0 Draft F-15SA PDM Work Specification.pdf

F-15SA PDM Work Specification (WS)

April 2026

Work Specification (WS) for

The Royal Saudi Air Force (RSAF) F-15SA Program Depot Maintenance (PDM)

Model Contract: XXXXXX-XX-X-XXXX

Date Prepared: MM/DD/YYYY

Table of Contents

Section Page Number

1.0 - General 4

1.1 – Information 4

1.2 - Terms Explained 5

1.3 - Data 5

1.4 - Security 9

1.5 - Quality Control Requirements 9

1.6 - Condemnation & Repair 9

1.7 - Accessory and Component Reuse, Repair and Replacement 9

1.8 - Fuel Tank Storage/Preservation 10

1.9 - Other 10

2.0 - Receipt of Aircraft at Facility 13

2.1 - Handling and Safety 13

2.2 - Inventory 14

2.3 - Preservation 15

3.0 - Work Requirements 15

3.1 - General Aircraft 15

3.2 - Specific Work Requirements 16

4.0 - Final Processing of Aircraft 66

4.1 - Finishing 66

4.2 - De-preservation 66

4.3 - Servicing 67

4.4 - Weight and Balance 68

4.5 - Preflight 68

4.6 - Flight Test 68

4.7 - Post-Flight 68

4.8 - Preparation for Ferry 68

4.9 - Forms Preparation 69

4.10 - Government Acceptance 69

5.0 - Tech Orders & Other Directives 69

5.1 - Applicable Technical Orders 69

5.2 - Applicable Time Compliance Technical Orders 70

5.3 - Applicable Directives 70

1.0 - General

1.1 – Information

1.1.1 - This Work Specification (WS) establishes the requirements for receipt, inspection, maintenance, modification, functional testing and delivery of F-15SA aircraft input for Programmed Depot Maintenance (PDM) at Source of Repair (SOR). The aircraft shall be received by and reassigned to Royal Saudi Air Force (RSAF) in accordance with (IAW) AFI 21-103. The aircraft shall be returned to RSAF in the same configuration as received. The aircraft shall contain the same type of components, accessories, and special equipment installed except as modified, removed, or added by requirements of this WS. No attempt shall be made to standardize aircraft on which previous non-standard system or structure installations have been made.

1.1.2 - New work requirements, deletion of work requirements or a scope change to requirements of this WS will not be put into effect without prior approval of the System Program Office (SPO). Prior to non-performance of a WS requirement the SOR shall notify F-15SA Engineering.

1.1.3 - Disassembly of aircraft shall be limited to the extent necessary to accomplish the inspection and work required by this specification.

1.1.4 - Maintenance outside of the WS may be accomplished by the SOR but only with approval from the PM AND

COR.

1.1.5 - During closing inspection, inspect the entire aircraft/systems after all maintenance has been completed to be sure all tools/foreign objects have been removed and there are no loose parts.

1.1.6 - A sign-off sheet and/or an in-process inspection sheet shall be maintained for closeout inspections by access panels or areas where there is, at present, no requirement for quality control listed in technical manuals.

1.1.7 - Any maintenance generated defects, (Example: Dents caused by work stands, misdrilling of sheet metal, etc.)

shall be corrected by the SOR without cost to the project.

1.1.8 - All applicable work outlined in this WS, including all TABs, must be completed for a PDM aircraft to be considered ‘sold’. THIS INCLUDES PROPER DOCUMENTATION OF ALL PDM TASKS (REMOVAL, INSPECTION, REPAIR, INSTALL, OPS CHECKOUT, SERVICING, ETC.) IAW TO 00-20-2.

1.1.9 - System checkout because of removal and reinstallation of a Line Replaceable Unit (LRU) or panel to gain access for other work shall require checkout IAW applicable Country Specific Technical Order or basic Technical Order (CSTO or TO).

CAUTION: Extreme caution must be taken in reinstallation of connections and cannon plugs to ensure that the connections are not damaged.

1.1.10 - Complete an Air Force Technical Order (AFTO) Form 238 for all wing, horizontal stabilator, and/or landing gear removal and installations. Include the component serial number, aircraft serial number, flight hours, and date of removal and/or installation.. A copy of the AFTO Form 238 for each component removal and installation shall be furnished to F-15SA Engineering immediately.

