DS9 Document EFTA01119963

s M• QO•••MMv am Rd. - Savannah, Georgia 31407 Work Order Detail Repair Station: FAA CRS GR4R216M Order: SC35I348 Status: Completed Squawk: 1.20 "I N Title: HYPERION AIR, INC. Department: SC Maintenance Resolution: No Weight and Balance revisions required during this visit. Signed Off 12/4/2013 6:38:19AM By. IGGLEHART, DAVID-312188 Completed: 12/4/2013 6:38:19AM BY: IGGLEHART, DAVID-312188 Status: Completed Discrepancy: Exterior Paint and Weight & Balance Requirements. Review scope of aircraft exterior paint touch-up/repairs, and skin replacements resulting in paint reapplication, and determine affect on weight and balance. For surfaces where paint is stripped and reapplied or added on top of existing paint on an area greater than 36 square feet the thickness values will be documented before and after painting . If average thickness values remain the same, weight and balance revision is not required. Resolution: Signed Of Completed: For surfaces painted with an area greater than 36 square feet and before and after paint thickness average varies, QC review for possible weight and balance revision will be required. • Thickness will be plotted on an aircraft drawing derived from AMM chapter 6 or other suitable sketch, attached to the work order and measurements taken on a two square foot grid. • Reference CAMPS 4000, paragraph 3.5.1 for paint restrictions to flight control surfaces and RVSM certified aircraft. • Reference CAMPS 4000, total average thickness shall not exceed 6 mils. • Per CAC Mass Properties Engineering, paint thickness of 5 mils equals .055 pounds per square foot. • If after QC review, weight change is greater than 2 pounds or .05% of MAC, the weight and balance report will require recomputation. No Exterior Paint Weight and Balance revisions required during this visit. 12/4/2013 6:37:51AM IGGLEHART, DAVID-312188 12/4/2013 6:37:51AM By: IGGLEHART, DAVID-312188 Squawk: 1.21 Discrepancy: Status: Wafting approval (L) Resolution: Aircraft Ready for Return to Service. All required inspections, to include preflight inspections, maintenance tasks, operational & leak checks, related documentation, and cleaning activities complete. Aircraft returned to service for the maintenance workscope. - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Squawk: 1.22 Discrepancy: Status: Completed Resolution: Advise customer of preservation requirements per ATA Chapter 10 of the relevant maintenance manuals for Airframe, Engines, and APU; review requirements in relation to scheduled Date Promised and later potential Date Completed; and perform maintenance or preservation actions as directed by the customer and documented as a Work Order Squawk. Advised customer Signed Off 12/4/2013 6:38:05AM Inspected: 12/4/2013 10:37:36AM Completed: 12/4/2013 10:37:36AM By IGGLEHART, DAVID-312188 By: LINDEMAN, STANLEY H-300563 Br LINDEMAN, STANLEY H-300563 ,uawk: 1.23 Discrepancy: Pre-Compliance Induction inspection Status: Waiting approval (L) Resolution: Item: 2 ENGINE TAY Mark 611-8 Part II: Tay Mark 6114 Serial H: 16291 GACWorkOrderDetailspt TEST Page 5 of 15 Printed: 12/5/2013 4:12:37AM Rd XIS EFTA01119963 R.,(,)( 1 -501 Rev. 22 Work Order: Fuselage and Wings Measuring Guide riallIAMLJULDIMITI welt ec et A A • • /SS • 18 IR )0 )1 • • • • —7r- 27 22 26 25 24 23 * Note GV1 aircraft shouts. acceptable to measure points 5 & 12 adjacent to 4 & 13 for CIV-X aircraft. *AM% oa *C8OLEVA- 01 n Mnt, CO`r•h SURFACES lan.88. 