Bernhard Baur Date: February 23, 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 2015

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. When an aircraft is parked most of the time outside 

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 1976, 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 period for compliance?

The initial inspection must be accomplished before the next flight after the effective date of 

EASA AD 2015-0023-E. No extension of the compliance is foreseen at this time.

4. Cost of parts and/or installation workhours for the owner/operator (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 maintenance 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 condition:

Design Problem Quality Control Problem Operational

Maintenance Unapproved Parts Other (Specify)

Other: N/A

7. Should a ferry flight be permitted? 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 contained in the referenced airworthiness directive (AD) 

or service information.
Bernhard Baur Date: February 23, 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 aircraft (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.