1.1.11 - Electrical wiring found to be misrouted will be brought to the attention of applicable SPO F-15SA Engineer, PM, and COR for disposition and permission to repair or leave in current configuration. Misrouted electrical wiring that presents a SOF/unsafe condition shall be corrected. Wiring not corrected shall be returned to the user in the condition received and documented on AFTO Form 781 as such.

1.1.12 - Engines on PDM aircraft shall have only those Safety of Flight (SOF) conditions corrected which are within the capabilities of the SOR. SOF conditions which cannot be corrected shall be reason to return the engine to using command for replacement. Engines with non-SOF items shall be returned to the user in the condition received under the appropriate red diagonal/red dash condition symbol. NOTE: Engines damaged because of Foreign Object Damage (FOD) and/or negligence while in possession of SOR shall be replaced by RSAF without impact upon the using RSAF wing. Engines requiring return to overhaul for any reason other than stated above shall have a replacement engine furnished by the using RSAF wing.

1.1.13 - All flight checks shall be accomplished by qualified Royal Saudi Air Force (RSAF) pilots.

1.1.14 - All SOF systems required for functional check flight (FCF) or ferry mission must be airworthy. Other systems disturbed for repair, adjustment or alteration shall be checked in sufficient depth to ensure operational reliability IAW basic CSTO. Modified components shall be operationally checked in accordance with applicable Country Specific Time Compliance Technical Order (CSTCTO) instructions. Systems not disturbed or not required for FCF and ferry mission may be returned to the using activity in the same condition as received, unless otherwise directed in this specification or by separate negotiation.

1.1.15 - All 103 delayed discrepancies shall be reviewed and considered by the PM and COR and only corrected if approved. Discrepancies not approved for work shall be entered on AFTO Form 781K and returned to the using activity for corrective action.

1.1.16 - Incoming AFTO Form 781 write-ups shall be approved/disapproved for work during predock conference.

Correct all approved write-ups.

1.1.17 - CSTCTO implementation shall be accomplished within thirty days after receipt of formal publications, and supportability for negotiated workload is available at the maintenance facility. Incorporation shall be as negotiated.

1.1.18 - Organization and Intermediate Maintenance (O&I) level CSTCTOs that have less than 60 days to rescission date shall be accomplished after approval of the PM AND COR, provided parts and kits are available.

1.1.19 - AFTO Form 103 requests for work shall be IAW TO 00-25-4.

1.1.20 - Furnish F-15SA Engineering a copy of Predock minutes.

1.1.21 - Accomplish maintenance compression requirements when directed by the SPO IAW AFI 21-102 and AFMCI 21-118 as defined in TAB B of this WS.

1.2 - Terms Explained

1.2.1 - See Attachment 1.

1.3 - Data

1.3.1 - Maintenance Records, Forms and Publications

1.3.1.1 - The applicable forms and records listed in Table 1 shall be maintained IAW the listed directives listed during the time the aircraft is at the facility. Publications delivered with the aircraft shall be maintained IAW TO 00-5-1.

Table 1

Form Number Form Title Applicable Directive AF Form 2691 Aircraft/Missile Equipment Property

Record

AFI 21-103

AF Form 2692 Aircraft Inventory Records AFI 21-103 AFTO Form 44 Turbine Wheel Historical Data 00-20-1 AFTO Form 95 Significant Historical Data 00-20-1 AFTO Form 98 Engine or Afterburner Instl Recd 00-20-1 AFTO Form 100 Series Aircraft Data Records 00-20-1 AFTO Form 103 Aircraft/Missile Condition Data 00-25-4 AFTO Form 147 Engine Hot Section Data 00-20-1 AFTO Form 242(A-D) Nondestructive Inspection Data 33B-1-1 AFTO Form 290 Aerospace Vehicle Delivery Receipt 00-20-1 AFTO Form 349 Maintenance Data Collection Records 00-20-2 AFTO Form 350 Repairable Item Processing Tag 00-20-2 AFTO Form 781 Series Aircraft Flight Data Records 00-20-1 DD Form 35 Series Record Weight & Balance 1-1B-40, 1-1B-50, 1F-15E-5

1.3.1.2 - Deficiency Reports (DRs) shall be submitted as necessary IAW TO 00-35D-54.

