Attachment_017_SEMA_Appendix_M_PWS

W58RGZ-15-R-0045 Appendix M to SEMA PWS

C-12, MC-12 & RC-12 Maintenance Supplement

Document number: xx-xxxx-xxx

Date: 18 MAY 15

Revision: IX

This supplement is for Time Between Overhaul (TBO), Inspections, and Maintenance requirements. The items covered in this supplement are unique to the Army King Air aircraft.

When performing requirements of Chapters 4 and 5, the contractor (maintainer) is responsible for inspecting and maintaining all items in the area of inspection.

General: Serial number chart and references……..………………..…page 3

Engine TBO/ HSI Intervals……………………………………….page 4

C-12 and RC-12 Special Notifications……………….…………...page 5

C-12……………………Revision 8………………………….…...page 5

GR Series aircraft…………………………………………….…...page 6

RC-12………………….Revision 8………………………….…...page 7

Additions when complying with IML Phase 1……………page 9

Additions when complying with IML Phase 2……………page 10

Additions when complying with IML Phase 3……………page 11

Additions when complying with IML Phase 4……………page 13

Items to comply with ARMS aircraft Inspections...………page 14

C-12/RC-12 Daily/Preflight Check List…………………………..page 15

Aircraft Interior..…………………………………………………..page 16

Aircraft Cleaning……………………………………………….….page 19

Aircraft Preservation……………………………………………....page 20

To allow use of the Beechcraft Corporation Interactive Maintenance Library (IML) Chapters 4 and 5, the following chart is to show the applicable Army aircraft serial numbers that are equivalent to the aircraft serial numbers listed in the IML.

Serial Number Equivalency Chart for use with IML chapters 4 and 5

BC-010 thru BC-069 will be equivalent to BB-2 thru BB-1192 for effectivity

BP-001 thru BP-045 will be equivalent to BL-001 thru BL-72 for effectivity

BP-046 thru BP-071 will be equivalent to BL-73 thru BL-137 for effectivity

BL series aircraft will continue to use the IML for effectivity

BW series aircraft will continue to use the IML equivalent to BL-140 for effectivity

FE- 1 thru FE-036 will use the IML, equivalent to BL-140 for effectivity

GR-001 thru GR-019 will use BL-001 thru BL-072 for effectivity

NOTE

The following Original Equipment Manufacturer Maintenance Manuals will continue to be the primary reference for maintenance actions, repair procedures, part number research, wiring diagrams and Army unique phase inspection; all chapters, except 4 & 5, will continue to be applicable for the BC, BD, BP, GR & FE series aircraft. Hawker Beechcraft Corporation;

• Beech Super King Air A200CT (RC-12 Series) Maintenance Manual, Part Number 92-30109B1, revised 10 Sep 10. Aircraft RC-12D, (GR-1 thru GR-13), RC-12H, (GR-14 thru GR-19), RC-12K, (FE-1 thru FE-9), RC-12N, (FE-10 thru FE-24), RC-12P, (FE-25 thru FE-31, FE-33, FE-35, FE-37 and After), RC-12Q, (FE-32, FE-34, FE-36).

• Beech Super King Air A200/A200CT/B200C, Maintenance Manual, Part Number 92-37443-1C, reissued 1 Feb 09. Aircraft C-12C, (BD-1 thru BD-30), C-12D (BP-40 thru BP-45).

• Beech Super King Air B200C Maintenance Manual Supplement to Super King Air 200 Series Maintenance Manual P/N 101-590010-19A or Subsequent, Part Number 990-38816B, revised 15 Nov 08. Aircraft C-12R, (BW-1 and After).

C-12J aircraft will continue to use the current and subsequent revisions of the IML for the 1900C/D models and the following supplements.

o 92-31326B Maintenance Manual Supplement Model 1900C-1 (C-12J), UD-1 - UD-6 o 990-31368C Wiring Diagram Model 1900C-1 (C-12J), UD-1 - UD-6 o 1900C: Illustrated parts Catalog: 990-31366 or subsequent

The Beechcraft 300/B300 series aircraft will continue to use the current and subsequent revisions of the IML for the 300/B300 models.

Engine TBO & HSI intervals (Per Pratt & Whitney Service Bulletins)

The below listed changes to time are a result of coordination and concurrence from the OEM.

