C130_PWS_UDLM_PDM_App_H_Examples_dtd_ 2019 09 12.pdf
PDF 7 MB Posted
- Attached to
- C-130 Contract Depot Maintenance (UDLM/PDM)
- Solicitation number
- FA850420R0001
About this file
This solicitation is for C-130 contract depot maintenance and mid-cycle paint services. The Air Force Materiel Command Lifecycle Management Center at Robins Air Force Base anticipates issuing a request for proposal for C-130 unscheduled and programmed depot maintenance that cannot be completed organically due to capacity constraints. The five-year indefinite delivery/indefinite quantity contract will predominantly use firm fixed pricing, with some cost reimbursement for travel, fuel, and over and above work. A best value source selection will be conducted according to FAR Part 15. A single award will be made to a CONUS offeror. Foreign companies will be ineligible to compete. Services will include overflow C-130 depot maintenance, mid-cycle paint, and a mixture of contract types for associated costs.
View the file
Other files
Show all 33
On GovTribe
Work with this file
- Download the original file
- Contacts named in this file
- Similar government files
- Ask GovTribe AI about this file
Text version
PWS
APPENDIX H
(3 Day Message)
SUBJ: AIRCRAFT DEPOT MAINTENANCE MOVEMENT REPORT
LOCATION: "Contractor Facility" REPORT: Three (3) Day Message
MDS: C-130H
SER NO: 74-0000
DEST: "Unit" 1ST AVAIL: 30 Aug 2018
Aircraft 74-0000 is released from PDM effective 29 Aug 18. Robins has coordinated the delivery of the aircraft on 06 Sept.
Call prior to dispatching crew to ensure aircraft availability.
PLEASE CONTACT “Contractor” MAINTENANCE OPERATIONS AT “Primary and Alternate Commercial Numbers” WITHIN 72 HOURS OF AIRCRAFT ESTIMATED AVAILABILITY DATE BEFORE DISPATCHING AIRCREW OPERATIONS SQUADRONS: UNITS MUST INSURE THAT PILOT/AIRCREW BRING WITH THEM EVERYTHING NEEDED AND ALL EQUIPMENT TO FLY THE MISSION BACK TO HOME UNIT, THIS INCLUDES ENROUTE CHARTS/PUBLICATIONS/CHECKLISTS, AND ALL MISSION SPECIFIC LIFE SUPPORT EQUIPMENT.
FOR OVERWATER MISSIONS, LAKENHEATH AND ELMENDORF, THAT REQUIRE LPU'S (LIFE PRESERVER UNITS), ARRANGEMENTS MUST BE MADE WELL PRIOR TO THE AIRCRAFT'S DEPARTURE DATE. INDIVIDUAL UNIT EQUIPMENT MUST BE IN PLACE AND INSPECTED AND SERVICEABLE WELL THROUGH AIRCRAFT DEPARTURE DATE. ABSOLUTELY NO EXCEPTIONS AND NO LOANER EQUIPMENT IS AVAILABLE. UNITS MAY CHOOOSE TO FED EX/UPS SHIP LPU'S TO THE FOLLOWING ADDRESS: “Contractor Address” OR LEAVE LPU'S AT “Contractor facility” WHILE THE JET IS IN PDM.
Mr. Hercules C-130 Contractor Master Scheduler “Commercial Number” Email of org and dispatcher
EXAMPLE 3 DAY MESSAGE
EXAMPLE 3 DAY MESSAGE APPENDIX H - REPORT EXAMPLES
FUNCTIONAL CHECK FLIGHT DEBRIEF
JON Tail Nr MDS Date Event # FCF/OCF FCF # Sch
Takeoff
766 74-0000 C130H 08/20/2018 1 FCF
(Outgoing) 0 0900
Crew to ACFT Eng St Take Off LDG FLT Time Event
Classification Landing Status Code
F/E
Crew Show
Ground Abort 0
Debriefer:
Pilot/Commander Co-Pilot Flt Engineer Scanner
Totals Defects ME MC RED X RED / RED - REPEATS RECUR
7 7 0 5 2 0 0 0 Skill
Discrepancy: ME X 22 Skill: AC Repeat Recur Abort Reason
#2 THROTTLE BINGING MID TRAVEL. REF 781A PG 8 BLK 2
Corrective Action: WUC:
22E00
How Mal:
127 Action Taken Code: F Failure Cause:
Material When Disc: A
ADJUSTED BACKLASH IN VAVLE HOUSING OPS CHECKED GOOD.
Discrepancy: ME X 22 Skill: AC Repeat Recur Abort Reason
#3 THROTTLE BINDING MID TRAVEL. REF 781A PG 8 BLK 3
Corrective Action: WUC:
22E00
How Mal:
127 Action Taken Code: F Failure Cause:
Material When Disc: A
ADJUSTED BACKLASH IN VAVLE HOUSING OPS CHECKED GOOD.
Discrepancy: ME X 22 Skill: AC Repeat Recur Abort Reason
#4 THROTTLE BINDING MID TRAVEL. REF 781A PG 9 BLK 1
Corrective Action: WUC:
22E00
How Mal:
127 Action Taken Code: F Failure Cause:
Material When Disc: A
ADJUSTED BACKLASH IN VAVLE HOUSING OPS CHECKED GOOD.
Discrepancy: ME X 45 Skill: AC Repeat Recur Abort Reason
AUX PUMP INOP RESET PHASE A, B ADN C CIRCUIT BREAKERS TURNED AUX PUMP ON,
BREAKERS POPPED AGAIN. REF 781A PG 9 BLK 2
Corrective Action: WUC:
453AS
How Mal:
242 Action Taken Code: F Failure Cause:
Material When Disc: A
EXAMPLE 3 DAY MESSAGE
REMOVED & REPLACED AUX SYSTEM PUMP OPS CHECKED GOOD.
