ATTACHMENT_41_-_PWS_Encl_4_-_T-44C_Corrosion_Control_Plan.pdf

U.S. NAVY T-44C

PEGASUS

NAVAIR (PMA 273) T-44C

CORROSION CONTROL PLAN

January 1, 2013

ATTACHMENT 41

PWS Enclosure 4 T-44C Corrosion Control Plan N00019-14-R-0018

PAGE EFFECTIVITY LISTING

NAVAIR (PMA 273)

Summary:

• The original issue of the Corrosion Control Plan, which was NAVAIR document, was dated September 1989.

• The issue date of Change Two is unknown.

• Change Three was issued 27 September 1994.

• Change Four was issued 1 January 2000 as a PMA 207 document.

• Change Five was issued 22 January 2001.

• Change Six was issued 2 January 2003.

• Change Seven is now a PMA 273 document issued 1 March 2005.

• Change Eight is the current version, and is dated 1 January 2013.

Page(s) Change Number Date Comments

Cover 8 1/1/2013 Changes Not Bar Marked i 8 1/1/2013 Changes Not Bar Marked 1 8 1/1/2013 Changes Not Bar Marked 2 8 1/1/2013 Changes Not Bar Marked 3 8 1/1/2013 Changes Not Bar Marked 4 8 1/1/2013 Changes Not Bar Marked 5 8 1/1/2013 Changes Not Bar Marked 6 8 1/1/2013 Changes Not Bar Marked 7 8 1/1/2013 Changes Not Bar Marked 8 8 1/1/2013 Changes Not Bar Marked 9 8 1/1/2013 Changes Not Bar Marked 10 8 1/1/2013 Changes Not Bar Marked 11 8 1/1/2013 Changes Not Bar Marked 12 8 1/1/2013 Changes Not Bar Marked 13 8 1/1/2013 Changes Not Bar Marked 14 8 1/1/2013 Changes Not Bar Marked 15 8 1/1/2013 Changes Not Bar Marked 16 8 1/1/2013 Changes Not Bar Marked

Interim Change Notice (ICN) Log

ICN Number Page/Section/Item Date Comments/Information

Interim Change Notice information and entry requirements:

Interim Change Notices (ICNs) can be either issued in hard copy, navy message format or via E-Mail.

Each ICN will have a unique serial number assigned for tracking purposes.

When an ICN is received/issued holders of the Scheduled Inspection Requirements Guide (SIRG) will be required to enter the data in the above log in the appropriate section of the manual that it applies to; i.e., the NAVAIR (PMA-273) 01-50-T44A-600-6, -600-6-4.1, –600-6-6-4.2 or the Corrosion Control Manual.

NOTE: Changes to the Daily/Turnaround and the Seven Day Inspection MRCs will be annotated on Page ii of the applicable MRC package.

Entry information requirements in the above ICN Log are self-explanatory. All ICNs will be incorporated into the appropriate portion of the SIRG package when a formal change is to the document is issued.

Copies of ICNs shall be posted to the applicable document immediately behind the title/cover page and a notation shall be made in the appropriate/referenced area of the affected document to alert the user to the ICN that has modified or amended the requirements.

TECHNICAL INFORMATION REPORT, DISCREPANCY (TIRD)

CHANGE RECOMMENDATION

(TO BE FILLED IN BY ORIGINATOR)

REPORT DATE: __________________________________

FROM (Originator): ________________________________ ACTIVITY: ________________________________________

ADDRESS AND/OR E-MAIL OF ORIGINATOR:________________________________________________________________

SEND COMPLETED FORM TO:

NAVAIRSYSCOM

ATTENTION: PMA-273, T-34 OR T-44 APMSE

22581 SAUFLEY ROAD, BUILDING 3258

PATUXENT RIVER, MARYLAND 20670

NAME/P/N OF MANUAL CHANGE # CHANGE DATE PAGE/SECTION/PARAGRAPH

DEFICIENCY: ____________________________________________________________________________________________

RECOMMENDATION (Be Specific): __________________________________________________________________________

________________________________________________________________________ Check if continuation sheets or drawings attached.

