Bernhard Baur Date: February 2 3, 2015

Federal Office of Civil Aviation (FOCA)



# FAA MCAI INFORMATION FORM

To: Federal Aviation Administration, USA

Aircraft Certification Service Federal Aviation Administration

Aircraft Manufacturer/Model ECAA AD/Revision No./Date Service Bulletin/Revision No./Date

FFA / AS 202 “Bravo” EASA AD 2015

- 0023

- E / 0 / Feb 18 2015 GFM SB 2015

- 1 / 0 / Feb 5 201 5

1. Describe the unsafe condition, AND its root cause. Include description of how the problem could affect the safe operation of the airplane.

Heavy corrosion at the airframe located under the windshield LH and RH frame (material steel) could lead to failure of the LH or RH upper fuselage longeron, which reduces the structural integrity of the affected area and could lead to catastrophic failure

. W hen an aircraft is parked most of the time outs ide
in sometimes

- wet weather conditions, it’s to be assumed that the development of corrosion could be favoured in the FWD upper stringer area.

2. Provide the number and description of occurrences which prompted the AD.

One aircraft (S/N 023), built in 197 6, was at an annual inspection at a maintenance organization in Switzerland . Additionally to this inspection, the replacement of the windshield was also planned. After the removal of the windshield, a roughness was detected at the fuselage cord. After the removal of the windshield frame, heavy corrosion at the airframe was detected. This corrosion is not visible with the windshield frame installed.

3. What is the compliance time and consequences if extended? What would be considered an appropriate
grace per

iod for compliance?

T he initial inspection must be accomplished before the next flight afte r the effective date of EASA AD 2015

- 0 0 23

- E. No extension of the compliance is foreseen at this time.

4. Cost of parts and/or installation workhours for the owner/op erator (data from the manufacturer and their supplier, if applicable)

The number of work hours for the initial inspection is expected to be 3 hours. Depending on the findings after the initial inspection

, for the removal of the corrosion or for a possible repair

, additional work hours

are possibly needed.

5. If parts are required, are they available for all aircraft?

The GFM SB 2015

- 1 requires an initial inspection and depending of the findings the removal of the corrosion according the applicable maintenan ce manual and AC43.13

- 1B

, if possible. In all other cases the contracted DOA organization has to be contacted for an appropriate repair solution. No replacement parts are available at this time.

6. What category best describes the cause of the unsafe condi tion:

Design Problem Quality Control Problem Operational

Maintenance Unapproved Parts Other (Specify)

Other: N/A

7. Should a ferry flight be permitt ed? If no, why not?

Yes No In support of the FAA’s actions to address your country’s mandatory continued airworthiness information (MCAI) in the United States, please provide the items highlighted below, if
not conta ined in the referenced airworthiness directive (AD)
or service information.Bernhard Baur Date: February 2 3, 2015

Federal Office of Civil Aviation (FOCA) 8. Number of aircraft affected, by model designation and serial number (U.S. registered and worldwide)

Roughly 80 aircraft worldwide of which 1 a ircraft (S/N 238 ) is registered in the USA.

9. Is further action anticipated to be necessary to correct this unsafe condition? If so, please provide description and recommended compliance time.

None; no further action is planned at this time.

10. Other:

None.