Discrepancy: ME / 22 Skill: AC Repeat Recur Abort Reason
WHEN #3 CONDITION LEVER IS PLACED TO FEATHER, PROP FEATHERS NTS LIGHT
EXTINGUISHES. REF 781A PG 9 BLK 3
Corrective Action: WUC:
22670
How Mal:
127 Action Taken Code: F Failure Cause:
Material When Disc: A
ADJUSTED NTS SWITCH IN VALVE HOUSING. OPS CHECKED GOOD.
Discrepancy: ME / 12 Skill: AV Repeat Recur Abort Reason
WITH ADTJ COMPUTER SELECTED ADTJ TEST ON DOES NOT ILLUMINATE TROOP JUMP /
TROOP CAUTION. IN COMPUTER MANUALLY SELECTED TROOP JUMP / TROOP CAUTION
ILLUMINATES LIGHTS. REF 781A PG 10 BLK 1
Corrective Action: WUC:
12970
How Mal:
242 Action Taken Code: F Failure Cause:
Material When Disc: A
REPAIRED WIRING AT AD / TJ SWITCH OPS CHECKED GOOD. ON AIR DROP TROOP JUMP
SYSTEM.
Discrepancy: ME X 22 Skill: AC Repeat Recur Abort Reason
#1 THROTTLE BINDING MID TRAVEL. REF 781A PG 10 BLK 2
Corrective Action: WUC:
22E00
How Mal:
127 Action Taken Code: F Failure Cause:
Material When Disc: A
ADJUSTED BACKLASH IN VAVLE HOUSING OPS CHECKED GOOD.
For help contact “POC” at “Number”
EXAMPLE 3 DAY MESSAGE
Takeoff
766 74-0000 C130H 08/21/2018 2 FCF
(Outgoing) 0 0830
Crew to ACFT Eng St Take Off LDG FLT Time Event
Classification Landing Status Code
F/E Crew Show 1235 Ground Abort 0
Debriefer:
Pilot/Commander Co-Pilot Flt Engineer Scanner
Totals Defects ME MC RED X RED / RED - REPEATS RECUR
4 4 0 0 4 0 0 0
Discrepancy: ME / 45 Skill: AC Repeat Recur Abort
#2 HYD LOW PRESSURE LIGHT ILLUMINATES AT 600 PSI. REF 781A PG 15 BLK 1
Corrective Action: WUC:
45100
How Mal:
127 Action Taken Code: F Failure Cause:
Material When Disc: A
RAN ENGINES UPON SHUT DOWN #2 HYD ILLUMINATED AT 950 PSI NO DEFFECTS NOTED.
Discrepancy: ME / 22 Skill: AC Repeat Recur Abort Reason
#2 PROP RPM DECREASES FROM 102% TO 99% WHEN SWITCHED FROM NORMAL TO MECH
GOV. REINDEXED 2 TIMES NO CHANGE. REF 781A PG 15 BLK 2
Corrective Action: WUC:
22E00
How Mal:
127 Action Taken Code: F Failure Cause:
Material When Disc: A
FOUND #2 RPM %1 HIGH ON GAUGE THE ACCUTAC R2 GAUGE. PERFORMED COMPLETE RUN
UP & SYNC CHECK ALL RPMS GOOD ON ACCUTAC & ALL OPS CHECKS GOOD.
Discrepancy: ME / 22 Skill: AC Repeat Recur Abort Reason
#3 ENG FLUID LEAK AFT OF OIL COOLER FLAP. REF 781A PG 15 BLK 3
Corrective Action: WUC:
22E00
How Mal:
381 Action Taken Code: F Failure Cause:
Material When Disc: A
INSP ENGINE FOUND RESIDULE OIL TRAPPED IN PANEL SEEMS NO DEFFECTS NOTED INSIDE
ENGINE CLEANED OUT PANELS & INSP AFTER ENGINE RUN NO LEAKS NOTED.
Discrepancy: ME / 13 Skill: AC Repeat Recur Abort Reason
AIRCRAFT LEANS RIGHT. REF 781A PG 16 BLK 1
Corrective Action: WUC: How Mal: Action Taken Code: F Failure Cause: When Disc: A
EXAMPLE 3 DAY MESSAGE
13100 127 Material
STRUTS VERIFIED AND SERVICED, FUEL LOAD VERIFIED AND BALANCED ACFT LEVELED & NO
LEANING RIGHT.
For help contact “POC” at “Number”
EXAMPLE 3 DAY MESSAGE
Takeoff
766 74-0000 C130H 08/22/2018 3 FCF
(Outgoing) 1 1000
Crew to ACFT Eng St Take Off LDG FLT Time Event
Classification Landing Status Code
F/E Crew Show 1014 1035 1230 1.9 Fly Non
Release 3
Debriefer:
Pilot/Commander Co-Pilot Flt Engineer Scanner
Totals Defects ME MC RED X RED / RED - REPEATS RECUR
11 10 1 2 9 0 0 0
Discrepancy: ME / 63 Skill: AV Repeat Recur Abort
#1 UHF RADIO WHEN TURNED ON, HIGH PITCH TUNE THAT WILL NOT STOP. SUSPECT STUCK
IN TEST MODE. REF 781A PG 18 BLK 2
Corrective Action: WUC:
63000
How Mal:
Action Taken Code:
F
Failure Cause:
Other When Disc: B
CYCLED POWER ON MANUAL CONTROL HEAD. TONE WENT AWAY OPS CHECKED GOOD.
Discrepancy: MC / 12 Skill: AS Repeat Recur Abort Reason
COCKPIT FLOOR PANEL BETWEEN FE PEDESTAL & ENTRANCE DETERIORATED; FLEXES
BETWEEN METAL STRUCTURE. REF 781A PG 18 BLK 3
Corrective Action: WUC:
12318
How Mal:
Action Taken Code:
F
Failure Cause:
Material When Disc: B
R2 FLOOR BOARD.
Discrepancy: ME / 41 Skill: AC Repeat Recur Abort Reason
#2 BLEED AIR REGULATOR PRESSURE LOW; 30 PSI, 1, 3, & 4 = 40 PSI. REF 781A PG 19 BLK 1
Corrective Action: WUC:
41400
How Mal:
Action Taken Code:
F
Failure Cause:
Material When Disc: P
ADJUSTED BLEED AIR REGULATOR OPS CHECKED GOOD.