IMPACT: _________________________________________________________________________________________________

REPORT BY: _____________________________________________

SIGNATURE:_____________________________________________ TITLE:________________________________________

TO BE FILLED IN BY PMA-273

FROM: __________________________________________________ DATE: ________________________________________

TO: _____________________________________________________

REFERENCE:_______________________________________________________________________________________________

INSTRUCTIONS FOR COMPLETING THE TIRD

1. REPORT DATE: This identifies the year, month, and day that the report was prepared and consists of six digits, e.g., 050115. The first two digits indicate the year, the second two digits indicate the month, and the remaining two digits specify the day.

2. FROM: The reporting activity originating change request. Address and/or e-mail address should be provided.

3. ACTIVITY: The activity reporting the discrepancy, e.g., Contractor, NAS Corpus Christi

4. TECHNICAL MANUAL: Give the complete number assigned to the manual being reported as deficient.

5. CHANGE NUMBER: This appears on the area/page on which the deficiency is located.

6. CHANGE DATE: This appears on the area/page on which the deficiency is located.

7. SECTION/PAGE: Enter the number of the pages of the technical manual on which the deficiency is located.

8. PARAGRAPH: Enter the specific number in which the deficiency is located.

9. DEFICIENCY: Be very specific. Provide complete information regarding discrepancy, including drawings, schematics, sketches, and references. If necessary, attach copies of any reference data.

10. RECOMMENDATION: Be very specific. Provide complete information regarding the corrective action required, including drawings, schematics, sketches, and references. If necessary, attach additional pages.

11. IMPACT: Enter concise statement of the impact of this discrepancy on work load/operational readiness.

12. REPORTED BY: Name and position of person that prepared the TIRD.

TABLE OF CONTENTS

SECTION I

GENERAL REQUIREMENTS

1.1 PURPOSE……………………………………………………………………………. 2

1.2 CORROSION PREVENTION PHILOSOPHY……………………………………… 2

1.3 CORROSION PREVENTION AND CONTROL PROGRAM

1.4 CONFLICTS…………………………………………………………………………. 2

1.5 REFERENCES………………………………………………………………………. 2

1.6 CHANGE RECOMMENDATIONS………………………………………………… 3

1.7 RESPONSIBILITY…………………………………………………………………... 3

1.8 MATERIAL………………………………………………………………………….. 3

1.9 DISTURBED SYSTEMS……………………………………………………………. 3

1.10 APPLICABILITY……………………………………………………………………. 3

1.11 TRAINING…………………………………………………………………………... 3

1.12 DOCUMENTATION………………………………………………………………... 4

SECTION II

DETAILED REQUIREMENTS

2.1 CORRECTIVE MAINTENANCE…………………………………………………... 5

2.2 PREVENTIVE MAINTENANCE…………………………………………………… 5

2.3 LUBRICATION……………………………………………………………………… 5

2.4 AIRCRAFT WASH………………………………………………………………….. 6

2.5 ENGINE WASH……………………………………………………………………... 8

2.6 56-DAY CORROSION INSPECTION……………………………………………… 9

SECTION III

EMERGENCY PROCEDURES

3.1 EMERGENCY PROCEDURES…………………………………………………….. 11

3.2 EMERGENCY RECLAMATION TEAM ORGANIZATION…………………….. 11

3.3 EMERGENCY RECLAMATION EQUIPMENT………………………………….. 11

3.4 EQUIPMENT REMOVAL PRIORITY LIST………………………………………. 12

3.5 DOCUMENTATION………………………………………………………………... 12

SECTION I

GENERAL REQUIREMENTS

1.1 PURPOSE:

1.1.1 This plan provides the minimum requirements and procedures to establish a comprehensive program for corrosion control by contractor maintenance on T44A aircraft.

