C-212 - SERVICE BULLETIN

ENGINE CONTROLS

POWER AND RPM MECHANICAL CONTROLS. SAFETYING OF THE ENGINE POWER CONTROL

REVISION TRANSMITTAL SHEET

ATA SYSTEM : 76

This sheet transmits the Revision No. 1 of the Service Bulletin

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 described 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 increased.

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 (depending on

whether the Original issue of the Service Bulletin has been accomplished

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 Bulletin

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 modification 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, dividing it in

A/C without the Original issue of the Service Bulletin accomplished and

A/C with the Original issue of the Service Bulletin accomplished.

- The Figure 1 Sheet 2 is modified, and Figure 1 Sheet 3 and Figure 1

Sheet 4 are added.

Date:Mar 08/2011 SB-212-76-0009

Revision No:1 Date:Aug 03/2012 Pag : 1 of 2
C-212 - SERVICE BULLETIN

FILING INSTRUCTIONS

This Service Bulletin has been generated electronically and 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 : 2
C-212 - SERVICE BULLETIN

ENGINE CONTROLS

POWER AND RPM MECHANICAL CONTROLS. SAFETYING OF THE ENGINE POWER CONTROL

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 resulting

from transfer of an aircraft from one version to another will not

be reflected in this list unless the Service 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 18
C-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 : 2
C-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 : 3
C-212 - SERVICE BULLETIN

B. CONCURRENT REQUIREMENTS

The accomplishment of this Service Bulletin requires the prior 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 tasks,

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 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 position that

was marked before, with new attaching parts.

- Check the measurement between the angled joint shaft and the 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 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.

Date:Mar 08/2011 SB-212-76-0009

Revision No:1 Date:Aug 03/2012 Pag : 4
C-212 - SERVICE BULLETIN

E. COMPLIANCE

(1) Classification

Recommended

(2) Accomplishment Timescale

None

F. APPROVAL

The technical content of this document has been approved by the

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 based on the

direct labour cost to do the work. These estimates assume that 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. Manufacture

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 : 5
C-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 : 6
C-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 the

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 CAN42081M5 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 : 7
C-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 Bulletin 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 : 8
C-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 that

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 position

that was marked before, with new attaching parts.

- Check the measurement between the angled joint shaft and the

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 : 9
C-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 Original

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 issue

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 : 10
C-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 Original

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 : 11
C-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 issue

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 : 12
C-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 removed 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 Bulletin.

F. FIGURES

See next page/s.

Date:Mar 08/2011 SB-212-76-0009

Revision No:1 Date:Aug 03/2012 Pag : 13
C-212 - SERVICE BULLETIN

INTENTIONALLY LEFT BLANK

Date:Mar 08/2011 SB-212-76-0009

Revision No:1 Date:Aug 03/2012 Pag : 14
C-212 - SERVICE BULLETIN

Figure 1. Modification of the Safetying of the Power Controls. (Sheet 1 of

4)

Effectivity: SB212760009K01A and K02

Date:Mar 08/2011 SB-212-76-0009

Revision No:1 Date:Aug 03/2012 Pag : 15
C-212 - SERVICE BULLETIN

Figure 1. Modification of the Safetying of the Power Controls. (Sheet 2 of

4)

Effectivity: SB212760009K01A and K02

Date:Mar 08/2011 SB-212-76-0009

Revision No:1 Date:Aug 03/2012 Pag : 16
C-212 - SERVICE BULLETIN

Figure 1. Modification of the Safetying of the Power Controls. (Sheet 3 of

4)

Effectivity: SB212760009K01A and K02

Date:Mar 08/2011 SB-212-76-0009

Revision No:1 Date:Aug 03/2012 Pag : 17
C-212 - SERVICE BULLETIN

Figure 1. Modification of the Safetying of the Power Controls. (Sheet 4 of

4)

Effectivity: SB212760009K01A and K02

Date:Mar 08/2011 SB-212-76-0009

Revision No:1 Date:Aug 03/2012 Pag : 18
C-212 - SERVICE BULLETIN

ENGINE CONTROLS

POWER AND RPM MECHANICAL CONTROLS. SAFETYING OF THE ENGINE POWER CONTROL

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: ..........................................

............................................................................

............................................................................

B - SB HAS BEEN embodied on aircraft: .......................................

............................................................................

............................................................................

Operator comments: ..........................................................

............................................................................

............................................................................

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 prior 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

- updating 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 accomplishment of other SBs,

EADS-CASA(MTAD) shall automatically include them in the manual 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