Discrepancy: ME / 22 Skill: AC Repeat Recur Abort Reason
#3 ENGINE FUEL GOVERNING, FF VS RPM OUT OF LIMITS. 1550 / 104.0 (104.5 MIN) RPM
VERIFIED WITH FREQUENCY METER. REF 781A PG 19 BLK 2
Corrective Action: WUC:
2251E
How Mal:
Action Taken Code:
F
Failure Cause:
Other When Disc: P
EXAMPLE 3 DAY MESSAGE
ADJUSTED FUEL GOVERNING OPS CHECKED GOOD.
Discrepancy: ME / 22 Skill: AC Repeat Recur Abort Reason
#3 TIT AT T/O 1087 DEGREES; 1083 DEGREES LIMIT. REF 781A PG 19 BLK 3
Corrective Action: WUC:
22GC0
How Mal:
Action Taken Code:
F
Failure Cause:
Other When Disc: P
ADJUSTED SLOPE ON TD AMP OPS CHECKED GOOD.
Discrepancy: ME / 22 Skill: AC Repeat Recur Abort Reason
#3 TIT 955 DEGREES IN NULL AT 17,000, 1007 MIN. REF 781A PG 20 BLK 1.
Corrective Action: WUC:
22GC0
How Mal:
Action Taken Code:
F
Failure Cause:
Other When Disc: P
INSP ENG FOUND ALTITUDE COMPENSATOR LINE CLOGGED WITH BAKING SODA. CLEARED
LINE IN FLT OPS CHECK DUE.
Discrepancy: ME / 14 Skill: AC Repeat Recur Abort Reason
LT AILERON PUSH PULL ROD PRESSURE SEAL LEAKS ABOVE 8' HG DIFF PRESSURE. REF 781A
PG 20 BLK 2
Corrective Action: WUC:
14110
How Mal:
Action Taken Code:
F
Failure Cause:
Material When Disc: P
ADJUSTED ROLLER &LUBED CHECKED GOOD.
Discrepancy: ME X 22 Skill: AC Repeat Recur Abort Reason
#4 PROP BRAKE FAILED AFTER INFLIGHT SHUTDOWN. REF 781A PG 20 BLK 3
Corrective Action: WUC:
2264J
How Mal:
Action Taken Code:
F
Failure Cause:
Material When Disc: P
PERFROMED PROP BRAKE FLUSH.
Discrepancy: ME X 13 Skill: AV Repeat Recur Abort Reason
W/ NLG INDICATING IN-TRANSIT & ONE THROTTLE AT FI, NLG WARNING INOP LT & RT MLG
GOOD. REF 781A PG 21 BLK 1
Corrective Action: WUC:
13200
How Mal:
Action Taken Code:
F
Failure Cause:
Other When Disc: P
REPAIRED BROKEN SPLICE AT DOWN LOCK LIMIT SWITCH OF THE NOSE GEAR.
Discrepancy: ME / 22 Skill: AC Repeat Recur Abort Reason
#1 TIT INDICATOR FLUCTUATES INTERMITTENTLY; TORQUE FF & RPM STEADY. REF 781A PG 21
BLK 2
Corrective Action: WUC:
22GCA
How Mal:
Action Taken Code:
F
Failure Cause:
Material When Disc: P
EXAMPLE 3 DAY MESSAGE
REMOVED & REPLACED TIT GAUGE OPS CHECKED GOOD.
Discrepancy: ME / 65 Skill: AV Repeat Recur Abort Reason
IFF MODE 4 FLICKERS INTERMITTENTLY CONSTANT MASTER CAUTION LIGHT. REF 781A PG 21
BLK 3
Corrective Action: WUC:
65JAA
How Mal:
Action Taken Code:
F
Failure Cause:
Material When Disc: P
R2 IFF CONTROL PANEL OPS CHECKED GOOD.
For help contact “POC” at “Number”
EXAMPLE 3 DAY MESSAGE
Takeoff
766 74-0000 C130H 08/24/2018 4 FCF
(Outgoing) 2 0900
Crew to ACFT Eng St Take Off LDG FLT Time Event
Classification Landing Status Code
F/E Crew Show 1033 1121 1218 1 Fly Non
Release 3
Debriefer:
Pilot/Commander Co-Pilot Flt Engineer Scanner
Totals Defects ME MC RED X RED / RED - REPEATS RECUR
4 4 0 2 2 0 2 0
Discrepancy: ME X 52 Skill: AV Repeat Recur Abort
PILOTS HSI INOP. REF 781A PG 37 BLK 2
Corrective Action: WUC:
526DD
How Mal:
242 Action Taken Code: F Failure Cause:
Material When Disc: B
R2 PILOTS HSI OPS CHECKED GOOD.
Discrepancy: ME X 22 Skill: AC Repeat Recur Abort Reason
#4 PROP BRAKE FAILED. REF 781A PG 37 BLK 3
Corrective Action: WUC:
2264J
How Mal:
932 Action Taken Code: F Failure Cause:
Material When Disc: P
R2 ENGINE #4 OPS CHECKED GOOD.
Discrepancy: ME / 14 Skill: AC Repeat Recur Abort Reason
LT AILERON PUSH ULL ROD PRESSURE SEAL LEAKS ABOVE 8" HG DIFF PRESS. REF 781A PG 38
BLK 1
Corrective Action: WUC:
14110
How Mal:
020 Action Taken Code: F Failure Cause:
Material When Disc: P
R2 PRESSURE SEAL OPS CHECKED GOOD.
Discrepancy: ME / 22 Skill: AC Repeat Recur Abort Reason
#1 ENGINE WILL HAVE 2,000 INCH POUNDS MORE OF TOURQUE WITH KNOBS LINED UP. FUEL
FLOW, AND TIT MATCH ON OTHER ENGINES. REF 781A PG 38 BLK 2
Corrective Action: WUC:
22GB0
How Mal:
127 Action Taken Code: F Failure Cause:
Other When Disc: P
EXAMPLE 3 DAY MESSAGE
RERIGGED #1 ENGINE THROTTLE SYSTEM AND REACCOMPLISHED BLADE ANGLES OPS
CHECKED GOOD.
