C-212 - SERVICE BULLETIN

E N G I N E C O N T R O L S P O W E R A N D R P M M E C H A N I C A L C O N T R O L S . S A F E T Y I N G O F T H E E N G I N E P O W E R C O N T R O L REVISION TRANSMITTAL SHEET

ATA SYSTEM : 76
This sheet transmits the Revision No. 1 of the Service Bullet in SB-212-76–0009. ADDITIONAL WORK Additional work is required by this revision for aircraft modified by the Original issue of this Service Bulletin. If this Service Bulletin has been accomplished in accordance with the Original issue, it is necessary to do the additional work des cribed in this revision. NOTE : The additional work consists of increasing the attachment items on

the engine power control lever. REASON The attachment system of the engine power control lever is in creased. The effectivity of the Service Bulletin is updated. CHANGES The sections of the Service Bulletin that follow are revised : - 1.A. The kit K01 is replaced by the kits K02 or K01A (dependin g on whether the Original issue of the Service Bulletin has been a ccomplished or not, respectively). Also, the aircraft MSN 480 from the version EE91 is added. An explanatory note is added. - 1.B. The necessity to accomplish the Honeywell Service Bul letin TPE331-72-2190 is added. - 1.C. The section OBJETIVE/ACTION is modified. - 1.D. The description of the work to be done is modified. - 1.M. The revision bar is incorporated because of the modifi cation of the Figure 1. - 2.C. The kit K01 becomes K01A. The new kit K02 is added. - 3.A. The work breakdown to be done is modified. - 3.B. The description of the work to be done is modified, divi ding it in A/C without the Original issue of the Service Bulletin accomplished and A/C with the Original issue of the Service Bulletin accompli shed. - The Figure 1 Sheet 2 is modified, and Figure 1 Sheet 3 and Figu re 1 Sheet 4 are added.

Date:Mar 08/2011 SB-212-76-0009 Revision No:1 Date:Aug 03/2012 Pag : 1 of 2C-212 - SERVICE BULLETIN

FILING INSTRUCTIONS This Service Bulletin has been generated electronically an d is reissued as a complete document. Replace the complete document. Put this Revision Sheet in front of the Service Bulletin. REVISION SEQUENCE ORIGINAL : Mar 08/2011 Revision: 1 - Aug 03/2012

Date:Mar 08/2011 SB-212-76-0009 Revision No:1 Date:Aug 03/2012 Pag : 2C-212 - SERVICE BULLETIN

E N G I N E C O N T R O L S P O W E R A N D R P M M E C H A N I C A L C O N T R O L S . S A F E T Y I N G O F T H E E N G I N E P O W E R C O N T R O L

1. GENERAL INFORMATION A. EFFECTIVITY (1) Models C-212-CB, C-212-CC, C-212–CE, C-212-CD, C-212-DD, C-212- DF, C-212-EE. (2) Aircraft The Version/MSN relationship is provided for information only and is correct at the time of issue in accordance with the information available to EADS-CASA. Any future changes res ulting from transfer of an aircraft from one version to another will not be reflected in this list unless the Se rvice Bulletin is revised for another reason. VERSION MSN KIT No. C4 34, 39 SB212760009K01A or K02 CB14 149, 150 SB212760009K01A or K02 CB16 125 SB212760009K01A or K02 CB20 154 SB212760009K01A or K02 CB8 89 SB212760009K01A or K02 CC14 159 SB212760009K01A or K02 CC15 161, 162 SB212760009K01A or K02 CC20 164, 165, 169,

172, 174, 175, 181 SB212760009K01A or K02

CC22 167 SB212760009K01A or K02 CC23 171 SB212760009K01A or K02 CC24 168 SB212760009K01A or K02 CC29 180 SB212760009K01A or K02

Date:Mar 08/2011 SB-212-76-0009 Revision No:1 Date:Aug 03/2012 Pag : 1 of 18C-212 - SERVICE BULLETIN VERSION MSN KIT No.
CC30 236 SB212760009K01A or K02 CC34 195, 235 SB212760009K01A or K02 CC35 192 SB212760009K01A or K02 CC37 138 SB212760009K01A or K02 CC4 209, 210, 211,

212, 214, 215, 216, 219, 220, 221, 222, 224, 225, 226, 227, 249, 250, 251, 252, 253, 254, 255, 256, 257, 274, 275, 276, 277, 278, 279, 280, 281, 282, 410, 411, 413 SB212760009K01A or K02

CC40 190, 238, 240,

242, 248 SB212760009K01A or K02
CC41 193 SB212760009K01A or K02 CC44 290 SB212760009K01A or K02 CC46 308 SB212760009K01A or K02 CC50 262, 263, 265,

