Service difficulty report · Panel · Cndair CL6002B19

Difficulty date
February 7, 2020
Submitted
March 26, 2020
Operation
Air carrier
Aircraft
N709BR
Make and model
Cndair CL6002B19
Aircraft serial
7850
Aircraft time
38,208 hours, 32,915 cycles
Part
Panel
Condition
Corroded
Location
Fuselage
Stage of operation
IN
How discovered
V
Nature of condition
O
Precautionary procedure
K

As reported to the FAA. Reports are unverified, and codes are left as the FAA publishes them.

What was found

* CORROSION ON FUSELAGE AT MULTIPLE FASTENER LOCATIONS FOR PANELS 191BB AND 192BB BETWEEN APPROXIMATELY FS 409+64 AND FS409+100 BELOW STR20L AND STR20R (MARKED). (C-CHECK) RO 3/25/2020 REMOVED CORROSION ON FUSELAGE AT MULTIPLE FASTENER LOCATIONS FOR PANELS 191BB AND 192BB BETWEEN APPROXIMATELY FS 409+64 AND FS409+100 BELOW STR20L AND STR20R. REF CRJ200 SRM. NDT COMPLIED WITH PERF'D U/T INSP ON FUSELAGE SKIN BLEND OUTS IAW CRJ200 NDTM USING TUC7933 CAL DUE 04/30/20. MINIMUM THICKNESS IS .054. NDT REPORT ATTACHED. EVALUATED BLENDED AREAS. (TOTAL 35 FASTENER HOLES) ORIGINAL MATERIAL THICKNESS .058€? REF CRJ200 SRM PAGE 2 AND 5. REMAINING THICKNESS AT FOLLOWING LOCATIONS #1 .056€?, #2 .057€?, #3 .058€?, #4 .057€?, #5 .057€?, #6 .057€?, #6 .057€?, #7 .056€?, #8 .057€?, #9 .057€?, #10 .057€?, #11 .057€? #12 .056€?, #13 .057€?, #14 .056€?, #15 .056€?, #16 .054€? #17 .057€?, #18 .055€?, #19 .057€? #20 .057€?, #21 .056€?, #22 .057€?, #23 .057€? #24 .056€?, #25 .058€?, #26 .055€?, #27 .058€?, #28 .056€?, #29 .057€?, #30 .057€?, #31 .057€?, #32 .056€?, #33 .055€?, #34 .057€?, AND #35 .057€?. NO ALLOWABLE DAMAGE IN BLENDED AREAS THEREFORE FOUND TO BE OUT OF LIMITS. REF CRJ200 SRM ALL THICKNESS WERE MARKED ON PART. SEE STEP 3 OF THIS CONTI