CURRENT TBO INTERVALS

Aircraft Engine Hours C-12/RC-12 PT6A-41 4000 Hours* C-12/RC-12 PT6A-41 4500 Hours** C-12/RC-12 PT6A-42 4000 Hours* C-12/RC-12 PT6A-42 4500 Hours** C-12/RC-12 PT6A-60A Per Pratt & Whitney Guidance C-12/RC-12 PT6A-65B 6000 Hours C-12/RC-12 PT6A-67 3500 Hours* C-12/RC-12 PT6A-67 4000 Hours** C-12/RC-12 PT6A-67D 6000 Hours

Current HSI Intervals Aircraft Engine Hours

C-12 /RC-12 PT6A-41 1500 3000

C-12 PT6A-42 1500 3000

C-12 J PT6A-65B 2000 4000

C-12 J PT6A-67D 2000 4000

RC-12 PT6A-67* 1750

RC-12 PT6A-67** 1500 3000

C-12S PT6A-60 Per Pratt & Whitney Guidance

* Engines overhauls prior to 1 Oct 05 ** Engines overhauled after 1 Oct 05

C-12 and RC-12 Special Notifications Nose Landing Gear Drag Brace o Per Beechcraft Letter dated 17 OCT 12 the pivot pin bolts are to be installed with the head up o Ensure bolts are installed properly during Inspection and maintenance action Main Landing Gear Actuator o Per Aviation Safety Action Message 01, Install actuator assembly with a nut, either Beechcraft part number 115-810029-23 or 115-810029-24, or an equivalent Federal Aviation Administration (FAA) Parts Manufacturer Approval (PMA) Part Installed.

Main Landing Gear down Lock Pin and Hook o It is possible for the Main Landing Gear Drag Leg Pin to turn, which could prevent the gear from locking into place.

o During Inspection and Maintenance action ensure pin has not rotated

Propeller Governor for PT6A - 41 & 42 o Reference Woodward Service Bulletin Propeller – Turboprop Governor Assembly –

Replacement of Beta Valve Packing and Introduction of New Assembly part Numbers o Comply with Pratt & Whitney Service Bulletin No. 3435

C-12 Structural Inspections (Supersedes IML Requirements) o BW (ARMS) SIRM Supplement 101-510010-529 o H model (GR-14 thru GR-019) SIRM Supplement 101-590010-527

C-12 Landing Gear (Hydraulic and Mechanical) TBO o Seven (7) years or 6000 cycles whichever occurs first - Perform overhaul, includes:

Oleo Strut Assembly – includes shock absorber and axle Drag Brace Retract Actuator (mechanical gear)

C-12 o Every 100 hours – Corrosion Inspection Inspection will be completed at the above interval IAW the latest revision of the IML

Super King Air Series 200 Manual 101-590010-19 and Subsequent Revisions.

Continuous Corrosion Control Inspection 05-29-00-201.

C-12J o Every 50 hours – Routine (Corrosion) Inspection Inspection will be completed at the above interval IAW the latest revision of the IML

1900C Manual 114-590021-7, Routine Inspection 05-20-01-001. And, IML 1900D Manual 129-590000-15, Routine Inspection 05-20-01-201, and any Subsequent Revisions.

C-12/C-12J o Preflight/Daily

To be performed in accordance with check list provided in this document. The check list was developed to establish an acceptable and uniform Daily Inspection Guideline to meet qualitative expectations for all C-12/C-12J/RC-12 aircraft. To be performed at the end of each flight day, or prior to first flight of the day, or every three (3) days, if the aircraft is not flown or if the aircraft has been inspected. Per the DA PAM 738- 751 an entry in the 2408-13 will annotate the completion of the PMD/preflight.

Flight Data Recorder (FDR) o Operational check FDR & underwater beacon IAW OEM continued airworthiness instructions. Comply with Acoustic Beacon Battery replacement per OEM requirements.

Standby (magnetic) Compass Swing o Maintain per OEM maintenance program, FAA AC 43.13-1B, Chapter 12-37 and Army TM 1-1500-204-23-4. Compensation frequency as required per previous references.

C-12 o Lower Fuselage Pod (If Installed) Interval and inspection requirements listed in tables of this document

GR series aircraft

Inspections every 500 hours o Blower motor (Forward wide band antenna data link Radome anti-ice system) – Inspect for condition o Regulator valve (Forward wide band antenna data link Radome anti-ice system) – Inspect o Temperature sensor (Forward wide band antenna data link Radome anti-ice system) – Inspect for condition o Butterfly valve (Forward wide band antenna data link Radome anti-ice system) – Inspect o Air temperature controller (Forward wide band antenna data link Radome anti-ice system)

– Inspect for condition

Inspect per Battery OEM Recommendation o Battery (PME – Inertial Navigation System) – Check battery servicing, check connection for corrosion and arcing, check battery box for signs of leakage and corrosion.