272, 286, 287, 289, 292 SB212760009K01A or K02

CC60 320, 322, 324,

328, 332, 336, 347, 348, 349 SB212760009K01A or K02

CC79 273 SB212760009K01A or K02 CD58 294 SB212760009K01A or K02 CD63 291 SB212760009K01A or K02 CD67 356 SB212760009K01A or K02 CE25 261, 323 SB212760009K01A or K02

Date:Mar 08/2011 SB-212-76-0009 Revision No:1 Date:Aug 03/2012 Pag : 2C-212 - SERVICE BULLETIN VERSION MSN KIT No.
CE25/2 359 SB212760009K01A or K02 CE25/3 247 SB212760009K01A or K02 CE61 343 SB212760009K01A or K02 CE62 363 SB212760009K01A or K02 DD65 371 SB212760009K01A or K02 DF72 397, 398 SB212760009K01A or K02 EE88 474, 475 SB212760009K01A or K02 EE90 478 SB212760009K01A or K02 EE91 480 SB212760009K01A MS03 379, 393 SB212760009K01A or K02 MS60 405 SB212760009K01A or K02 TC15 9, 119 SB212760009K01A or K02 TC18 133 SB212760009K01A or K02 TC9 92 SB212760009K01A or K02 VC61 229 SB212760009K01A or K02 VF25 178 SB212760009K01A or K02 VF25/2 311 SB212760009K01A or K02 VP85 465 SB212760009K01A or K02 VP85/2 470 SB212760009K01A or K02 VP85/3 472 SB212760009K01A or K02 NOTE : The aircraft that have the Original issue of the Service

Bulletin accomplished only require the kit K02 and must accomplish the necessary instructions. (3) Spares None

Date:Mar 08/2011 SB-212-76-0009 Revision No:1 Date:Aug 03/2012 Pag : 3C-212 - SERVICE BULLETIN

B. CONCURRENT REQUIREMENTS The accomplishment of this Service Bulletin requires the pr ior or simultaneous accomplishment of the service bulletin: TPE331-72-2190 C. REASON (1) HISTORY The connection lever to the engine propeller pitch control ( PPC) shaft was found disconnected on one aircraft. (2) OBJETIVE / ACTION To prevent the occurrence of a similar case in maintenance ta sks, the attachment system of the lever is modified to incorporate a nut safetied with a cotter pin and a bolt to apply a double lock
. (3) ADVANTAGES To prevent the disconnection of the lever from the propeller pitch control shaft. (4) OPERATIONAL/MAINTENANCE CONSEQUENCE None D. DESCRIPTION To accomplish this Service Bulletin it is necessary to: FOR EACH ENGINE: - Remove the related engine cowlings. - Mark the position to help with the later assembly, then remo ve the angled joint of the lever. Discard the attaching parts. - Remove the attaching parts from the clamped end of the transmission lever and remove the splined shaft of the PPC. - On the work bench, drill the lever. - Install the lever on the splined PPC shaft in the same positi on that was marked before, with new attaching parts. - Check the measurement between the angled joint shaft and th e splined shaft of the PPC. - Fully tighten the attaching parts. - Install the attaching parts in the inner thread of the shaft , fully tighten, and safety with lockwire in the drill hole made befo re in the lever. - Check that the joints are tight and safetied. Check that the flight controls operate correctly in direction and freedom of movement. - Do the adjustments and tests. - Record the accomplishment.

Date:Mar 08/2011 SB-212-76-0009 Revision No:1 Date:Aug 03/2012 Pag : 4C-212 - SERVICE BULLETIN

E. COMPLIANCE (1) Classification Recommended (2) Accomplishment Timescale None F. APPROVAL The technical content of this document has been approved by t he authority of the DOA No. EASA.21J.032.
NOTE: This issue is a translation of SB-212-76-0009. In case of any difficulty, reference should be made to the Spanish Revision 1 issue, which has been approved by the DOA No. EASA.21J.032. G. MANPOWER The manpower estimates given in this Service Bulletin are ba sed on the direct labour cost to do the work. These estimates assume tha t the work will be done by experienced personnel, and may need to be revised upwards to suit operators’ circumstances. The estimates do not include the time to prepare, plan or inspect the work. Manufa cture and procurement of parts and tools, drying times for paints, sealants, etc, and general administration works are also not included
. ON AIRCRAFT: TBD
TOTAL MANHOURS : TBD ELAPSED TIME(HRS): H. WEIGHT AND BALANCE None I. ELECTRICAL LOAD DATA None J. REFERENCES List of Consumable Materials:

Date:Mar 08/2011 SB-212-76-0009 Revision No:1 Date:Aug 03/2012 Pag : 5C-212 - SERVICE BULLETIN Aircraft Maintenance Manual: AMM 20-20-00, AMM 20-21-00, AMM 20-24-00, AMM 71-10-00, AMM 76-10-00, AMM 76-10-10 K. PUBLICATIONS AFFECTED EFFECTIVITY: SERIES 200: Illustrated Parts Catalog: IPC 76-12-00 EFFECTIVITY: SERIES 100, 300, and 400: Illustrated Parts Catalog: IPC 76-10-10 L. INTERCHANGEABILITY/MIXABILITY Not applicable M. RELATED FIGURES - Figure 1 Modification of the Safetying of the Power Controls.

Date:Mar 08/2011 SB-212-76-0009 Revision No:1 Date:Aug 03/2012 Pag : 6C-212 - SERVICE BULLETIN

2. MATERIAL INFORMATION A. MATERIAL - PRICE AND AVAILABILITY (1) Material Operators with aircraft shown in the effectivity of this Service Bulletin should send a purchase order to EADS-CASA. Quote th e number of the Service Bulletin. The address is: EADS-CASA SERVICES - MATERIAL SUPPORT Avda. de Aragón, 404 28022 MADRID SPAIN Fax: +34 91 585 55 05 (2) Price and Availability Sales terms must be agreed between the Operator and EADS-CASA in accordance with the established procedure. B. INDUSTRY SUPPORT INFORMATION None C. LIST OF COMPONENTS SB212760009K01A FIG ITEM N/P NEW QTY UM KEYWORD ITEM N/P OLD INT INST DISP
10 CAN42 081M5 2 NUT 20 LN29522S05015 2 BOLT 30 NAS6703H14 2 BOLT 40 NAS1587A3C 2 WASHER 50 CAN42080M5 2 NUT 60 LN9025–0510L 4 WASHER 70 LN94–10012 4 PIN 100 MS20995C32 0.4 M1 WIRE 110 NAS620C10 8 WASHER 120 212–E4261–0101 2 BUSHING NOTE : The quantities given are calculated to implement the changes

on the two engines.

Date:Mar 08/2011 SB-212-76-0009 Revision No:1 Date:Aug 03/2012 Pag : 7C-212 - SERVICE BULLETIN SB212760009K02 FIG ITEM N/P NEW QTY UM KEYWORD ITEM N/P OLD INT INST DISP
10 CAN42081M5 2 NUT 30 NAS6703H14 2 BOLT 40 NAS1587A3C 2 WASHER 70 LN94–10012 4 PIN 100 MS20995C32 0.4 M1 WIRE 110 NAS620C10 8 WASHER 120 212–E4261–0101 2 BUSHING D. LIST OF MATERIALS - OPERATOR SUPPLIED (1) Consumable Materials To accomplish this Service Bul letin it is necessary to use the consumable materials listed in the referenced procedures. (2) Components None E. PARTS TO BE RE-IDENTIFIED BY THE OPERATOR None F. TOOLING - PRICE AND AVAILABILITY None G. SPECIAL TOOLS None

Date:Mar 08/2011 SB-212-76-0009 Revision No:1 Date:Aug 03/2012 Pag : 8C-212 - SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS WARNING: Make sure all warning indications are respected in the reference

procedures. A. GENERAL (1) Preparation (a) Put warning notices in position to tell the personnel tha t maintenance tasks are in progress. (b) Obey all the safety precautions. (c) Put warning notices in the correct positions to prevent accidental operation of any control or system. (2) Standard Practices (a) Standard torques. EFFECTIVITY: SERIES 100: Refer to AMM 20-20-00
. EFFECTIVITY: SERIES 200, 300, and 400: Refer to AMM 20-21-00
. (b) Control cables and pulleys. EFFECTIVITY: ALL: Refer to AMM 20-24-00
. (3) Work Breakdown To accomplish this Service Bulletin it is necessary to: FOR EACH ENGINE: - Remove the related engine cowlings. - Mark the position to help with the later assembly, then remove the angled joint of the lever. Discard the attaching parts. - Remove the attaching parts from the clamped end of the transmission lever and remove the splined shaft of the PPC. - On the work bench, drill the lever. - Install the lever on the splined PPC shaft in the same positi on that was marked before, with new attaching parts. - Check the measurement between the angled joint shaft and th e splined shaft of the PPC. - Fully tighten the attaching parts.