1.1.2 NAVAIR 0l-lA-509, and recommendations of the Beech Aircraft Corporation are the guidelines for this plan.

1.2 CORROSION PREVENTION PHILOSOPHY:

1.2.1 The basic philosophy of this corrosion control plan consists of the following steps:

1.2.1.1 Emphasizing the concept of all hands responsibility for corrosion control.

1.2.1.2 Adequately training personnel in recognition of corrosion-inducing conditions, detection, identification, cleaning, preservation, treatment and lubrication.

1.2.1.3 Using approved materials, equipment, and technical publications.

1.2.1.4 Thoroughly cleaning, preserving, and lubricating at prescribed intervals.

1.2.1.5 Inspecting for corrosion on a scheduled basis.

1.2.1.6 Applying thorough knowledge of corrosion identification techniques.

1.2.1.7 Promptly treating corrosion after detection.

1.2.1.8 Keeping accurate records and ensuring reporting of material/design deficiencies.

1.3 CORROSION PREVENTION AND CONTROL PROGRAM:

1.3.1 The Contractor shall establish and maintain a corrosion prevention and control program, which incorporates requirements of this plan to detect, correct, and prevent corrosion.

1.4 CONFLICTS:

1.4.1 Use this plan in conjunction with corrosion control requirements established in T- 44A aircraft maintenance manuals. In the event a conflict arises, the material and procedures contained in this plan shall take precedence.

1.5 REFERENCES:

NAVAIR 01-lA-509 Aircraft Weapons Systems Cleaning and Corrosion Control for organizational and Intermediate Maintenance Levels

NAVAIR 15-01-500 Preservation of Naval Aircraft and Engines

BEECH Service Instruction Wing Front Spar - Inspection of Upper and No. 0514-035, Rev II Lower Spar Caps

BEECH 92-38879 T-44A Maintenance Manual

NAVAIR 01-50-T44A-600-6 T-44A Continuous Inspection Procedures Manual

Pratt & Whitney Canada 3021242 PT6A-34B Maintenance Manual

1.6 CHANGE RECOMMENDATIONS:

1.6.1 Submit recommendations for additions, deletions or changes to the requirements of this plan to Commander Naval Air Systems Command, PMA 273, Patuxent River, MD 20670 to the attention of the T-44A APMSE using a Technical Information Report, Discrepancy (TIRD).

1.6.2 PMA-273 shall prepare and issue revisions and changes to this plan.

1.7 RESPONSIBILITY:

1.7.1 The contractor shall monitor the material condition of the aircraft and recommend changes to this plan as necessary to maintain and improve the material integrity of the aircraft.

1.8 MATERIAL:

1.8.1 The Contractor shall use only materials approved in NAVAIR 0l-lA-509, T-44A and PT6A-34B Maintenance Manuals for cleaning and corrosion control requirements/guidance, and MED PR-58.

1.8.2 The Contractor shall dispose of materials in accordance with local instructions.

1.9 DISTURBED SYSTEMS:

1.9.1 The Contractor shall operationally check/test aircraft systems that are disturbed during the corrosion prevention and control process to ensure system integrity and to verify proper installation and operation.

1.10 APPLICABILITY:

1.10.1 All assigned aircraft not in a preserved status are subject to the provisions of this plan. Preserved aircraft are subject to preservation maintenance requirements of NAVAIR 15-01-500 and aircraft preservation/depreservation sections of the T-34C/T-44A Aircraft Statement of Work.

1.11 TRAINING:

1.11.1 Contractor personnel performing aircraft maintenance shall possess those skills sufficient to perform the minimum corrosion control requirements in NAVAIR 0l-lA-509, aircraft maintenance manuals, and this plan. The contractor shall establish and maintain:

1.11.1.1 An on-going training program, based on NAVAIR 0l-lA-509 and stressing corrosion theory and identification, preventive maintenance programs, and temporary preservation, to train all contractor personnel performing maintenance on aircraft in recognition, temporary arrestment, and reporting of corrosion.