RC-12 Structural Inspections (Supersedes IML Requirements) o FE series:

• SIRM Supplement 101-590010-509

• Pilot’s Operating Handbook and manufacturer approved Airplane Flight manual

Supplement part number 990-31320-1

• Pilot’s Operating Handbook and manufacturer approved Airplane Flight manual

Supplement part number 990-30440-1

• Pilot’s Operating Handbook and manufacturer approved Airplane Flight manual

Supplement part number 990-30894-1

• Pilot’s Operating Handbook and manufacturer approved Airplane Flight manual

Supplement part number 990-3224-1

RC-12 Landing Gear (Hydraulic and Mechanical) TBO o Seven (7) years or 6000 cycles whichever occurs first - Perform overhaul, includes:

Oleo Strut Assembly – includes shock absorber and axle Drag Brace Retract Actuator (mechanical gear)

RC-12 Radome De-ice Blower TBO o Overhaul at 1000 hours

Dipole Antennas o Every 12 months REMOVE the mount from the wing and inspect the interior of the mount and nut plates for security, cracking and general condition.

RC-12

o Every 100 hours – Corrosion Inspection Inspection will be completed at the above interval IAW the latest revision of the IML

Super King Air Series 200 Manual 101-590010-19 and Subsequent Revisions.

Continuous Corrosion Control Inspection 05-29-00-201.

o Preflight/Daily To be performed in accordance with check list provided in this document. The check list was developed to establish an acceptable and uniform Daily Inspection Guideline to meet qualitative expectations for all C-12/C-12J/RC-12 aircraft. To be performed at the end of each flight day, or prior to first flight of the day, or every three (3) days, if the aircraft is not flown or if the aircraft has been inspected. Per the DA PAM 738- 751 an entry in the 2408-13 will annotate the completion of the PMD/preflight.

Flight Data Recorder (FDR) o Operational check FDR & underwater beacon IAW OEM continued airworthiness instructions. Comply with Acoustic Beacon Battery replacement per OEM requirements.

Standby (magnetic) Compass Swing o Maintain per OEM maintenance program, FAA AC 43.13-1B, Chapter 12-37 and Army TM 1-1500-204-23-4. Compensation frequency as required per previous references.

o Interval and type of inspection for Army unique items are contained in tables of this document o Wing Pod Inspection (If Installed)

Inspections every 500 hours o Blower motor (Forward wide band antenna data link Radome anti-ice system) – Inspect o Regulator valve (Forward wide band antenna data link Radome anti-ice system) – Inspect o Temperature sensor (Forward wide band antenna data link Radome anti-ice system) –

Inspect for condition o Butterfly valve (Forward wide band antenna data link Radome anti-ice system) – Inspect o Air temperature controller (Forward wide band antenna data link Radome anti-ice system)

– Inspect for condition

Inspect per Battery OEM Recommendation o Battery (PME – Inertial Navigation System) – Check battery servicing, check connection for corrosion and arcing, check battery box for signs of leakage and corrosion.

Additions when complying with IML Phase 1 Aircraft Tech Inspector

Aircraft Exterior (to include ALL installed Army unique items GR-1 thru GR-19 i.e. pods, Radome, covers & fairings) - Visual Inspection for FE-1 thru FE-36 General Condition and Serviceability. _________ _________

WING PODS - Visual Inspection for General Condition and Serviceability. If installed _________ _________ POD DEICE BOOTS - Inspect for punctures and proper sealing around boots. If installed _________ _________

ANTENNA DEICE BOOTS – Inspect boots for cuts, abrasion, sealant and proper operation. If installed _________ _________

ANTENNA DEICE DISTRIBUTION VALVE - General condition, security and operational check. If installed _________ _________

DIPOLE ANTENNAS - Inspect antennas and mounts for security of attachment, inspect deice boots for punctures and proper edge sealing. Inspect the micro-switch mount for security.

Check for excessive play in the antenna support bushings. If installed _________ _________

DIPOLE ANTENNA ACTUATOR - Check for security and general condition. If installed _________ _________

STABILON DEICE BOOTS - Inspect for proper sealing around boots and for blistering. Inspect for exposed heating element. If installed _________ _________

Fire Detection Control Module - General Condition & Security FE-1 and after _________ _________

M-130 or AAR-57 ICMD dispenser control panel and electronic module - Inspect connector for bent or broke pin.

Inspect connector for corrosion or damage. Perform a visual examination for structural cracks, breaks, distortion, and deterioration of the dust boots, damaged threads, and evidence of overheating. Check for evidence of corrosion of the terminals, terminal lugs, and screws. If installed _________ _________

MISSION INVERTERS - Check for security of installation. GR-1 thru GR-19 Inspect for chafing, damage, cleanliness/dust build-up, proper FE-1 thru FE-36 routing of wire bundles and security of attachment.