Date:Mar 08/2011 SB-212-76-0009 Revision No:1 Date:Aug 03/2012 Pag : 9C-212 - SERVICE BULLETIN - Install the attaching parts in the inner thread of the shaft , fully tighten, and safety with lockwire in the drill hole made before in the lever. - Check that the joints are tight and safetied. Check that the flight controls operate correctly in direction and freedom of movement. - Do the adjustments and tests. - Record the accomplishment. B. MODIFICATION (1) Preliminary operations (a) Put access platforms in the work area. (b) Remove and keep the engine cowlings of the front area and the center area to get access (Refer to AMM 71-10-00 ). (2) Removal (a) Effectivity: A/C that have not accomplished the Origina l issue of the Service Bulletin: Refer to Figure 1, Sheets 1 and 2. 1 Remove the angled joint (11) from the lever (90). Keep the splined plate (80) and discard the attaching parts (4), (5), (6). NOTE : Mark the position of the splined plate (80) on

the lever (90) before being removed to give a reference during the later installation. 2 Remove and discard the attaching parts (1), (2), (3) from the end of the lever (90) that holds the splined shaft of the PPC. NOTE : Mark the position of the lever (90) with respect

to the splined shaft of the PPC before being removed. 3 Remove and keep the lever (90) with respect to the splined shaft of the PPC and remove it from the aircraft. (b) Effectivity: A/C that have accomplished the Original is sue of the Service Bulletin: Refer to Figure 1, Sheets 1 and 3. 1 Remove the angled joint (11) from the lever (90). Keep the splined plate (80) and discard the attaching parts (4), (5), (6).

Date:Mar 08/2011 SB-212-76-0009 Revision No:1 Date:Aug 03/2012 Pag : 10C-212 - SERVICE BULLETIN NOTE : Mark the position of the splined plate (80) on

the lever (90) before being removed to give a reference during the later installation. 2 Remove and keep the attaching parts (20), (50), (60) from the end of the lever (90) that holds the splined shaft of the PPC. Discard the cotter pin (70). NOTE : Mark the position of the lever (90) with respect

to the splined shaft of the PPC before being removed. 3 Remove and keep the lever (90) with respect to the splined shaft of the PPC and remove it from the aircraft. (3) Modification of the lever Refer to Figure 1. (a) On the workbench, make a 1.5 drill hole in the lever (90) with reference to the measurements (refer to detail C). Deburr and clean the drill hole. (4) Installation (a) Effectivity: A/C that have not accomplished the Origina l issue of the Service Bulletin: Refer to Figure 1, Sheets 1 and 2. 1 Install the lever (90) on the splined shaft of the PPC in the position that was marked before. Temporarily attach it to the shaft with new attaching parts (20), (60), and (50). Tighten the new nut to the final torque with reference to the referenced procedures. Safety it with the new cotter pin (70). 2 Locate the splined plate (80) on the lever (90) in the position that was marked before. Install the threaded stud of the angled joint (11) in the plate and the lever with no change to the marked position. 3 Fasten the stud of the angled joint (11) to the lever (90) with the attaching parts (10) and (60). NOTE : At this point, check the measurement of 39 between

the shaft of the angled joint and the splined shaft of the PPC (refer to detail C).

Date:Mar 08/2011 SB-212-76-0009 Revision No:1 Date:Aug 03/2012 Pag : 11C-212 - SERVICE BULLETIN 4 Fully tighten the installed nuts (10) and (50) and safety them with a cotter pin (70) with reference to the referenced procedures. 5 Install the attaching parts (30), (40), (110), (120) in the inner thread of the PPC shaft and fully tighten with reference to the referenced procedures. Installation as described in Figure 1, Sheet 4. 6 Safety the head of the bolt with lockwire (100) through the drill hole made in the lever. 7 Check that the engine control has freedom of movement and operates in the correct direction. (b) Effectivity: A/C that have accomplished the Original is sue of the Service Bulletin: Refer to Figure 1, Sheets 1 and 3. 1 Install the lever (90) on the splined shaft of the PPC in the position that was marked before. Temporarily attach it to the shaft with the attaching parts (20), (60), and (50) kept. Tighten the new nut to the final torque with reference to the referenced procedures. Safety it with the new cotter pin (70). 2 Locate the splined plate (80) on the lever (90) in the position that was marked before. Install the threaded stud of the angled joint (11) in the plate and the lever with no change to the marked position. 3 Fasten the stud of the angled joint (11) to the lever (90) with the attaching parts (10) and (60). NOTE : At this point, check the measurement of 39 between

the shaft of the angled joint and the splined shaft of the PPC (refer to detail C). 4 Fully tighten the installed nuts (10) and (50) and safety them with a cotter pin (70) with reference to the referenced procedures. 5 Install the attaching parts (30), (40), (110), (120) in the inner thread of the PPC shaft and fully tighten with reference to the referenced procedures. Installation as described in Figure 1, Sheet 4. 6 Safety the head of the bolt with lockwire (100) through the drill hole made in the lever.

