / / /2 S/N 389 and on including S/N 384 P68C P68C-TC P68 Observer-TC P68 Observer B / B / / / A / / /2 NOTE In order to carry out MOD. P68/03 the underbelly centrally mounted inspection hatch positioned alongside Frame No.3 must be installed. When only one or neither hatch is installed, ask for Kit No and carry out the installation as per S.I. No.56 Rev. 2 dated 31 May 2011 Page 4 of 13

5 3.1 MATERIAL NECESSARY FOR MODIFICATION RUDDER CIRCUIT STATION AT FRAME 3 AND BETWEEN 4 AND 5 a) P.68 Series Aircraft up to S/N 388 (excluding S/N 384) KIT No A (Observer series) SUPPORT SUPPORT SUPPORT 2 4 MS B PULLEY 2 5 MS COTTER PIN CABLEGUARD 2 7 NAS SCREW 8 8 NAS1149FN832P WASHER 8 9 MS21042-L08 NUT REAR CABLE LH/RH RUDDER 2 11 MS20470-AD4-4 RIVET SPACER SPACER 1 14 MS21083N3 NUT 2 15 R.0309 REPAIR SCHEME 1 KIT No B (P.68B, P.68C, P.68C-TC) SUPPORT SUPPORT SUPPORT 2 4 MS B PULLEY 2 5 MS COTTER PIN CABLE GUARD 2 7 NAS SCREW 8 8 NAS1149FN832P WASHER 8 9 MS21042-L08 NUT REAR CABLE LH/RH RUDDER 2 11 MS20470-AD4-4 RIVETS SPACER SPACER 1 14 MS21083N3 NUT 2 15 R.0309 REPAIR SCHEME 1 Rev. 2 dated 31 May 2011 Page 5 of 13

6 In addition to Kit No A or B: Aircraft S/N 001 to S/N 015 WITHOUT PHOTOGRAMMETRY HATCH KIT No / STABILATOR TRIM CABLE CABLE FWD. RH RUDDER CONTROL RUDDER TRIM CABLE CABLE FWD. LH RUDDER CONTROL HEXAGONAL HEAD SCREW 1 6 MS B PULLEY 2 7 NAS1149F0332P WASHER 1 Aircraft S/N 001 to S/N 015 WITH PHOTOGRAMMETRY HATCH KIT No / STABILATOR TRIM CABLE CABLE FWD. RH RUDDER CONTROL RUDDER TRIM CABLE CABLE FWD. LH RUDDER CONTROL HEXAGONAL HEAD SCREW 1 6 MS B PULLEY 3 7 NAS1149F0332P WASHER SUPPORT SUPPORT 1 10 MS20470-AD4-4 RIVET 6 P.68B, P.68C, P.68C-TC Aircraft, S/N 016 to S/N 338 EXCLUDING S/N 384 WITHOUT PHOTOGRAMMETRY HATCH KIT No / STABILATOR TRIM CABLE CABLE FWD. RH RUDDER CONTROL CABLE FWD. LH RUDDER CONTROL RUDDER TRIM CABLE 1 Rev. 2 dated 31 May 2011 Page 6 of 13

7 P.68B Aircraft S/N 016 to S/N 207 WITH PHOTOGRAMMETRY HATCH KIT No / STABILATOR TRIM CABLE CABLE FWD. RH RUDDER CONTROL RUDDER TRIM CABLE CABLE FWD. LH RUDDER CONTROL 1 5 MS B PULLEY SUPPORT SUPPORT 1 P.68B, P.68C, P.68C-TC Aircraft, S/N 208 to S/N 338 EXCLUDING S/N 384 WITH PHOTOGRAMMETRY HATCH KIT No / STABILATOR TRIM CABLE CABLE FWD. RH RUDDER CONTROL RUDDER TRIM CABLE CABLE FWD. LH RUDDER CONTROL HEXAGONAL HEAD SCREW 1 6 MS B PULLEY 3 7 NAS1149F0432P WASHER SUPPORT SUPPORT 1 10 MS20470-AD4-4 RIVET 6 P.68 Observer Aircraft, S/N 208 to S/N 338 EXCLUDING S/N 384 WITHOUT PHOTOGRAMMETRY HATCH KIT No / CABLE TRIM STABILATOR CABLE FWD. RH CONTROL RUDDER CABLE TRIM RUDDER CABLE FWD. LH CONTROL RUDDER 1 Rev. 2 dated 31 May 2011 Page 7 of 13