Check for proper operation. _________ _________

Flight Data Recorder (FDR) - Inspect mount for security of installation. Accelerometer, Impact Switch, Sensors & underwater beacon – inspect for general condition and security.

Check Acoustic Beacon Battery manufacture date. If installed _________ _________

Check that all In-Flight Worksheet discrepancies are cleared or GR-1 thru GR-19 transcribed per service instructions (Customer) and FARs FE-1 thru FE-36 where applicable. _________ _________

Make appropriate logbook entries indicating completion of the Supplemental Inspection.

Signature ______________________________ Date________________

Additions when complying with IML Phase 2 Aircraft Tech Inspector

ANTENNA DEICE BOOTS – Inspect boots for cuts, abrasion, sealant and proper operation If installed ________ _________

M-130 or AAR-57 ICMD dispenser control panel and electronic module - Inspect connector for bent or broke pin. Inspect connector for corrosion or damage. Perform a visual examination for structural cracks, breaks, distortion, and deterioration of the dust boots, damaged threads, and evidence of overheating.

Check for evidence of corrosion of the terminals, terminal lugs, and screws. If installed ________ _________

PROPELLER MODULAR BRUSH ASSEMBLY – Inspect GR-1 thru GR-19 for wear and condition FE-1 thru FE-36 ________ _________

BLEED AIR PRE-COOLER - Check for security, Check for condition of seals and indication of chaffing, replace seals if chaffing is found, Check light in annunciator panel for proper operation. FE-1 and after ________ _________

MISSION INVERTERS - Check for proper operation. GR-1 thru GR-19 FE-1 thru FE-36 ________ _________ Check that all In-Flight Worksheet discrepancies are cleared or transcribed per service instructions (Customer) and FARs Where applicable ________ _________

Make appropriate logbook entries indicating completion of the Supplemental Inspection.

Additions when complying with IML Phase 3 Aircraft Tech Inspector

Aircraft Exterior (to include ALL installed Army unique items i.e. pods, Radome, covers & fairings) - Visual Inspection for GR-1 thru GR-19 General Condition and Serviceability FE-1 thru FE-36 ________ ________

WING PODS - Visual Inspection for General Condition and Serviceability If installed ________ ________

POD DEICE BOOTS - Inspect for punctures and proper sealing around boots If installed ________ ________

ANTENNA DEICE BOOTS – Inspect boots for cuts, abrasion, sealant and proper operation If installed ________ ________

ANTENNA DEICE DISTRIBUTION VALVE - General condition, security and operational check If installed ________ ________

DIPOLE ANTENNA ACTUATOR – Inspect for security and general condition If installed ________ ________

STABILON DEICE BOOTS (If Equipped) - Inspect for proper sealing around boots and for blistering. Inspect for exposed heating element. If installed ________ ________

M-130 or AAR-57 ICMD dispenser control panel and electronic module - Inspect connector for bent or broke pin. Inspect connector for corrosion or damage. Perform a visual examination for structural cracks, breaks, distortion, and deterioration of the dust boots, damaged threads, and evidence of overheating. Check for evidence of corrosion of the terminals, terminal lugs, and screws. If installed ________ ________

MISSION INVERTERS - Check for proper operation. GR-1 thru GR-19 FE-1 thru FE-36 ________ ________

AIR DUCT SENSE ELEMENT – Inspect for security GR-1 thru GR-19 and general condition FE-1 thru FE-36 ________ ________

WAVEGUIDE PRESSURIZATION DESICCANT

CANISTERS - Check color of desiccant, if pink replace the GR-1 thru GR-19 dehydrator unit. FE-1 thru FE-36 ________ ________

WAVEGUIDE PRESSURIZATION FILTER/SEPARATOR GR-1 thru GR-19 ELEMENT – Clean the filter, louver, and bowl with warm FE-1 thru FE-36 soapy water and blow dry, filtered compressed air. Inspect the performed packing’s and gasket for nicks or cracks replace if damaged. Inspect the automatic drain for free movement inside the collector. ________ ________

WAVEGUIDE PRESSURIZATION REGULATOR – GR-1 thru GR-19 Inspect for condition FE-1 thru FE-36 ________ ________

WAVEGUIDE PRESSURIZATION GAGE ASSEMBLY- GR-1 thru GR-19 Inspect for condition FE-1 thru FE-36 ________ ________

WAVEGUIDE PRESSURIZATION DEHYDRATION GR-1 thru GR-19 UNIT - Inspect for condition FE-1 thru FE-36 ________ ________

Additions when complying with IML Phase 3 Aircraft Tech Inspector

Flight Data Recorder (FDR) - Inspect mount for security of installation. Accelerometer, Impact Switch, Sensors & underwater beacon – inspect for general condition and security.