1.11.1.2 A program to train all contractor personnel engaged in corrosion removal to include inspection, cleaning, removal, treatment, and protection methods as described in NAVAIR 0l-1A-509.

1.11.1.3 A training program for personnel to wash the exterior surfaces of T-44A aircraft, based on the frequency identified in table 2-1 and materials and procedures recommended in NAVAIR 0l-lA-509, T-44A aircraft. Training shall address (1) Preparation for wash, (2) Cleaning methods, (3) Post-cleaning lubrication and corrosion inspection requirements identified in NAVAIR 0l-lA-509.

1.11.1.4 A training program for personnel to wash/rinse the PT6A-34B engines.

This training shall include procedures and materials based on the latest revision of the T-44A aircraft and PT6A-34B engine maintenance manuals and this plan.

1.12 DOCUMENTATION:

1.12.1 A corrosion control record documenting corrosion discrepancies discovered during Post-Wash and 56 Day inspections shall be maintained for each aircraft. The corrosion control record shall accompany the aircraft to ACI.

1.12.2 In contractor format, the corrosion control record shall contain as a minimum:

(a) Complete description of defect including type designation (TABLE 1-1), size, severity designation (TABLE 1-2), and criticality (critical, major, minor).

(b) Accurate location of the defect.

TABLE 1-1 - TYPE DESIGNATION

CODE: DEFINITION:

A Direct surface attack B Galvanic or dissimilar corrosion C Pitting D Intergranular attack including exfoliation E Crevice attack or concentration cell corrosion F Fretting corrosion G Stress corrosion cracking H Corrosion fatigue I Filiform corrosion J Microbiological corrosion, as defined and illustrated in NAVAIR 0l-lA-509

TABLE 1-2 - SEVERITY DESIGNATION

CODE: DEFINITION:

1 Light corrosion removable by chemical cleaners and repairable by chemical treatment.

2 Light to moderate corrosion removable by manual application of mild abrasive compounds or soft grit blasting and repairable by chemical treatment.

3 Moderate to severe corrosion removable by mechanical methods and repairable by chemical treatment.

4 Severe corrosion removable by mechanical methods and repairable by Structural Repair Manual.

5 Severe corrosion not removable by any method and requires replacement of the affected part.

SECTION II

DETAILED REQUIREMENTS

2.1 CORRECTIVE MAINTENANCE:

2.1.1 The contractor shall perform immediate corrective maintenance, in accordance with NAVAIR 0l-lA-509, and PT6A-34B and T-44A maintenance manuals to remove all corrosive products and repair all corrosion damage discovered.

2.1.2 If operational commitments prevent immediate correction of corrosion, the Contractor shall perform temporary arrestment procedures in accordance with NAVAIR 01-lA-509. Corrective action shall in no case be later than the next scheduled corrosion control inspection.

2.2 PREVENTIVE MAINTENANCE:

2.2.1 The Contractor shall perform preventive maintenance requirements for corrosion control including aircraft and Engine cleaning, corrosion inspection, temporary corrosion arrestment, documentation, lubrication, and preservation in accordance with the requirements of this plan. The Contractor shall perform the corrosion preventive maintenance requirements stated in TABLE 2-1.

2.3 LUBRICATION:

2.3.1 The contractor shall lubricate the aircraft at the intervals specified by T-44A aircraft Scheduled Inspection Requirements Documents (Lubrication Charts and Tables), TABLE 2-1 and Figure 2-1 of this plan. These three references establish the current lubrication requirements and procedures.

NOTE: Lubrication charts and tables are also contained in the NAVAIR (PMA

273) 01-50-T44A-600-6-4.1 and 4.2 Detailed Inspection packages.

NOTE: In case of conflict the data contained in above references takes precedence over and supercedes the data contained in Section 12-00-00 of the T-44A

Maintenance Manual.

TABLE 2-1 - T-44A CORROSION PREVENTATIVE MAINTENANCE REQUIREMENTS

FREQUENCY REQUIREMENT

Daily Perform compressor desalination wash (compressor rinse) and turbine desalination wash (compressor turbine rinse). See Paragraph 2.5.2.