For help contact “POC” at “Number”
EXAMPLE 3 DAY MESSAGE
Takeoff
766 74-0000 C130H 08/27/2018 5 FCF
(Outgoing) 3 1200
Crew to ACFT Eng St Take Off LDG FLT Time Event
Classification Landing Status Code
F/E Crew Show 1006 1035 1118 0.7 Released 1
Debriefer:
Pilot/Commander Co-Pilot Flt Engineer Scanner
Totals Defects ME MC RED X RED / RED - REPEATS RECUR
No reported defects.
For help contact “POC” at “Number”
EXAMPLE 3 DAY MESSAGE
(AMREP)
402 AMXG Revision to Scheduled Output Date Request
(A) Initial Assessment
(AA) Post Assessment Schedule Extension (POST)
Tracking Number (include Fiscal Year (FY),Mission Design Series (MDS), AMREP number for MD, and what type of AMREP; example FY14-F-15C #5 (AA))
MDS:
Aircraft Tail Number: Command:
Date of Request:
Assessment End Date:
Original In work Date: Original output Date: Original Flow Days:
New Requested Output Date: Number of days Requested: Revised Flow Days:
Reason for current Schedule Extension Request; also include the number of any previous AMREPS, if any, # of days approved and a brief synopsis of each: (continuation block on page 3 if needed)
EXAMPLE
EXAMPLE AMREP APPENDIX H - REPORT EXAMPLES
1138456613C Typewritten Text
Pre-coordination Statement: (example: Master Scheduler pre-coordinated the AMREP request with John Doe, AFLCMC/WLNA DSN 123-4567)
Digitally sign this form if you concur with the request:
Master Scheduler Name: Date: Phone Number:
(Applicable) AMXS CC/DD Name: Date: Phone Number:
402 AMXSS/MXDSA Name: Date: Phone Number:
402 CMXG CL/DD Name: Date: Phone Number:
402 AMXG CC/DD Name: Date: Phone Number:
WR-ALC CC/DV/DCM Name: Date: Phone Number:
SPM Name: Date: Phone Number:
SPM Non Concur: SPM Concur with Notes:SPM Concur:
SPM Notes (if needed):
EXAMPLE
EXAMPLE AMREP APPENDIX H - REPORT EXAMPLES
Reason for Schedule Extension Request (continued):
EXAMPLE
EXAMPLE AMREP APPENDIX H - REPORT EXAMPLES
(QUICK LOOK REPORT)
A/C 91-0XXXX Evaluation Date: 21 August 2018 C130-202-2018-0XXXXX
Bonded Repairs Anticipated: 2, replacement patches for incoming boron patches on Eng 2 and 3.
Observations:
1. Engine 1:
a) OB drag & attach angles, panels 1-3: Tool marks, corrosion, and bare metal along drag and attach angles: Submit an Organically caused 202 for drag and attach angle removal due to tool marks; BBRA
b) OB drag angle: Tool marks on drag angle: Blend IAW 1C-130A-3 and/or 1C-130A-23 guidance, Replace if grind-outs go beyond minimum drawing thickness
c) OB stud row, panels 3-4: Knife marks, tool marks, 1 unseated stud, and bare metal along stud row:
Remove and replace 1 unseated stud; BBRA
d) OB drain trough, panels 1-4: No damage noted: N/A
e) IB drag & attach angles, panels 1-3: Knife marks, corrosion, and bare metal along drag and attach angles: Submit a 202 for drag and attach angle removal due to corrosion; BBRA
f) IB drag angle: No damage noted: N/A
g) IB stud row, panels 3-4: Knife marks, tool marks, 2 unseated studs, 1 broken fastener, and bare metal along stud row: Remove and replace 2 unseated studs; Remove and replace 1 broken fastener; BBRA
h) IB drain trough, panels 1-4: Knife marks, tool marks, and bare metal along drain trough: BBRA
i) Panel 1: Knife marks, tool marks, corrosion, and bare metal on panel 1: Submit a 202 for fwd nacelle removal due to corrosion; BBRA
j) Panel 2: Knife marks, tool marks, corrosion, and bare metal on panel 2: BBRA
k) Panel 3: Knife marks, tool marks, and bare metal on panel 3: BBRA
l) Panel 4: Knife marks, tool marks, corrosion, and bare metal on panel 4: BBRA
m) Contact Engineering for inspection of damage if grind out is outside T.O. 1C-130A-23 limits
n) Note: Alodine all bare aluminum with Specification MIL-C-5541, Class 1A conversion coating on wing lower plank in vicinity of quick look area, being approximately 20” each side of engine centerline on all panels, as required, IAW T.O. 1C-130A-23 & T.O. 1-1-691.
