Ref No.: AOT

- C295

- 27

- 0001
Rev No.: 1 Rev Date: 29/09/2015

SERVICES DIRECTORATE Po John Lennon s/n 28906 Getafe, Madrid, SPAIN mta.technicalservice@airbus.com 

# Alert Operators Transmission Page 1 / 7 ATA Chapter: 27 Subject: RUDDER PEDAL ADJUSTMENT DEVICE INSPECTION

Aircraft Type: C

- 295 Applicability: ALL

Referenced Documents: IPC 27

- 21

- 01 Fig. 0 1 AMM CA

- A

- 27

- 21

- 00

- 00A

- 271A

- A CMM FE150 DGAM AD 295/AD/IN/002/14



### 1. REASON FOR REVISION

The revision 01 of this AOT is issued to inform C

- 295 operators about the release of Airworthiness D irective (AD) 295/AD/IN/002/14 Edic.1 issued by DGAM ( Spanish Military Airworthiness Authority ).

No additional work is required by this revision for aircrafts who have performed the inspections required in the revision 00 of the AOT

- C295

- 27

- 0001.



### 2. REASON
Airbus Defence and Space ha s received a report of a C

- 295 oper ator concerning a mechanical disconnection that was located in the kinematic chain from the co

- pilot pedal set to the rudder control bars located under the cockpit

.

2.1 FACTS

C

- 295 aircraft includes the adjustment device P/N FE150

- 001 (AC650107) on each pedal set to permit the regulation of the pedals for pilot and co

- pilot

, by mean of a gear drive operated by a han d cranked twin output drive box (see item 110 on IPC 27

- 21

- 01 Fig.01).

During a pre

- flight check, co

- pilot pedals were found not aligned in their neutral position when the gust lock lever was on locked position. Further observations revealed that the eye

- end of the pedal adjustment device was disconnected from the actuator (s ee Figure 01).

2.2 CONSEQUENCES

A disconnection in the pilot or co

- pilot pedal adjustment device could lead to a loss of the rudder control on the affected side.

2.3 AIM

The aim of this AOT is to provide C

- 295 operators with the necessary instructions to perform a visual inspection of the pedals adjustment device in order to confirm the correct installation on both pedals for each pilot position and toReference No.: AOT

- C295

- 27

- 0001

Revision No.: 1 Date

: 29/09/2015 

# Alert Operators Transmission Page 2 / 7 ATA Chapter: 27 Subject: RUDDER PEDAL ADJUSTMENT DEVICE INSPECTION

inform C

- 295 operato rs about the issuance of DGAM AD 295/AD/IN/002/14 (attached to this AOT)

. This AD requires to perform the same instructio ns and recommendations defined in this AOT.



### 3. SHORT TERM ACTION

3.1 PLANNING AND MANPOWE R

3.1.1 ACCOMPLISHMENT TIMES CALE

Airbus Defence and Space recommend s to perform the detailed visual inspection described with in the following paragraph before the next flight from the date of receipt of th is AOT

.

3.1.2 MANPOWER

To perform the visual inspection described, two persons are required. The approx imated time required to perform the detailed visual inspection is 30 minutes.

3.2 DESCRIPTION

Perform a visual inspection inside pedals set on pilot and co

- pilot station in order to confirm the ir correct alignment and installation of the adjustment device.

3.2.1 ACCESS

To ge t access to the inspection area

, make sure that the pedals box area is free the obstacles. The pedal adjustment mechanism can be inspected through the lateral ope nings located in the pedals box.

3.2.2 INSPECTION REQUIREME NTS

NOTE : The following visual inspections must be performed on each pedal for pilot and co

- pilot side.

3.2.2.1 Inspection o f the pedals adjustment device union status

a) Adjust the pedals position to the c orrect length using the 

### hand cranked

. b) Put the gust lock lever in its locked positio n. c) Check through the lateral opening s of the pedals box the correct installation of the union between the

eye

- end and the actuator of the adjustment device.