7 Day (1) Lubricate all airframe hinge points using VV-L-800 General Purpose Lubricating Oil of the:

(a) Avionics bay access door.

(b) Rudder trim tab.

(c) Elevator trim tab.

(d) Aileron trim tab.

(e) Cowling doors.

(f) Main cabin door.

(2) Clean/wipe down the exposed chrome area on the landing gear oleo struts with MIL-H-83282C Hydraulic Oil.

14 Day Wash aircraft.

56-Day Perform 56 Day Inspection.

100 Flight Hours Perform engine performance recovery/compressor turbine wash.

2.4 AIRCRAFT WASH: The Contractor shall:

2.4.1 Rinse each aircraft exterior (including wheel wells) thoroughly following each low-level tactical flight over water. The Navy will inform the Contractor of such flights.

2.4.2 Adhere to all safety requirements in NAVAIR 0l-lA-509, and T-44A aircraft maintenance manuals.

2.4.3 Wash each aircraft every 14 days (plus or minus three (3) days), using the following procedures:

2.4.4 Preparation for Cleaning. Prepare the aircraft for washing of the exterior as follows:

2.4.4.1 To protect against cleaning solution entrapment, lubricate the following points identified in Figures 2-1.1, 2-1.2 and 2-1.3 of this plan, using methods and materials specified:

NOTE: Lubrication charts and tables are also contained in the NAVAIR (PMA

273) 01-50-T44C-600-6-4.1 and 4.2 Detailed Inspection packages.

NOTE: Prior to lubricating any components or parts, remove all foreign matter from joints, fittings and bearing surfaces.

2.4.4.2 Lower Flaps to FULL DOWN position.

2.4.4.3 Engage parking brake and control lock.

2.4.4.4 Close doors and emergency openings.

2.4.4.5 Check moisture/condensation drain holes. Make sure that all drain holes are clear by inserting a probe such as a pipe cleaner. Refer to Figure 2-1 at the end of this plan for locations of the drains.

2.4.4.6 Ground aircraft.

2.4.4.7 In order to protect against water/cleaning solution intrusion, tape the following:

(a) Pitot Tubes.

(b) Static air sources.

CAUTION: Ensure that tape adhesive transfer does not foul the static vents.

Cover static vents with a properly sized disc of suitable material, and then apply masking tape.

(c) Condenser Air Intake and Exhaust.

(d) Intakes, Exhausts and Vents Identified in Figure 2-2.

(e) Engine Air Intakes.

CAUTION: Take care not to scratch surfaces. Wipe away from seal areas, not toward seals.

2.4.4.8 Wipe exposed chrome area of shock struts with MIL-H-46170 or specified operating fluid.

WARNING: Open all circuit breakers associated with battery power prior to application of cleaning compounds. Refer to T-44A aircraft maintenance manual.

2.4.5 Cleaning Method. The aircraft cleaning sequence is as follows:

(a) Wheel Wells and Landing Gear.

(b) Aircraft Exterior.

WARNING: When using cleaning compounds wear a faceshield or goggles, rubber gloves and coveralls.

2.4.5.1 Wheel Wells and Landing Gear Area. Apply MIL-C-85570, Type V, cleaning compound undiluted with spray or brush and allow 5 to 15 minute dwell. Brush if necessary, and rinse thoroughly with fresh water. Repeat rinsing with brush to remove cleaner residue.

2.4.5.2 Aircraft Exterior. The following procedures shall be used to clean the T-44A aircraft exterior. Utilizing the procedures described below, wash the aircraft starting with the underside center and work toward the nose, tail and wing tips. Wash the top of the aircraft starting top center and work toward the nose, tail and wing tips.

WARNING: Use care when washing the wings. Ensure that moisture and solvents are not allowed to remove or dilute the anticorrosive grease on the wing attach bolts.

(a) Mix approved cleaning compound using mixing directions in NAVAIR

0l-lA-509.