Date:Mar 08/2011 SB-212-76-0009 Revision No:1 Date:Aug 03/2012 Pag : 12C-212 - SERVICE BULLETIN 7 Check that the engine control has freedom of movement and operates in the correct direction. C. TEST (1) Check that all the joints and attachments are tight, safe , and safetied. (2) Do the adjustment/test of the power and RPM controls. EFFECTIVITY: SERIES 100 and 200: Refer to AMM 76-10-00
. EFFECTIVITY: SERIES 300 and 400: Refer to AMM 76-10-10
. D. CLOSE UP (1) Install the engine cowlings of the front area and the center area that were removed before (Refer to AMM 71-10-00 ). (2) Make sure that the work areas are clean and free from tools , equipment and foreign objects. (3) Remove the warning notices. (4) Make sure that all the tools and equipment have been remov ed from the area around the aircraft. E. DOCUMENTATION Write in the applicable aircraft records (Aircraft Modification Log Book) that you have done all the work given in this Service Bul letin. F. FIGURES See next page/s.

Date:Mar 08/2011 SB-212-76-0009 Revision No:1 Date:Aug 03/2012 Pag : 13C-212 - SERVICE BULLETIN

INTENTIONALLY LEFT BLANK

Date:Mar 08/2011 SB-212-76-0009 Revision No:1 Date:Aug 03/2012 Pag : 14C-212 - SERVICE BULLETIN

Figure 1. Modification of the Safetying of the Power Control s. (Sheet 1 of 4) Effectivity: SB212760009K01A and K02 Date:Mar 08/2011 SB-212-76-0009 Revision No:1 Date:Aug 03/2012 Pag : 15C-212 - SERVICE BULLETIN

Figure 1. Modification of the Safetying of the Power Control s. (Sheet 2 of 4) Effectivity: SB212760009K01A and K02 Date:Mar 08/2011 SB-212-76-0009 Revision No:1 Date:Aug 03/2012 Pag : 16C-212 - SERVICE BULLETIN

Figure 1. Modification of the Safetying of the Power Control s. (Sheet 3 of 4) Effectivity: SB212760009K01A and K02 Date:Mar 08/2011 SB-212-76-0009 Revision No:1 Date:Aug 03/2012 Pag : 17C-212 - SERVICE BULLETIN

Figure 1. Modification of the Safetying of the Power Control s. (Sheet 4 of 4) Effectivity: SB212760009K01A and K02 Date:Mar 08/2011 SB-212-76-0009 Revision No:1 Date:Aug 03/2012 Pag : 18C-212 - SERVICE BULLETIN

E N G I N E C O N T R O L S P O W E R A N D R P M M E C H A N I C A L C O N T R O L S . S A F E T Y I N G O F T H E E N G I N E P O W E R C O N T R O L REPORTING SHEET Please complete the appropriate item (A or B): A - SB WILL BE embodied ......................... YES/NO (if NO please comment) If YES, aircraft concerned (as per SB effectivity by default ) and planned dates (month/year) of embodiement: ....................
......................

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................................................... ......................... B - SB HAS BEEN embodied on aircraft: ................................
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................................................... ......................... Operator comments: ..................................
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................................................... ......................... From Airline: .......................................
........................ Name/Title: ........................................
......................... Signature:..................... Date: ...............
...... If operational documentation is affected (see Paragraph 1. K of this SB): If information is needed prior to next normal revision or pri or to SB embodiment, please indicate required service(s): Either : Advance data ................................. YES/NO Or : Intermediate/Temporary revision .............. YES/ NO Important Information: This SB will only be incorporated in your maintenance and operational documentation if this sheet is returned to EADS-CASA(MTAD) and signed by a duly authorised representative. With the next feasible revision, this will result in - updati ng of maintenance documentation to show pre and post SB data. - updating of maintenance and operational documentation to show post SB data after embodiment. If this SB requires previous or simultaneous accomplishmen t of other SBs, EADS-CASA(MTAD) shall automatically include them in the ma nual revisions.

Please return this completed sheet to: AIRBUS MILITARY ENGINEERING SUPPORT - SERVICE ENGINEERING Autovia A-4, km 528,5. San Pablo North. 41020 Seville (Spain) TEL: (34) 95 459 41 69 FAX: (34) 95 459 35 31

Date:Mar 08/2011 SB-212-76-0009 Revision No:1 Date:Aug 03/2012 Pag : 1 of 1