Check Acoustic Beacon Battery manufacture date. If installed ________ ________

Check that all In-Flight Worksheet discrepancies are cleared where applicable ________ ________

Additions when complying with IML Phase 4 Aircraft Tech Inspector

ANTENNA DEICE BOOTS – Inspect boots for cuts, abrasion, sealant and proper operation If installed ________ ________

M-130 or AAR-57 ICMD dispenser control panel and electronic module - Inspect connector for bent or broke pin. Inspect connector for corrosion or damage. Perform a visual examination for structural cracks, breaks, distortion, and deterioration of the dust boots, damaged threads, and evidence of overheating. Check for evidence of corrosion of the terminals, terminal lugs, and screws. If installed ________ ________

PROPELLER MODULAR BRUSH ASSEMBLY – Inspect for GR-1 thru GR-19 wear and condition FE-1 thru FE-36 ________ ________

BLEED AIR PRE-COOLER - Check for security, Check for condition of seals, replace seals as required, check light in annunciator panel for proper operation. FE-1 and after ________ ________

MISSION INVERTERS - Check for proper operation. GR-1 thru GR-19

FE-1 thru FE-36 ________ ________

Check that all In-Flight Worksheet discrepancies are cleared where applicable ________ ________

C-12 – ARMS Modification

The aircraft maintenance manual shall be supplemented with the maintenance manual supplement; Commuter Air Technology, Maintenance Manual Supplement for Beechcraft Models 200/B200 Equipped with 60 Cubic Foot Cargo Pod, 5 January 1989.

A daily visual inspection shall be made of the cargo pod installation to ensure that no progressive structural deterioration is occurring.

Inspect non-Original Equipment Manufacturer (OEM) penetrations, modifications and fastener holes on all ARMS modifications for cracks and/or missing rivets using a detailed visual Nondestructive Inspection (NDI) method at the intervals defined in Table. Modifications are described by Fuselage Station (FS) and stringer (STGR) locations unless located on the cargo pod.

C-12R Inspection for ARMS related Modifications

Detailed Visual = 1OX: magnification with light.

Signature Lead/Inspector __________________________ Date________________

Item Location Interval

(More Frequent Of Landings Or Flight

Hours Method Tech Inspector

A Iridium Antenna

FS 246.00 - 255.88

STGR 1LH - BL.O

Detailed

Visual

B SATCOM Antenna #1

FS 176.25- 187.388

STGR 1LH - 2LH

C SATCOM Antenna #2

FS 285.19 - 298.56

STGR 1 LH - 2LH

D AMT-50 Antenna FS 207.12 -226.25

STGR 1 RH - 3RH

E Radar Altimeter Closeout

FS 207.00 -246.00

Near STGR 16

F Lower TCAS Closeout

FS 143.00-158.00

Near STGR 16

G Lower ADF Closeout

FS 207.00

STGR 13LH -14LH

H DRT Closeout

FS 298.56 -305.25

STGR 15LH- 16LH

I Cargo Pod Attachments To Fuselage

FS 134.00 - 316.00 1200

J Ventral Surface Feed- Through Penetrations

FS 134.00 - 316.00 1200

K Forward ASE Installation

Cargo Pod Near FS

L Aft ASE Installation

FS 368.75 - 389.75

STGR 7 - 9

M REA Antenna (BW-008

& BW-017)

FS 94.00 -193.00 1200

N REA Antenna (BW-004) FS 305.00 -337.00 800

C-12/RC-12 SERIES AIRCRAFT

DAILY INSPECTION CHECK-SHEET

AIRFRAME

1. Check fuselage, empennage, wings, and cowlings for security and evidence of damage.

2. Check all control surfaces for security and visual damage.

3. Check inspection panels for emplacement and security.

4. Check landing gear wheel wells and brakes for leaks, wear, and security of components and general condition.

5. Check landing gear struts and actuators for attachment, leaks and evidence of damage.

6. Check landing gear wheels, tires and steering mechanisms for security of components and general condition.

7. Check landing gear hydraulic reservoir fluid level.(If installed)

8. Check cockpit lighting and annunciator lights for operation.

9. Check O2 masks for general condition.

10. Check navigation lights, beacons, strobes, recognition lights, landing lights, interior/exterior emergency lights and ice lights for operation and general Condition.