(b) Apply the mixture using foaming equipment or fiber brush.

(c) To prevent streaking, start at the lower surfaces, working upward and out. Scrub the surface with fiber brushes if necessary.

(d) Rinse away the loosened soil and cleaner with a stream of water. For rinsing, a rubber padded shutoff-spray nozzle is recommended.

2.4.6 Post-Clean. The post-cleaning procedures shall be carried out in the following order:

(a) Remove all covers and masking installed during preparation for cleaning.

(b) Check moisture/condensation drain holes. Clean all drain holes by inserting a probe such as a pipe cleaner. Assure that all areas, with or without drain holes, accumulating water have been drained. Refer to Figure 2-2 at the end of this plan for general location of moisture/ condensation drain holes.

(c) Inspect aircraft exterior, including wheel wells and landing gear, for corrosion and deterioration. Document corrosive products and damage.

(d) Perform the post-wash lubrication as follows:

(1) To protect against cleaning solution entrapment, lubricate the following points identified in Figures 2-1.1, 2-1.2 and 2-1.3 of this plan, using methods and materials specified:

NOTE: Lubrication charts and tables are also contained in the NAVAIR (PMA

273) 01-50-T44C-600-6-4.1 and 4.2 Detailed Inspection packages.

NOTE: Prior to lubricating any components or parts, remove all foreign matter from joints, fittings and bearing surfaces.

(2) Lubricate all external visible piano hinges.

2.5 ENGINE WASH:

NOTE: Since engine wash procedures in the Pratt & Whitney Canada Maintenance Manual are referred to throughout this section, the same terminology is used. To clarify: Only the performance recovery wash uses a wash compound. Both the compressor desalination wash and the turbine desalination wash are what are commonly called a “rinse.” Wash medium for both of the desalination washes is drinking quality water, which has to meet the minimum standards called out in the PWC maintenance manual.

2.5.1 The contractor shall adhere to recommendations in latest revision of the T-44A aircraft and PT6A-34B engine maintenance manuals and this plan, for performing engine Desalination and Performance Recovery washes. The following applies:

(a) Use a minimum of two (2) personnel for engine washing with one of the two qualified in powerplant turnup procedures.

(b) Wash the aircraft exterior after the engine wash whenever the two washes coincide. Otherwise, ensure the aircraft exterior is rinsed thoroughly after every engine wash to remove the engine wash deposits.

(c) As required in Table 2-1, perform a Compressor Turbine desalination wash, in accordance with Pratt & Whitney Canada Maintenance Manual, Chapter 71-00-00 (700 series pages) in conjunction with each Engine Performance Recovery Wash.

2.5.2 Perform engine compressor desalination wash and turbine desalination wash in accordance with the following guidelines:

(a) Both desalination washes (rinses) are to be performed after the last flight of the day on each engine using the "motoring" method described in the Pratt & Whitney Maintenance Manual, Chapter 71-00-00 (700 series pages). If desired, it is permissible to perform desalination washes the following as long as the engine is washed prior to the next flight. The goal and intent is to rinse the engine compressor and compressor turbine not later than 24 hours after any flight.

NOTE: Engine rinses may be discontinued for a maximum of 7 consecutive days when the temperature drops below 36 degrees Fahrenheit. Engines shall be rinsed at the earliest opportunity when temperatures rise to greater than 36 degrees Fahrenheit. Should a “cold snap” of greater than 7 days occur, the engines shall be rinsed using methanol mixture as required.

(b) The addition of cleaning agents is not necessary and water only, or a mixture of water and methanol in freezing conditions, should be used. Water used must be "Drinking Quality Water" meeting criteria defined in the Pratt & Whitney manual. If drinking quality water cannot be obtained, use demineralized water, which meets criteria defined in the manual.

2.5.3 The following information applies to accomplishment of the Performance Recovery Wash:

(a) Use only solvents approved by Pratt & Whitney Canada and/or the NAVAIR

T-44C APMSE.