GENERAL INFORMATION
TAIL # MDS
CURRENT
AIRFRAME
HOURS
CURRENT
CENTER WING
HOURS
CURRENT
CENTER WING
EFH
CENTER WING
LIFETIME SF
CENTER WING
RECENT SF
910XXXX C-130H 9796.8 9800.5 23281.8 2.34 2.04
SEE "NOTES" BELOW FOR IMPORTANT REMARKS
EXAMPLE
EXAMPLE QUICK LOOK REPORT APPENIDIX H - REPORT EXAMPLES
2. Engine 2:
a) OB drag & attach angles, panels 1-2: Knife marks, tool marks, and bare metal along drag and attach angles: Submit an Organically caused 202 for drag and attach angle removal due to knife marks;
BBRA
b) OB drag angle: Tool marks on drag angle: Blend IAW 1C-130A-3 and/or 1C-130A-23 guidance, Replace if grind-outs go beyond minimum drawing thickness
c) OB stud row, panels 2-3: Knife marks, tool marks, 1 gouge, and bare metal along stud row: BBRA
d) OB drain trough, panels 1-3: Knife marks and bare metal along drain trough: BBRA
e) IB drag & attach angles, panels 1-2: Knife marks, tool marks, and bare metal along drag and attach angles: Submit an Organically caused 202 for drag and attach angle removal due to knife marks;
BBRA
f) IB drag angle: Tool marks and 1 drill start on drag angle: Blend IAW 1C-130A-3 and/or 1C-130A-23 guidance, Replace if grind-outs go beyond minimum drawing thickness
g) IB stud row, panels 2-3: Tool marks, 1 gouge, and bare metal along stud row: BBRA
h) IB drain trough, panels 1-3: Tool marks and bare metal along drain trough: BBRA
i) Panel 1: Knife marks, tool marks, corrosion, improper radius, and bare metal on panel 1: Submit an
Organically caused 202 for radius recut; BBRA
j) Panel 2: Knife marks, tool marks, corrosion, and bare metal on panel 2: BBRA
k) Panel 3: Knife marks, tool marks, 2 gouges, and bare metal on panel 3, bare metal and corrosion around incoming boron patch: BBRA
l) LH Armpit: 3 gouges and bare metal on LH armpit: BBRA
m) Rainbow Fittings: Knife marks, tool marks, scratches, corrosion, and bare metal along lower and upper surface rainbow fittings: BBRA
n) Contact Engineering for inspection of damage if grind out is outside T.O. 1C-130A-23 limits
o) Note: Alodine all bare aluminum with Specification MIL-C-5541, Class 1A conversion coating on wing lower plank in vicinity of quick look area, being approximately 20” each side of engine centerline on all panels, as required, IAW T.O. 1C-130A-23 & T.O. 1-1-691.
EXAMPLE
3. Engine 3:
a) OB drag & attach angles, panels 1-2: Knife marks, tool marks, and bare metal along drag and attach angles: Submit an Organically caused 202 for drag and attach angle removal due to knife marks;
BBRA
b) OB drag angle: Tool marks and bare metal on drag angle: Blend IAW 1C-130A-3 and/or 1C-130A-23 guidance, Replace if grind-outs go beyond minimum drawing thickness
c) OB stud row, panels 2-3: Knife marks, tool marks, 1 gouge, corrosion, and bare metal along stud row:
BBRA
d) OB drain trough, panels 1-3: Knife marks, tool marks, corrosion, and bare metal along drain trough:
Submit an Organically caused 202 for drain trough removal due to knife marks; BBRA
e) IB drag & attach angles, panels 1-2: Knife marks, tool marks, corrosion, and bare metal along drag and attach angles: Submit an Organically caused 202 for drag and attach angle removal due to knife marks; BBRA
f) IB drag angle: Tool marks, 4 drill starts, and bare metal on drag angle: Blend IAW 1C-130A-3 and/or 1C-130A-23 guidance, Replace if grind-outs go beyond minimum drawing thickness
g) IB stud row, panels 2-3: Tool marks, corrosion, and bare metal along stud row: BBRA
h) IB drain trough, panels 1-3: Bare metal along drain trough: BBRA
i) Panel 1: Knife marks, tool marks, and bare metal on panel 1: BBRA
j) Panel 2: Knife marks, tool marks, and bare metal on panel 2: BBRA
k) Panel 3: Knife marks, tool marks, corrosion, and bare metal on panel 3: BBRA
l) RH Armpit: 5 gouges and bare metal on RH armpit: BBRA
m) Rainbow Fittings: Knife marks, tool marks, scratches, grindout, and bare metal along lower and upper surface rainbow fittings: BBRA
n) Contact Engineering for inspection of damage if grind out is outside T.O. 1C-130A-23 limits
o) Note: Alodine all bare aluminum with Specification MIL-C-5541, Class 1A conversion coating on wing lower plank in vicinity of quick look area, being approximately 20” each side of engine centerline on all panels, as required, IAW T.O. 1C-130A-23 & T.O. 1-1-691.
EXAMPLE
4. Engine 4:
a) OB drag & attach angles, panels 1-3: Tool marks and bare metal along drag and attach angles: BBRA
b) OB drag angle: No damage noted: N/A
c) OB stud row, panels 3-4: Knife marks, tool marks, drill start, and bare metal along stud row: BBRA
d) OB drain trough, panels 1-4: No damage noted: N/A
e) IB drag & attach angles, panels 1-3: Knife marks, tool marks, and bare metal along drag and attach angles: BBRA
f) IB drag angle: No damage noted: N/A
g) IB stud row, panels 3-4: Knife marks, tool marks, and bare metal along stud row: BBRA
h) IB drain trough, panels 1-4: Knife marks and bare metal along drain trough: Submit an Organically caused 202 for drain trough removal due to knife marks; BBRA
i) Panel 1: Knife marks, tool marks, paint, sealant, and bare metal on panel 1: Depaint and contact engineering for inspection; BBRA
j) Panel 2: Tool marks and bare metal on panel 2: BBRA
k) Panel 3: Knife marks, tool marks, scratches, and bare metal on panel 3: BBRA
l) Panel 4: Tool marks and bare metal on panel 4: BBRA
m) Contact Engineering for inspection of damage if grind out is outside T.O. 1C-130A-23 limits
n) Note: Alodine all bare aluminum with Specification MIL-C-5541, Class 1A conversion coating on wing lower plank in vicinity of quick look area, being approximately 20” each side of engine centerline on all panels, as required, IAW T.O. 1C-130A-23 & T.O. 1-1-691.
EXAMPLE
NOTES:
1) Unless otherwise stated herein, all observed scratches, corrosion, dings, & abrasions are so considerably less than .020 inches deep, that an instruction to BBRA should afford the technician ample material below the defect (a few thousandths at minimum) to properly buff & blend the defect & still have the deepest area of the resultant depression measure less than .020 inches deep as measured to the undisturbed original material surface.
2) RA shall be interpreted to mean Roto-peen, Alodine (conducted in that order).
3) BBRA shall be interpreted to mean Buff, Blend, Roto-peen, & Alodine to be conducted in that order.