11. Check Pitot, fuel vent, and stall warning heated elements for obstructions, operation and general condition.

12. Check all flight controls and trim tabs for freedom of movement.

13. Check cockpit, cabin, cargo area and toilet for cleanliness, servicing and general condition.

14. Check antennas, strakes, tailets, and stabilons for security/condition. (If installed)

15. Check M-130 or AAR-57 ICMD for security and visual damage. (If installed)

16. Check supplemental oxygen system for servicing

17. Check wing pods for security and condition. (If installed)

18. Check lower fuselage pod for security and condition. (If installed)

19. Check fuel system for water or contaminants.

20. Check hand operated cockpit and cabin fire extinguishers for condition and security.

21. Check engine fire extinguishers for condition and security. (If installed)

PROPELLERS

1. Check propeller spinners for condition and attachment.

2. Check propellers for nicks and general condition.

3. Check propeller de-ice brush blocks and slip ring for general condition through gap in spinner and cowling.

POWERPLANT

1. Check engine through front cowl, cowling doors, for fuel, oil, exhaust leaks and general condition.

2. Check engine oil coolers for obstructions, leakage and general condition.

3. Check engine controls for freedom of operation.

4. Check engine cowling inspection plates for security and general condition

5. Check engine exhaust stacks for cracks and condition

6. Check engine oil tanks are serviced to proper level.

7. Check engine cowling intake area for foreign objects and general condition

LUBRICATION/SERVICING

1. Lubricate and service as required.

GENERAL

1. Check TLMC/TBO listing for items required and update as needed. Verify that logbooks and records reflect current TLMC/TBO data.

2. Make appropriate logbook entries indicating completion of Preventative Maintenance Daily Inspection (PMD).

3. Check that all In-Flight Worksheet discrepancies are cleared or transcribed per service instructions (Customer) and FARs where applicable.

4. Check for foreign objects after completion of maintenance.

Aircraft Interior Maintenance

The Contractor shall furnish the personnel and material necessary to accomplish interior maintenance to the standards specified in this Appendix.

General

The aircraft interior shall be maintained in a clean and serviceable condition. After each flight, all ashtrays and trash receptacles shall be emptied and carpets cleaned as required. Windows shall also be cleaned. Oxygen masks will be inspected and properly stowed.

J-1.1 Materials

All materials must meet the specifications in the following paragraphs:

Burn Testing: All soft and hard goods, other than metals, used in refurbishment or modification must be shown to comply with FAR 25.853 and FAA AC 43-16, February 1994 by burn test only by an FAA approved facility. Certificates from the manufacturer stating "...material manufactured to meet FAR 25.853..." or similar comments are unacceptable as evidence of compliance. Materials include fabrics, carpets, seat belts, curtains, thermoplastic, high pressure laminates, paneling, adhesives, insulation, etc.

Test results must be provided which show the type of test and evidence of compliance; i.e., vertical, burn distances, times, etc. The soft good materials must be identified as to composition. The use of acrylic or modacrylic trim is not allowed, and natural fibers are recommended.

Flame-proofing Treatment: If flame-proofing treatment is required for compliance, then the treatment must be identified by name and life limit (if any). If the life limit is by reason of cleaning process, then the cleaning process must be identified and the burn samples processed the limiting number of cycles prior to the burn test and so noted on the report. No flame-proofing treatment which causes or accelerates corrosion shall be used nor any flame-proofing treatment which is applied by application after assembly or installation.

J-1.2 Interior Replacement Criteria

The Contractor shall replace at their expense, those interior items that are no longer serviceable due to fair wear and tear. Those items include carpeting, seat covers, cushions, head rest covers, arm covers, headliner material, wood grain veneer on toilet, cabinets and partitions, toilet cushion cover, privacy curtain, cargo webbing, sound proofing (RC-12 aircraft), window frame cover, trim panels and cabin side wall head vent covers. The Contractor is fully responsible for repairs and replacement as required for those aircraft equipped with standard interior (Gray Leather).

J-2.0 Interior Appearance Standard

Blind fasteners shall be used whenever practical. Consideration shall be given to both appearance and maintenance requirements. In areas where exposed fasteners must be used, only OEM aircraft quality hardware (AN/MS/NAS) shall be used.

All glue remnants shall be removed from the interior portions visible to the naked eye. Glue application methods chosen shall provide a smooth finished product.

When attaching materials, leather, plastic, etc. sufficient overlap shall be left on the back sides of panels to prevent loosening of the front fabric surfaces or edges.

Window shades and escape hatches shall be fully operational. The Contractor shall ensure that these areas are properly tested.

J-2.2 Airstair and Cargo Doors

Airstair and cargo doors shall be clean in appearance without significant scuffs, stains, mars or scratches. Minor scratches and discoloration shall not be cause for replacement. Door treads shall be replaced when damaged or worn. Minor rips, tears, gouges shall be repaired. Corroded hardware shall be replaced.

