Ref No.: AOT

- CN235

- 27

- 0002

Rev No.: 1 Rev Date: 22/09/2015

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: CN

- 235 Applicability: ALL

Referenced Documents:
IPC 27

- 21

- 00 Fig. 01
CMM FE150 DGAM AD 235/AD/IN/003/14



### 1. REASON FOR REVISION

The revision 01 of this AOT is issued to inform CN

- 235 operators about the release of Airworthiness Directive (AD) 235/DA/IN/003/14 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

- CN235

- 27

- 0002.



### 2. REASON

Airbus Defence and Spac e ha s received a report of a C

- 2 9 5 M operator co ncerning 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.

The pedals adjustment mechanism is the same for the C

- 295M and CN

- 235 fleet. For this reason this AOT is published.

2.1 FACTS

CN

- 235 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 hand cranked twin output drive box (see i tem 110 on IPC 27

- 21

- 00 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 (see 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 o f this AOT is to provide C N

- 2 3 5 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

- CN235

- 27

- 0002

Revision No.: 1 Date

: 22/09/2015 

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

inform CN

- 235 operators about the issuance of DGAM AD 235/DA/IN/003/14 (attached to this AOT). This AD requires to perform the same instruction s and recommendations defined in this AOT.



### 3. S HORT 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 inspe ction described with in the following paragraph before the next flight from the date of receipt of this AOT.

3.1.2 MANPOWER

To perform the visual inspection described, two persons are required. The approximated time required to perform the detailed visual inspec tion is 30 minutes.

3.2 DESCRIPTION

Perform a visual inspection inside pedals set on pilot and co

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

3.2.1 ACCESS

To get 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 openings located in the pedals box.

3.2.2 INSPECTION REQUIREME NTS

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

- pilot side.

3.2.2.1 Inspection on 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 position.
c) Check through the lateral opening s of the pedals box the cor rect 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 on the union of the pedals adjustment device when the pedals are a ctuated (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

: 22/09/2015 

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

c) Move the pedals while checking through the lateral openings of the pedals box that the union of the adjust ment device and the actuator do not move independently but jointly. d) Check that the eye

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

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

a) Put the gust lock lever i n its locked position

. b) Move the hand cranked to the rearward and forward position while checking through the lateral openings of the peda ls 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 T echnical P ubli cations do not meet adequate instructions to avoid the rotation and possible disengagement of the union.

The amended instr uctions will be included on the next AMM revision on November 2015.

4.2 IMPACTED DOCUMENTATI ON

N/AReference No.: AOT

- CN235

- 27

- 0002

Revision No.: 1 Date

: 22/09/2015 

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



### 5. REPORTING

Questions about this AOT and inspection results with or without findings 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

- CN235

- 27

- 0002

Revision No.: 1 Date

: 22/09/2015 

# 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 d isconnection of the eye

- end from actuatorReference No.: AOT

- CN235

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Revision No.: 1 Date

: 22/09/2015 

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

F igure 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

- CN235

- 27

- 0002

Revision No.: 1 Date

: 22/09/2015 

# 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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