4) Buff & blend shall be accomplished using cratex rods or fine/very fine grade ScotchBrite disks.
Buff & blend only as deep as necessary to remove the defect. When using cratex rods, use smallest cratex rod to remove & blend damage. Start with #8C cratex rod & finish with #8F or #8XF cratex rod. Defect shall be blended out to a length of 20 times the depth in the span wise direction & to a width of 10 times the depth in the chord wise direction. Run out radius shall be at least 10 times blend out depth.
5) Blend knife marks & other shallow damage along drag or attach angles with cratex rods to avoid removal of drag or attach angles. If drag or attach angles inhibit proper blending of knife marks & other shallow damage when using cratex rods, then said angles shall be removed (which requires removal of engine) to allow the use of ScotchBrite disks.
6) Roto-peen IAW SAE AMS2590 & 1C-130A-23, Chapter 8, Fig. 8.3.
7) Alodine bare metal in reworked areas & all bare aluminum on wing lower plank in vicinity of quick look area (approximately 20” each side of engine centerline on all panels) with Specification MIL-C-5541, Class 1A conversion coating IAW T.O. 1C-130A-23 & T.O. 1-1-691.
8) During the process of repairing underside of wing, mechanics may observe other minor defects not addressed in this quick look report. Notify WR-ALC engineering of such observations.
9) For any fasteners removed & replaced, standard procedures, cautions & warnings apply, such as:
a) Remove solid rivets per 1-1A-8 Para 1.1.16
b) Remove Hi-Tigue fasteners per T.O. 1C-130A-3 Sec. 51-70-00 Par. L & Fig. 51-70-09.
c) Remove Taper-Lok fasteners per T.O. 1C-130A-3 Sec. 51-70-00 Par. G & Fig. 51-70-07.
d) Remove Hi-Loc fasteners per T.O. 1C-130A-3 51-70-00 Par. D. & Fig. 51-70-04
e) BHEC NDI per 33B-1-2 & T.O. 1C-130A-36
f) Install B-fit HLT Hi-Tigue fasteners per T.O. 1C-130A-3 51-70-00 Par. L. & Fig. 51-70-09.
g) Wet install fasteners IAW T.O. 1C-130A-3 Figure 51-40-00 Para. T
10) Steel tools are NOT authorized to remove sealant from aluminum aircraft wing surfaces! Proper tools include scrapers made from maple, oak, phenolic laminate, plastic, or Radial Bristle Disk (available from 3M) or Sealant Removal Cutter (available from 3M). Ref 1C-130H-2-00GE-00- 1.
A/C 91-0XXXX Evaluation Date: 21 August 2018 C130-202-2018-0XXXXX
EXAMPLE
F W D
OUTBD
Engine #1
A/C 91-0XXXX
Evaluation Date: 21 August 2018 C130-202-2018-0XXXXX
Trailing edge
Panel 3
Panel 4
Panel 2
Panel 1
Leading edge
EXAMPLE
Engine #1
A/C 91-0XXXX
Evaluation Date: 21 August 2018 C130-202-2018-0XXXXX
Tool marks, corrosion, and bare metal along OB drag and attach angles, panel 1
Tool marks and bare metal along OB drag and attach angles, panels 1-2
Tool marks, corrosion, and bare metal along OB drag and attach angles, panel 2
Knife marks, tool marks, corrosion, and bare metal along OB attach angle, panels
2-3
Knife marks, tool marks, unseated stud, and bare metal along OB stud row , panel
Close-up of unseated stud at OB stud row, panel 3
EXAMPLE
F W D
OUTBD
ENGINE #2
A/C 91-0XXXX Evaluation Date: 21 August 2018 C130-202-2018-0XXXXX
Trailing edge
Panel 3
Panel 2
Panel 1
Leading edge
EXAMPLE
Engine #2A/C 91-0XXXX Evaluation Date: 21 August 2018
C130-202-2018-0XXXXX
Knife marks, tool marks, and bare metal along OB drag and attach angles, panel 1
Knife marks, tool marks, and bare metal along OB drag and attach angles, panel 1
Knife marks, tool marks, and bare metal along OB drag and attach angles, panel 2
Knife marks and bare metal along OB attach angle, panel 2
Knife marks, tool marks, and bare metal along OB stud row, panels 2-3
Knife marks, tool marks, 1 gouge, corrosion, and bare metal along OB stud row, panel 3
EXAMPLE
Left Wing Lower Rainbow
IN
BD
A/C 91-0XXXX Evaluation Date: 21 August 2018 C130-202-2018-0XXXXX
Tr ai lin g e dg e
Pa ne l 4
Pa ne l 3
Pa ne l 2
Pa ne l 1
Le ad in g ed ge
EXAMPLE
Left Wing Lower Rainbow
Knife marks, tool marks, and bare metal along LH lower rainbow fittings, panel 1
Knife marks, tool marks, and bare metal along LH lower rainbow fittings, panel 2
Knife marks, tool marks, corrosion, and bare metal along LH lower rainbow fittings, panel 3
Knife marks, tool marks, corrosion, and bare metal along LH lower rainbow fittings, panel 4
Knife marks, tool marks, and bare metal along LH lower rainbow fittings, panels 1-
Knife marks, tool marks, corrosion, and bare metal along LH lower rainbow fittings, panels 3-4
EXAMPLE
ENGINE #3
Trailing edge
Panel 3
Panel 2
Panel 1
Leading edge
F W D
EXAMPLE
Engine #3
Tool marks, scratches, corrosion, and bare metal along OB stud row, panel 3
Tool marks scratches, and bare metal along OB stud row, panel 3
Knife marks and corrosion along aft edge of panel 3
Tool marks, corrosion, and bare metal along IB stud row, panel 3