(b) Use the motoring method, in accordance with the Pratt & Whitney PT6A-34B maintenance manual using an external power source.

2.6 56-DAY CORROSION INSPECTION: The Contractor shall:

2.6.1 Maintain a 56-Day corrosion inspection cycle. The authorized deviation is plus or minus three (3) days.

2.6.2 Complete the aircraft 14-Day Corrosion Preventive Maintenance requirements aircraft wash prior to 56-Day Corrosion Inspection induction.

2.6.3 Conduct corrosion inspection, evaluation and classification, and repair in accordance with NAVAIR 0l-lA-509, applicable data contained in Chapters 12 and 20 of the T-44A aircraft Maintenance Manual and this plan. Document, as a minimum, location and severity of corrosion damage.

2.6.4 During the 56-Day Corrosion Inspection, as a minimum, inspect the following areas, and the components contained within:

(a) Aircraft exterior, including landing gear and wheel wel1s.

(b) Relief tube outlet.

(c) Battery compartment.

NOTE: Removal of the battery is required.

(d) Antenna mountings.

(e) Wing, vertical and horizontal stabilizer leading edges.

(e) Exhaust track areas on nacels.

(f) Aircraft interior.

NOTE: Sub-floor areas inside of the cabin/pressure vessel shall only be removed when a 56-Day Inspection is being accomplished as part of the requirements for returning an aircraft to service after the aircraft has been in a preservation status or in an Out of Reporting status for Depot Level Repair requirements. At that time the sub-floor areas will be thoroughly cleaned, inspected and treated to remove any traces of corrosion or fungus. ?

(g) Inside of fuselage/tail section behind the aft pressure bulkhead for fungus.

(h) Ensure that the 0.19-inch-diameter drain holes in the four stringers just aft of the rear pressure bulkhead are clear of debris. One stringer is located to the right of the centerline and the other three stringers are to the left of the centerline.

(i) At the airplane lower centerline, locate the channel that parallels the access door. Visually inspect the drain hole at the lower forward end of the channel.

Ensure that it is 0.50 inch in diameter and is clear of debris. Ensure the “KEEP DRAIN HOLE OPEN” decal is located on the channel.

(j) Visually ensure that all drain holes in the ventral fin are clear of debris.

(k) Control surface hinge point and hinge pins.

(l) Areas adjacent to windows.

(m) Low point drains.

(n) Air inlet and outlets.

(o) Avionics bay.

(p) Engine compartment including, engine, engine mounts, mount bolts and accessories.

(q) Wing Spar Caps, including sealant, in accordance with Beechcraft Service

Instruction Number 0514-035 Revision II. If no sealant is applied, perform re-application of Corrosion X.

(r) The surface of the lower spar cap beneath the wing tie down for both wings.

NOTE: Sub-floor areas inside of the cabin/pressure vessel shall only be removed when a 56- Day Inspection is being accomplished as part of the requirements for returning an aircraft to service after the aircraft has been in a preservation status or in an Out of Reporting status for Depot Level Repair requirements. At that time the sub-floor areas will be thoroughly cleaned, inspected and treated to remove any traces of corrosion or fungus.

(s) Aft bulkhead behind the urinal.

2.6.5 Consider the 56-Day Corrosion Inspection complete when all corrosive damage has been evaluated and classified, documented and repaired, and the aircraft satisfactorily passes re-inspection by a Contractor's Quality Assurance Team Member.

SECTION III

EMERGENCY PROCEDURES

3.1 EMERGENCY PROCEDURES:

3.1.1 The contractor shall establish, maintain and perform emergency corrosion control procedures on T-44A aircraft and components exposed to highly corrosive agents, such as gross amounts of salt water or fire extinguishing agents, to prevent further damage, in accordance with NAVAIR 0l-lA-509 and this plan.

3.1.2 The contractor's program shall address, 1) Emergency reclamation team organization.

2) Emergency reclamation equipment. 3) Priority list for equipment removal.