J-2.4 Bulkheads

Bulkheads shall be clean and present a suitable appearance. Bulkheads shall be free of chips, dents, mars, gouges, stains and scratches. Chips, dents and scratches in excess of one quarter (1/4) inch shall be patched and filled, and refinished as required. When several patches are evident or unsightly, the veneer shall be replaced. Partitions are treated in the same manner. Partitions and curtains shall be replaced if cleaning and/or repair does not restore their appearance to a condition that does not detract from aircraft appearance.

J-2.5 Headliners

The headliner shall be clean. Minor cracks, nicks, tears, or stains shall be repaired or cleaned. Damaged headliners which cannot be repaired to acceptable standards in appearance shall be replaced.

Emergency oxygen access shall not be inhibited by the material attached to the compartment covers.

J-2.6 Side Panels

Plastic, leather, synthetic, and carpeting material shall be clean in appearance. Minor stains, cuts, tears, and cracks shall be repaired and cleaned. Damaged side panels which cannot be repaired shall be replaced. All material shall be firmly attached and shall present a smooth, wrinkle-free and sag- free appearance.

J-2.7 Baggage Compartment

The baggage compartment shall be clean in appearance. Discrepancies are treated in the same manner as the headliner, carpet and side panels.

J-2.8 Carpets

The carpeting shall be clean and free from stains, rips, and tears. Carpets shall be repaired or replaced when edges become frayed. Stains shall be removed or the carpet shall be replaced. Minor cuts and tears of less than one inch shall not be cause for replacement. Cleaning - Comprehensively clean every 180 days, to include treating with Scotchguard or similar approved stain repellent. Do not degrade flame proofing. The spar cover shall be skid-resistant and shall be clean in appearance. Tears exceeding 1/2 x 1 inch which cannot be repaired shall be replaced. All floor carpet shall be secured by means of Velcro fasteners. A throw rug made of carpeting shall be provided for the entrance way. All carpet shall be of the same quality and color. The carpet edges shall be surged, sealed or bound. Carpet will be fitted to aircraft to ensure all edges fit properly so as not to have any floorboards showing.

J-2.9 Seating

The seating shall be clean in appearance. Leather cleaning and treatment is required each 180 days.

Seat Covers: Tears and cuts shall be repaired immediately upon discovery, using a like material and color. Stains shall be removed when possible. Seat covers shall be replaced when they become worn or damaged beyond repair, stained to the point they can no longer be cleaned, or when they detract from aircraft appearance. Comprehensively clean every 90 days to include treating with leather conditioner or stain guard product depending on the type of interior. (Leather or cloth). Do not degrade flame proofing.

Cushions: Tears, cuts, wear, and stains shall be treated in the same manner as the seat covers.

Cushions shall be replaced if distorted, have degraded to the point of contour causing passenger or pilot discomfort or deteriorated to the point that they detract from appearance and are no longer serviceable.

Head Rest and Arm Rest Covers: These items shall be maintained to the same standards as seat covers.

Seat Frames; The seat frames will be painted or touched up to keep appearance up at each #2 and #4 Phase Inspection.

J-2.10 Glareshield

The glareshield shall be securely attached and clean. Damage and stains which cannot be repaired shall be cause for replacement. Areas around vent access will be re-glued when it becomes loose.

J-2.11 Trim

All trim shall be clean. Plastic trim shall be repaired and refinished when possible, or replaced when no longer able to repair or refinish and returned to service. Painted trim shall be refinished when minor repairs and the condition of the trim deteriorates in appearance. Metal trim which has corroded and cannot be restored shall be replaced. Wood trim shall be clean and free of scratches, mars, rubs, gouges, dents etc. Dents, chips and scratches in wood trim exceeding one quarter inch (1/4) shall be filled and refinished to present a suitable appearance. Metal trim covered by adhesive backed vinyl shall be smooth tight and blister free. Minor defects such as cracks, scratches or dents of less than one quarter inch (1/4) shall be acceptable. Particular attention to the trim conditions shall be given to the passenger cabin area. All trim shall present a smooth, clean appearance.

J-2.12 Vinyl Runners

Tears of less than 1/2 inch shall be repaired. Tears of greater than 1/2 inch or a worn appearance warrant replacement.

J-2.13 Cabinet Knobs/Pulls

Repair as required and when damaged. Replace when repairs can no longer be made or when they detract from the appearance of the item.

J-2.14 Window Shades

Repair if torn, soiled, marred or marked. Must match existing color and texture. Replace when no longer serviceable due to stains, tears, discoloration or inability to operate as designed, or if repairs detract from appearance.