Tool marks and bare metal along IB stud row, panel 3
Knife marks, tool marks, corrosion, and bare metal along IB drag and attach angles, panel 1
EXAMPLE
Right Wing Lower Rainbow
O U
TBD
A/C 91-0XXXX Evaluation Date: 21 August 2018 C130-202-2018-0XXXXX
Le ad in g e dg e
Pa ne l 1
Pa ne l 2
Pa ne l 3
Pa ne l 4
Tr ai lin g ed ge
EXAMPLE
Right Wing Lower Rainbow
Knife marks, tool marks, and bare metal along RH lower rainbow fittings, panel 1
Knife marks, tool marks, and bare metal along RH lower rainbow fittings, panel 2
Knife marks, tool marks, and bare metal along RH lower rainbow fittings, panel 3
Knife marks, tool marks, and bare metal along RH lower rainbow fittings, panel 4
EXAMPLE
ENGINE #4
Trailing edge
Panel 3
Panel 4
Panel 2
Panel 1
Leading edge
F W D
EXAMPLE
Engine #4
Close up view of drill start at stud row, panel 3
Tool marks and bare metal along OB stud row, panels 3-4
Tool marks and bare metal along OB stud row, panel 4
Tool marks and bare metal along OB stud row, panel 4
Tool mark along aft edge of panel 4 Tool marks along IB stud row, panel 4
EXAMPLE
Left Wing Upper Rainbow
BD
A/C 91-0XXXX Evaluation Date: 21 August 2018 C130-202-2018-0XXXXX
Le ad in g g e dg e
Pa ne l 1
Pa ne l 2
Pa ne l 3
Pa ne l 4
Tr ai lin g e dg e
EXAMPLE
Left Wing Upper Rainbow
Knife marks, tool marks, scratches, and bare metal along LH upper rainbow fittings, panel 1
Knife marks, tool marks, scratches, and bare metal along LH upper rainbow fittings, panel 3
Knife marks, tool marks, scratches, and bare metal along LH upper rainbow fittings, panel 4
Knife marks, tool marks, scratches, and bare metal along LH upper rainbow fittings, panels 3-4
EXAMPLE
Right Wing Upper Rainbow
BD
A/C 91-0XXXX Evaluation Date: 21 August 2018 C130-202-2018-0XXXXX
Le ad in g g e dg e
Pa ne l 1
Pa ne l 2
Pa ne l 3
Pa ne l 4
Tr ai lin g e dg e
FWD
EXAMPLE
Right Wing Upper Rainbow
Incoming grindout of tool marks present in the center of RH upper rainbow, panel 3
Incoming grindout of tool marks in the center on panel 3, at the RH upper rainbow fittings.
Close up view of incoming grind out of tool marks on panel 3, at the RH upper rainbow fittings.
Close up view of incoming grind out of tool marks on panel 3
Close up view of incoming grind out of tool marks on panel 3
Close up view of knife marks in undercut along RH upper rainbow fittings, panel 4
EXAMPLE
Left Armpit
A/C 91-0XXXX C130-202-2018-0XXXXX
Leading edge
Panel 1
Panel 2
Panel 3
Trailing edge
3 gouges present at L/H armpit on panels 1-2 and Bare metal along panels 1,2 and 3
EXAMPLE
EXAMPLE QUICK LOOK REPORT APPENID H - REPORT EXAMPLES
Left Armpit
Close up view of 3 gouges at L/H armpit on panels 1-2
EXAMPLE
EXAMPLE QUICK LOOK REPORT APPENID H - REPORT EXAMPLES
Right Armpit
Leading edge
Panel 1
Panel 2
Panel 3
Trailing edge
FWDO
U
TB
D
5 gouges present at RH armpit at panel 1-2, Bare metal along panels 1-2
EXAMPLE
EXAMPLE QUICK LOOK REPORT APPENID H - REPORT EXAMPLES
Right Armpit
Close up view of gouges on panels 1-2 Close up view of gouges on panel 2
Close up view of gouges on panel 2
EXAMPLE
EXAMPLE QUICK LOOK REPORT APPENID H - REPORT EXAMPLES
(WORK CARD)
WORK CONTROL DOCUMENT I 1. Date: 2. Tracking#: I Page of Page
3. MDS#: 4. OPER# 5. SUBOP# 6.JON 7. Old Serial# 8. New Serial # 9. PAO 10. Planner 11. Scheduler
12. Tail Number 13. RCC 14. Technical Data Reference
15. Critical D Non Critical D 16. Initiator 17. Rework Operations# 18. wuc 19. How Mal Code 20. When Discovered Code
21. Descrepancy
22. 23. 24. 25. 26. 27. 28. 29. 30. 31.
JOB Skill Act. Inspection Date Secondary Quality SEQ Req Hrs Code "P" Stamp WORK TO BE ACCOMPLISHED Completed Mechanic Certifier Inspector
WR-ALC FORM 29, 20130329
EXAMPLE WORK CARD APPENIDX H - REPORT EXAMPLES
WORK CONTROL DOCUMENT (continued)
1. DA TE: Date the WR-A LC Fonn 29 is initiated.
2. TRACKING#: Number assigned by the computer for control of document (except on WR-ALC Fonn 29 Continuation sheet. See note 1 below).
3. MOS#: Mission Design Series of the aircraft (Example: HC-130, F-15C, C-58)
4. OP#: Operation number of the header Work Control Document (WCD)
5. SUBOP #: Sub operation number if using a definitized guide.
6. JON: Job Order Number
7. OLD Serial #: In an AFTO Fonn 95 item is removed, record serial number removed.
8. NEW SERIAL#: If an AFTO Fonn 95 item is installed, record serial number of item installed.
9. PAO: Project Administrator Officer approval.
10. PLANNER: Stamp of planner approving work to be accomplished.
11. SCHEDULER: Stamp of planner approving work to be accomplished.
12. NC SERIAL#: Year and sequence number of the aircraft (Example: 85-1368)
13. RCC: Assigned RCC Code (Example: MACPPB)
14. TECH DATA REFERENCE: Technical order required to clear the discrepancy. If additional references are needed for Job Seq# list in block 27.