- Check that the nut AN316C6R, the plate locking FE154

- 000

- 16 and the washer tab FE154

- 000

- 09

are correctly joined in accordance with the Figure 0 2

.

- Check that washer tab FE154

- 000

- 09 is correctly bent , over the nut on one side, and over the axle in the other side (see Figure 0 2 ), in order to avoid the rotation of the axle.

3.2.2.2 Inspection of the pedals adjustment device union when the pedals are actuated (2 persons required)

a) Adjust the pedals to the most rearward position using the hand cranked. b) Put the gust lock lever in its locked position.Reference No.: AOT

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Revision No.: 1 Date

: 29/09/2015 

# Alert Operators Transmission Page 3 / 7 ATA Chapter: 27 Subject: RUDDER PEDAL ADJUSTMENT DEVICE INSPECTION

c) Move the pedals while c heck ing through the lateral opening s of the pedals box that the union of the adjustment device and the actuator do not move indepen dently but jointly. d) Check that the eye

- end does not have an independent movement relative to t he actuator. e) Repeat the previous steps with the pedals on the most possible forward position.

3.2.2.3 Inspection of the pedals adjustment device union when the hand cranked is actuated (2 persons required)

a) Put the gust lock lever in its locked position

. b) Move the hand cranked to the rearward and forward position while checking through the lateral opening s of the pedals box that the union of the adjustment device and the actuator do not move independently. c) Check that the eye

- end does not have an independent movement relative to the actuator.

3.2.3 FINDINGS

In the case that the union is found not correctly installed, please contact Airbus Defense and S pace for further
instructions.

3.3 SPARES AND TOOLING

To accomplish this AOT it is necessary to use the following tooling: a) Torch b) Mirror



### 4. FURTHER INFORMATION

4.1 FOLLOW

- UP PLAN

Airbus Defence and Space has detected that the Technical P ublications do not meet adequate instructions to avoid the rotation and possible disengagement of the union.

T he amended instructions have be en included on the AMM April 2015 revision.

4.2 I MPACTED DOCUMENTATIO N

The impacted documentation is the following:

- Aircraft Maintenance Manual (AMM) CA

- A

- 27

- 21

- 00

- 00A

- 271A

- A RUDDER CONTROL

– Adjustment (last revision: October 15, 2012)Reference No.: AOT

- C295

- 27

- 0001

Revision No.: 1 Date

: 29/09/2015 

# Alert Operators Transmission Page 4 / 7 ATA Chapter: 27 Subject: RUDDER PEDAL ADJUSTMENT DEVICE INSPECTION



### 5. REPORTING

Questions about this AOT and inspection results are to be sent to Airbus Military Technical Assistance Center (AMTAC):

Telephone: (+34) 91 600 79 99 E

- mail: mta.technicalservice@airbus.comReference No.: AOT

- C295

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Revision No.: 1 Date

: 29/09/2015 

# Alert Operators Transmission Page 5 / 7 ATA Chapter: 27 Subject: RUDDER PEDAL ADJUSTMENT DEVICE INSPECTION



### 6. FIGURES

Figure 01

. P edals adjustment device location and disconnection of the eye

- end from actuatorReference No.: AOT

- C295

- 27

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Revision No.: 1 Date

: 29/09/2015 

# Alert Operators Transmission Page 6 / 7 ATA Chapter: 27 Subject: RUDDER PEDAL ADJUSTMENT DEVICE INSPECTION

Figure 0 2

. Correct installation of the pedals adjustment device union Washer tab bent over nut (T he other tab of the washer is bent over the axle ) Washer tab bent over the axle (The other tab of the washer is bent over the nut )Reference No.: AOT

- C295

- 27

- 0001

Revision No.: 1 Date

: 29/09/2015 

# Alert Operators Transmission Page 7 / 7 ATA Chapter: 27 Subject: RUDDER PEDAL ADJUSTMENT DEVICE INSPECTION

Released by

Yolanda Lara Electronically Validated

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