3.1.3 The On-Site Government Representative will notify the contractor whenever emergency reclamation actions are required. The contractor shall recall the emergency reclamation team and direct and manage the salvage/corrosion control emergency reclamation action in accordance with NAVAIR 01-1A-509.

3.2 EMERGENCY RECLAMATION TEAM ORGANIZATION:

3.2.1 The contractor shall establish and maintain an emergency reclamation team at each operation site of sufficient size and composition of maintenance skills and perform emergency procedures as warranted by the urgency of the situation and/or program priorities.

3.2.1.1 The emergency reclamation team shall be composed, as a minimum, of a supervisor with corrosion control background and members with:

(a) Avionics maintenance skills.

(b) Powerplant/fuel system maintenance skills.

(c) Airframe maintenance skills.

3.2.1.2 A roster of designated primary and alternate emergency reclamation team members shall be maintained and published in the Monthly Maintenance Plan.

3.3 EMERGENCY RECLAMATION EQUIPMENT:

3.3.1 The contractor shall establish and maintain an emergency reclamation kit at each operation site that contains the necessary tools, equipment, and materials sufficient to perform immediate emergency reclamation actions in accordance with NAVAIR 01- 1A-509 and this plan.

3.3.1.1 The contractor shall periodically inspect the emergency, reclamation kit to ensure outdated shelf-life materials are replaced.

3.3.1.2 The contractor shall establish and maintain an inventory for each emergency reclamation kit.

3.4 EQUIPMENT REMOVAL PRIORITY LIST:

3.4.1 The contractor shall establish, maintain, and use a list designating aircraft equipment removal priority based on NAVAIR 0l-lA-509 (Priority Guide for Emergency Treatment of Aircraft) recommendations.

3.5 DOCUMENTATION:

3.5.1 The contractor shall make the proper logbook entries recording the date, location on aircraft, and corrosive agents for which emergency reclamation actions were performed.

FIGURE 2-1.1

Landing Gear Retract System

Index No. Location Lubricant Accomplished By Inspected By 5 Chain Idler Sprocket MIL-G-81327 Grease 6 Retract Chains

Where Visible Clean With Soft Cloth Dampened With Mineral Spirits.

Apply 30 Weight Oil and Wipe Off Excess.

Propellers Index No. Location Lubricant Accomplished By Inspected By

3 Propeller Hub Blade Clamps (3 Places)

Aeroshell 6 Grease

4 Low Pitch Stop Rods

Marvel Mystery Oil

FIGURE 2-1.2

Nose Landing Gear

Index No. Location Lubricant Accomplished By Inspected By 1 Door Hinges and

Retract Linkage VV-L-800General Purpose Oil

2 Grease Fittings MIL-G-81322 Grease 4 Nose Wheel Steering

Mechanism MIL-G-81322 Grease

5 Top Brace Assy (Grease Fittings)

Aeroshell Grease 17 (Do Not Substitute)

6 Grease Fittings MIL-G-81322 Grease 7 Drag Leg Stop Bolt

Grease Fitting MIL-G-81322 Grease

8 Hinge Bolts and Bushings

LPS 2

9 Drag Leg Bolts and Bushings

LPS 2

Main Landing Gear Index No. Location Lubricant Accomplished By Inspected By

1 Grease Fittings MIL-G-81322 Grease 3 Retract Grease

Fittings (10 Places) MIL-G-81322 Grease

4 Door Hinges and Retract Linkage (12 Places)

VV-L-800 General Purpose Oil

5 Yoke Assembly, Drag Brace (2 Places)

M77 Graphite Paste

1 1

4 5

FIGURE 2-1.3

Rudder and Aileron

Index No. Location Lubricant Accomplished By Inspected By 1 Rudder Trim Tab

Tube VV-L-800 Oil

3 Rudder Trim Tab Hinge

VV-L-800 Oil

5 Elevator Trim Tab Control Tubes (4 Places)

VV-L-800 Oil

6 Elevator Trim Tab Hinges

VV-L-800 Oil

6 5

FIGURE 2-2