15. CRITICAL OR NON-CRITICAL: Mark out the category that does not apply.
16. INITIATOR: Person who initiates the WR-ALC Fonn 29.
17. REWORK: Indicated that work being accomplished is rework. Assigned by planner approving WCD.
18. WORK UNIT CODE: 5-digit code from the applicable -06 manual.
19. HOW MAL CODE: 3-digit code from the applicable -06 manual.
20. WHEN DISCOVERED CODE: From applicable -06 manual.
21. DISCRP ANCY: Description of the defect found.
22. JOB SEQ#: Number each line in order beginning with I (i.e. 1,2,3,4,etc.)
23. SKILL REQUIRED: Skill perfonning task
24. ACTUAL HRS: Time it took the mechanic to accomplish the work. This block is to be filled out by the mechanic perfonning the maintenance.
25. INSPECTION CODE: PAC Certification Code assigned by production supervisor. Designates the certification requirements of work to be perfonned.
26. "P" ST AMP: Stamp of supervisor reviewing the task and assigning to inspection code.
27. WORK TO BE ACCOMPLISHED: Description of the task to be perfonned including all follow-on maintenance.
28. DATE COMPLETED: Date task completed.
29. MECHANIC: Stamp of mechanic certifying completion of a task.
30. SECONDARY CERTIFIER: Stamp of mechanic certifying completion of a task.
31. QUALITY INSPECTOR: Used by quality assurance personnel to certify and "Q" coded operations.
* Note 1: On the WR-ALC Fonn 29 Continuation Sheet, manually record the tracking number from the applicable WR-ALC Fonn 29.
WR-ALC FORM 29, 20130329
EXAMPLE WORK CARD APPENIDX H - REPORT EXAMPLES
| 1 3 Day Message Example |
| Three (3) Day Message |
| 74-0000 FCF # 1 Example |
| 74-0000 FCF # 2 Example |
| 74-0000 FCF # 3 Example |
| 74-0000 FCF # 4 Example |
| 74-0000 FCF # 5 Example |
| 2 - AMREP Request Template V16 |
| 3 Quick Look Report Example 1 |
| Slide Number 1 |
| Slide Number 2 |
| Slide Number 3 |
| Slide Number 4 |
| Slide Number 5 |
| Slide Number 6 |
| Slide Number 7 |
| Slide Number 8 |
| Slide Number 9 |
| Slide Number 10 |
| Slide Number 11 |
| Slide Number 12 |
| Slide Number 13 |
| Slide Number 14 |
| Slide Number 15 |
| Slide Number 16 |
| Slide Number 17 |
| Slide Number 18 |
| Slide Number 19 |
| Slide Number 20 |
| Slide Number 21 |
| Slide Number 22 |
| Slide Number 23 |
| Slide Number 24 |
| Slide Number 25 |
| 4 - WRALC Example Work Card Feb 19 |
| Blank Page |
| Blank Page |
| Blank Page |
| Blank Page |
| Tracking Number (include Fisca_w4pcHCKGauUp3wgAWnVSaw: |
| MDS:_oQnP3M*5q5GLDfBBFtjWGg: |
| Aircraft Tail Number:_ViLl4qTLKDZ3WTsg7qK7Zw: |
| Command:_a1XTmEDrB2k2ssLkMW09Jw: |
| Date of Request:_qP1DV8R-zfyhbp63FPzjqw: |
| Assessment End Date:_KYtX3NcvcpBqzE1VwnEHEw: |
| Original In work Date:_I2nxmrCo92SpF6t4q40PMQ: |
| Original output Date:_4kvpCZxEec0bHQxVTSIIdA: |
| Original Flow Days:_n*1Jh3eJy44sxJ9r4a5Zkw: |
| New Requested Output Date:_RtKM-6XKwBlhjTASOYLdtg: |
| Number of days Requested:_YIV2P3QRJ6GNlnj6zhrDhg: |
| Revised Flow Days:_tzbOQmMX99kRj1oAvARWPA: |
| Reason for Schedule Extension _t0t0PJvV35Nnmf9zy9*EJA: |
| Reset Form: |
| _ Pre-coordination Statement: _nYmrV6YFwxF2hY8EMHG0Og: |
| Master Scheduler Name:_Qlh94l*Wq5ddxzmKskTdJg: |
| Date:_H8*Xu1-R3iehZe*HOGnA5A: |
| Phone Number:_nRpHDzTZjM-Tu4qnAuTpjg: |
| AMXS CC/DD Name:_pOW5gs8UBeDlPzqCRUx2dQ: |
| Date:_9oPln4jS5FJo4ETXXcW-Nw: |
| Phone Number:_klHc9Fk3aLCOBbR3S6KmNA: |
| _402 AMXSS/MXDSA Name: _ywVsTkuBL-t0ne4XdJXFmg: |
| Date:_P5N1bvT1mg1je*wXYmSvHg: |
| Phone Number:_n3GTk5meX1mXzTiGmajdrA: |
| _402 CMXG CL/DD Name:_SQtAv5yMiWUquMtp3qMotg: |
| Date:_xX3P6pA6YNYS0fZQoPS87A: |
| Phone Number:_mI2LMZtOeP90jH-mI534ng: |
| _402 AMXG CC/DD Name:_7WhBx6NJ1crAzO-G4fw-cw: |
| Date:_9V3LzMlEgYs1AwQVBLktzg: |
| Phone Number:_2JtkUocyHSfdOlXC-JAmtA: |
| WR-ALC CC/DV/DCM Name:_K2inWr3*2iMuvioFYg2EAA: |
| Date:_YCfCjoXd6KkRPJ7HOIG6zQ: |
| Phone Number:_FKN1viHAqAQAvTye5mxH4Q: |
| SPM Name:_Qfw5uSAR-ioL5-ysnt2atA: |
| Date:_JoyF5-9UVObzFM1KyXQt6w: |
| Phone Number:_Rtk4j6EeVtpHK45Tio*yqg: |
| Check Box1: Off |
| Check Box2: Off |
| Check Box3: Off |
| Text4: |
| fc-int01-generateAppearances: |
| Reason for Schedule Extension _9LztR5zK3ZIAR*yh3DlQPw: |
File details come from the government source that posted it. Updated .