J-2-15 Tables

Repairs shall be made to any component that is damaged or marred. This includes replacement of pulls, knobs, tracks, or panels. Replace if repairs detract from appearance.

Aircraft Cleaning Checklist

• The following cleaning requirements are in additional to the OEM requirements.

• When environmental conditions warrant more frequent washing and cleaning may be required and requested by the TW tech Rep.

• Approved cleaners and preservatives will conform to OEM, EPA, and OSHA Standards and MIL-

C-85570 (latest) and not contain alcohol or ammonia.

Daily

• The Contractor shall ensure that the aircraft and its systems are clean and ready for planned missions. Upon completion of each mission day, the Contractor shall perform the following actions:

o Remove all debris from the aircraft cockpit. Collect and dispose of all loose paper throughout the aircraft.

o Brush all loose dust from the center pedestal, the instrument panel operator’s console, and mission equipment with a soft paint style brush.

o Clean aircraft instruments as specified by the OEM manual.

o Clean windshields of all water spots, water trails, and debris, IAW OEM maintenance manuals. Cleaners with alcohol or ammonia will not be used on any aircraft windows.

o Wipe down and clean aircraft landing gear and landing gear bay area.. Ensure struts are wiped with MIL-H-5606 hydraulic fluid.

o Remove all oil traces from the aircraft engine compartment using a manufacturer’s approved solvent or cleaner that is compatible with plastics, rubber material such as baffles, seals and rubber engine mounts. If lubrication is removed from engine and propeller control linkages it shall be re-lubricated with OEM lubrication products.

o Remove exhaust trails from the engine cowling and surfaces of the aircraft using a manufacturer’s approved cleaner or a substitute that complies with MIL-C-85570 (latest) o Empty and clean aircraft galley facilities including emptying and cleaning coffee and water dispensers if aircraft so equipped.

o Clean, service, and restock aircraft latrines o Vacuum aircraft carpeting and spot clean on a day to day basis as necessary.

o Ensure the oxygen masks are cleaned and stowed.

14 Calendar Days

• The Contractor shall wash the aircraft with approved cleaners complying with MIL-C- 85570B every 14 calendar days.

Following Aircraft Wash and Rinse

• All exterior unpainted metal leading edges shall be polished after each aircraft wash and rinse.

Completion of 100 hour Inspection

• At the completion of the 100 hour inspection the contractor shall clean and condition all leather surfaces and treat and polish all wooden amenities as installed with approved cleaners and preservatives will conform to EPA and OSHA Standards and MIL-C-85570 and not contain alcohol or ammonia

Six (6) Month Intervals

• Contractor shall polish aircraft a minimum of once every six (6) months.

NOTE

IR gray painted aircraft are excluded from polishing, but must be washed thoroughly to remove oil and soot stains. Scotch-brite pads shall not be used as the remove layers of paint.

Cleaning agents: Skyrite and Simple Green will not be allowed on government aircraft. All cleaners will conform to EPA and OSHA Standards and MIL-C-85570 and not contain alcohol or ammonia.

C-12/RC-12 PRESERVATION DURING HEAVY MAINTENANCE & MODIFICATION

THE REQUIREMENTS IN THIS DOCUMENT ARE TO BE USED FOR PRESERVATION AND DE-

PRESERVATION DURING HEAVY MAINTENANCE & MODIFICATION.

FOLLOW THE STEPS BELOW, NOTES AND CAUTIONS FROM THE CURRENT AND FUTURE

REVISIONS OF THE IML BEECHCRAFT MAINTENANCE MANUAL CHAPTER 10-10-00-201.

AIRPLANE/ENGINE

0 to 7 Days

♦ The engines may be left in an inactive state, with no preservation protection requirements, provided: the engine is sheltered; the humidity is not excessively high; the engine is not subject to extreme temperature changes, which would produce condensation.

Over 7 days

♦ Static ground the airplane securely and effectively.

♦ Disconnect and remove the aircraft battery, then place in a suitable storage area.

8 to 30 Days

♦ Engines that are inactive up to 28 days require no preservation provided all engines openings are sealed off and the relative humidity in the engine is maintained at less than 40%. Humidity control is maintained by placing desiccant bags in the engine exhaust ducts.

Over 30 days

♦ Install covers over pitot head and cover static ports with barrier material secured with tape. Cover windows and windshield with either: (1) strippable coating, (2) alkali removable coating, or (3) barrier material secured with tape.

Over 90 Days

♦ Preserve fuel system as noted in steps 1 through 6 of IML Chapter 10-10-03-201, item D:

REMOVE FROM PRESERVATION

Reverse steps required from above I.A.W. IML Chapter 10-10-00-201.