8 P.68 Observer Aircraft, S/N 208 to S/N 338 EXCLUDING S/N 384 WITH PHOTOGRAMMETRY HATCH KIT No / STABILATOR TRIM CABLE CABLE FWD. RH RUDDER CONTROL RUDDER TRIM CABLE CABLE FWD. LH RUDDER CONTROL 1 b) P.68 Series aircraft S/N 389 and on (including S/N 384) KIT No A (Observer series) SUPPORT SUPPORT SUPPORT 1 4 MS20470-AD4-4 RIVETS 14 5 NAS SCREW 8 8 NAS1149FN832P WASHER 8 9 MS21042-L08 NUT 8 10 MS B PULLEY 2 11 MS COTTER PIN 1 12 MS COTTER PIN REAR CABLE LH RUDDER REAR CABLE LH/RH RUDDER CABLE GUARD 1 14 MS21083N4 NUT 1 14 MS21083N3 NUT 1 15 R.0309 REPAIR SCHEME 1 Rev. 2 dated 31 May 2011 Page 8 of 13

9 KIT No B (P.68B, P.68C, P.68C-TC) SUPPORT SUPPORT SUPPORT 1 4 MS20470-AD4-4 RIVETS 14 5 NAS SCREW 8 8 NAS1149FN832P WASHER 8 9 MS21042-L08 NUT 8 10 MS B PULLEY 2 11 MS COTTER PIN 1 12 MS COTTER PIN REAR CABLE LH RUDDER REAR CABLE LH/RH RUDDER CABLE GUARD 1 14 MS21083N4 NUT 1 14 MS21083N3 NUT 1 15 R.0309 REPAIR SCHEME 1 In addition to kit No A o B: For P.68C, P.68C-TC A/C WITHOUT Photogrammetry Hatch KIT No / CABLE FWD. RH, CONTROL - RUDDER CABLE, TRIM - RUDDER 1 For P.68C, P.68C-TC A/C WITH Photogrammetry Hatch KIT No / CABLE FWD. RH, CONTROL - RUDDER CABLE, TRIM - RUDDER 1 3 NOR CABLE GUARD 2 4 MS B PULLEY SCREW, HEX HEAD 1 6 NAS1149F0332P WASHER 1 7 MS21083N3 NUT SPACER 1 9 MS COTTER PIN SUPPORT LH 1 Rev. 2 dated 31 May 2011 Page 9 of 13

10 For P.68 Observer Series Aircraft WITH Photogrammetry Hatch KIT No / CABLE FWD, RH, CONTROL - RUDDER 1 3 NOR CABLE GUARD 2 4 MS B PULLEY SCREW, HEX HEAD 1 6 NAS1149F0332P WASHER 1 7 MS21083N3 NUT SPACER 1 9 MS COTTER PIN SUPPORT LH RUDDER AND STABILATOR CIRCUIT STATION BETWEEN FRAME 6 AND PHOTOGRAMMETRY HATCH P.68 Series Aircraft WITH Photogrammetry Hatch KIT No SUPPORT SUPPORT SUPPORT SUPPORT SUPPORT SUPPORT SUPPORT REAR CABLE RH/LH - STABILATOR 2 9 MS PULLEY BEARING SPACER 1 12 AN 4-12A SCREW, DOME HEAD 1 13 AN 4-26A SCREW 1 14 AN 4-11A SCREW 1 15 NAS SCREW 6 16 NAS 1149F0463P WASHER 3 17 NAS1149FN832P WASHER MS21083N4 NUT 3 19 MS21042-L08 NUT 6 20 MS20470-AD4-4 RIVET NOR CABLE GUARD 1 22 MS COTTER PIN FILLER 2 24 R PLATE TRAPDOOR TRAPDOOR TRAPDOOR TRAPDOOR TRAPDOOR 1 Rev. 2 dated 31 May 2011 Page 10 of 13