1IIPERATILY PER awn NSTRuCTCfraS RH )1399.111 totes APPROX•IATIN V €01.11LLLY Ill'ACED AT u00.0.0 Page 67 of 68 GA3968 09/11 EFTA01119964 1085 Mil Readings Aircraft Is Squawk Lt SC. 351348 j Date 12-2-13 Fusela e used PosiTector 6000 #556353- Cal due 2/2014 at -toe L 1 68 1 1 103 1 1 1 2 94 2 2 79 2 2 2 3 11 1 3 3 11 7 3 3 3 4 109 4 4 196 4 4 4 5 123 5 5 105 5 5 5 6 11 5 6 6 15 6 6 6 7 11.6 7 7 128 7 7 7 8 11.7 8 8 11 7 8 8 8 9 102 9 114 9 9 9 10 14.2 1 10 85 10 10 10 11 12 1 11 14 7 11 11 11 12 15.9 12 15 5 12 12 12 13 14.7 13 12 4 13 13 13 14 17 9 14 13.5 14 14 14 15 10.3 16 14 3 16 15 15 16 16 16 Total 180.6 0 Total 0 0 Total 189.8 0 Total 0 0 Total 0 0 Total 0 0 Lt upper Md Rear Lt lower Mid Near Rt upper id Hear Rt lower Md Hoar Lt rudder Rt rudder Total ISO Total Total Divide 155 a total Divide Total Divide Total la Dade i Divide 15 Total Total Total Total Total Total Add I Add Add Add Add Add Divide Divide Divide Divide Divide Divide Tota! Average I 12 04 Total Average 1 _Total Average 1 12 65 Total Average I Total Average r Total Average EFTA01119965 1085 Mil Readings Aircraft # SC, 351348 I Date 12-2-13 Squawk # Aileron-used Pos Tector 6000 #556353- Cal due 212014 For rudder Positector 200 #559877 Cal due 9/20 4 it .upp.. Mid Rear avower Mid Rear Itt -upper Mid Rear Rt -lower Mid Rear - Lt rudder Mid Rear Rt rudder Mid Rear 1 8 67 1 4.7 46 1 8.4 83 1 4.3 42 1 49 54 1 38 48 2 8.9 83 2 5.1 4 2 9.9 68 2 3.9 56 2 59 5 2 51 54 3 8.7 7.1 3 5.5 27 3 12.5 83 3 4.5 46 3 42 51 3 42 48 4 10 74 4 5.8 4 4 11.8 91 4 3.4 43 4 66 36 4 41 47 5 6.4 5 32 5 91 5 6 5 66 47 5 35 51 6 59 6 28 6 84 6 89 6 49 54 6 52 69 7 10.8 7 35 7 12.5 7 34 7 54 7 5 8 75 8 32 8 12.1 8 36 8 54 8 48 9 67 9 41 10 5 5 10 5 9 11 6 8 11 4 12 18 12 66 Total 35.6 60.1 Total 21.1 28 Total 42.6 74.6 Total 16.1 40.6 Total 33.1 60.8 Total 25.9 62.1 Lt upper Mid Rear Lt lower Mid Rear Rt upper Mid Rear Rt lower Mod Rear Lt rudder Mid Rear Rt rudder Mid Rear Total Divide 35 6 60.1 Total Divide 21 1 28 Total Divide 42 6 74 6 Total Divide 16 1 40 6 Total Divide 33 1 60.8 Total Divide 25 9 62 1 4 8 4 8 4 8 4 8 6 12 6 12 Total 8 9 7 51 Total 5.27 3 5 Total 10 65 9.5 Total 4 02 5.0/ Total 5 51 5 (.#:. Total 4 31 S 1/ Add 16 41 Add 8 77 Add 19 95_, Add 909 Add 10 57 Add 9 48 Divide 2 Divide / Divide 2 Divide I Divide 2 Divide 2 Total Average 8.2 Total Ave ale ) 4.38 Total Average I 9.97 Total Average 4.54 Total Average 5 28 Total Average 4 74 EFTA01119966 1085 Mil Readings Aircraft a SC 351348 Date 12.2.13 Squaws a Elevators and to sot wi s used Post Tector 6000 4556353- Cal due 22014 Lt .upper Mho Rear u teat Mid Rear Rt upper Mod Rear Rt -low Mid Rear Lt top wing Rt top wing 1 6.8 6.9 1 5.2 5.1 1 7.1 8.1 1 6.5 7.4 1 1 29.9 i' 1 20.2 2 6.5 5.7 2 5.4 6.6 2 7 9 8.1 8.2 2 _I 26.7 2 24.1 3 6.6 5.3 3 6.6 5.6 3 7.7 8.1 3 7.7 81 3 I 27.7 3 14.5 4 6.1 4.3 4 4.9 5.9 4 8.1 8.8 4 7.2 71 4 t 24.8 i 4 24.8 5 6.3 6 5 5.1 5 5 7.8 9.3 5 7.8 8.8 5 I 4.2 5 22 6 6.6 6.7 6 6.6 6 6 6.3 11.7 6 6.4 6.1 6 \ 6 7 7.4 7.7 7 6.4 5.2 7 5.7 7.9 7 6.8 7.2 7 7 \ 8 7.8 6.9 8 7.1 5.1 8 5.9 7.4 8 6 6.6 8 8 9 117 53 9 117 9 6.8 9 9 10 76 55 10 7 10 73 10 10 11 8 56 11 5 4 11 5 6 11 11 12 86` 56 12 59 12 53 12 12 13 79 54 13 54 13 53 13 13 14 74 59 14 52 14 57 14 14 15 78 59 16 54 16 5 15 16 16 82 57 16 6 16 55 16 16 Total 54.1 116.7 Total 47.3 88.3 Total 56.6 122.3 Total 56.5 106 Total 113.3 0 Total 106.6 0 Lt upper Mod Rear Lt lower Mod Rear Rt upper Mod Rear Rt lower Mod Rear Lt rudder 113 3 Rt rudder 105 6 Total Divide 54.1 115.7 Total Divide 47 3 883 Total Divide 556 122 3 Total Divide 56.5 106 Total Divide Total Divide 8 16 8 16 8 16 8 16 5 5 Total 6 76 7 23 Total 5 91 5 51 Total 695 7.64 Total 706 6.62 Total 22 66 Total 21.12 Add 13 99 Add 11.42 Add 14.59 Add 13 68 Add Add Divide 2 Divide 2 Divide 2 Divide 2 Divide Divide 'Total Average 6.99 Total Average 5 71 Total Average I 7.29 Total Average L 6.84 Total Average 122.66 Total Average 21 12 EFTA01119967