11 Kit N (Cont d) 30 NAS1097 AD3-3 RIVET MS20470-AD4-6 RIVET 6 32 NOR P-6 TYPE A SCREW, SELF TAPPING R.0310 REPAIR SCHEME 1 34 R.0313 REPAIR SCHEME 1 35 NOR A CABLE GUARD 4 In addition to Kit No : For P.68 Series Aircraft S/N 001 to S/N 015, WITH Photogrammetry Hatch KIT No / CABLE FWD. LH/RH STABILATOR 2 For P.68 Series Aircraft S/N 016 and on, WITH Photogrammetry Hatch KIT No / CABLE FWD. LH/RH STABILATOR RUDDER CIRCUIT STATION BETWEEN FRAMES 9 e 10 P.68 Series Aircraft WITH Photogrammetry Hatch KIT No SUPPORT SUPPORT SUPPORT SUPPORT POP RIVET 4 6 MS20470-AD4-6 RIVET 6 7 MS PULLEY BEARING CABLE GUARD 2 10 AN 4-12A SCREW 2 11 NAS 1149F0463P WASHER 2 12 MS21083N4 NUT 2 13 R.0311 REPAIR SCHEME 1 14 AN 3-13A SCREW 1 15 MS COTTER PIN SPACER 1 17 MS B PULLEY 1 Rev. 2 dated 31 May 2011 Page 11 of 13

12 3.1.4 AILERON CIRCUIT MODIFICATION TO SUBFRAME 8 FWD. P.68 Series Aircraft WITH Photogrammetry Hatch KIT No MS B PULLEY 1 2 NOR CABLE GUARD 1 3 NAS 1149F0463P WASHER POP RIVET 6 5 MS20470-AD4-4 RIVET 3 6 MS20470-AD4-6 RIVET 86 7 NAS1097-AD3-6 RIVET 2 8 R.0312 REPAIR SCHEME 1 In addition to Kit No : P.68 Series Aircraft WITH Photogrammetry Hatch, S/N 001 to S/N 015 KIT No / REAR CABLE, RH, CONTROL - AILERONS 1 All P.68 Observer, P.68 Observer2, P.68TC Observer Aircraft WITH Photogrammetry Hatch, S/N 208 INCLUDED KIT No / REAR CABLE RH CONTROL AILERONS 1 P.68B, P.68C, P.68C-TC Series Aircraft, S/N 016 and on WITH Photogrammetry Hatch KIT No / REAR CABLE RH CONTROL AILERONS 1 Rev. 2 dated 31 May 2011 Page 12 of 13

13 3.1.5 HATCH INSTALLATION IN CENTRAL FUSELAGE UNDERBELLY FORWARD OF FRAME 3 KIT No FRAME HATCH DOOR 1 3 MS20470-AD4-5 RIVET 18 4 MS24693S50 SCREW, COUNTERSUNK HEAD 8 5 R.0307 REPAIR SCHEME HATCH INSTALLATION IN CENTRAL FUSELAGE UNDERBELLY REAR OF FRAME 3 KIT No FRAME HATCH DOOR 1 3 MS20470-AD4-5 RIVET 18 4 MS24693S50 SCREW, COUNTERSUNK HEAD 6 5 R.0307 REPAIR SCHEME KIT AVAILABILITY Kits shall be available within 60/90 days from receipt of the order. When ordering please specify aircraft serial number. Rev. 2 dated 31 May 2011 Page 13 of 13