1.3.1.3 - All maintenance actions shall be documented IAW AFI 21-101, TO 00-20-2 and applicable -06 code manuals. Locally devised processing of forms and workbooks may be used in lieu of AFTO Form 349. Key punch cards for AFTO Forms will be processed IAW AFI 21-101.

1.3.1.4 - The aircraft records are to be maintained as described in the WS. This includes maintaining the weight and balance record on the aircraft. The table of maintenance records includes TOs 1-1B-40, 1-1B-50 and

CSTO SR1F-15SA-5.

1.3.2 - Reporting Requirements

1.3.2.1 - The SOR shall prepare the following reports as applicable.

1.3.2.1.1 - Special Delinquent Progress Report, 6-LOG-K7, IAW AFMCR 65-46.

1.3.2.1.2 - Aircraft Transfer IAW AFI 21-103.

1.3.2.1.3 - Aircraft Delivery IAW AFI 21-103.

1.3.2.1.4 - RCS 8, HAF-V39 AMREP IAW AFMCI 21-118 - DI-L-7023D.

1.3.2.1.5 - AFMC Form 200 IAW AFMCI 21-125 (C1).

1.3.2.1.6 - Reporting of F100PW220/229 Comprehensive Engine Management System (CEMS) Data.

1.3.2.1.7 - The applicable forms and records listed in Table 2 shall be used IAW the directives listed during the time the aircraft is at the SOR and just after departure to transmit data requested by this WS and TOs.

Table 2

Form Number Form Title Applicable Directive AF Form 1534 Comprehensive Engine Management System

(CEMS) Central Data Base (CDB) Report 00-25-254-1 and 00-25-254-2

AFTO Form 3 (via WebSAFE or other approved system)

F-15SA Inspection Tracking Record SR1F-15SA-36

AFTO Form 22 / RC via ETIMS Technical Order System Publication Improvement Report

00-5-1

AFTO Form 238 F-15SA Component Serialization Record SR1F-15SA-101 AFTO Form 239 F-15SA Flight Log and Exceedance Counter

Data Record

SR1F-15SA-101

AFLCMC/WWQEB Inspection/Discrepancy Report AFMCI 21-102 Local Form

1.3.2.1.8 - The applicable forms listed in Table 3 shall be used IAW the directives listed during the time the aircraft is at the SOR to request technical assistance, report technical data problems, and obtain general information to help process parts for delivery and storage.

Table 3

Form Number Form Title Applicable Directive(s) AFMC Form 202 Nonconforming Technical Assistance Request and Reply

AFMC MAN 21-1

AFMC Form 252 Liaison Engineering Change Order

(LECO)

AFMC MAN 21-1

AFMC Form 872 Packaging Requirements AFMCI 24-201 AFMC Form 874 Time Compliance Technical Order Supply Data

Requirement

AFMC MAN 21-1

DD Form 250 Material Inspection and Receiving Report AFMAN 23-122, and/or AFI 23-101 DD Form 1348 Department of Defense (DOD) Single Line Item

Requisition System Document AFMAN 23-122, and/or AFI 23-101

DD Form 1664 Data Item Description DODI 5000-2 AF SUP 1

1.3.3 - Technical Data

1.3.3.1 - Specific TOs, publications, and directives are specified in Section 5 of this WS (does not include CSTCTOs).

1.3.3.2 Structural repairs accomplished by the SOR shall conform to TOs SR1F-15SA-3-1, SR1F-15SA-3-2, SR1F-15SA-3-3, SR1F-15SA-3-4, SR1F-15SA-3-5, SR1F-15SA-3-6, SR1F-15SA-3-7, SR1F-15SA-3-8, 1F-15-3, 1-1A-8, 1-1A-1 or other authorized directives as specified by F-15SA Engineering.

1.3.3.3 - Replacement parts, materials, equipment and components used in the repair of the aircraft or any component of the aircraft shall be those authorized in approved publications. Any substitution shall be approved by appropriate F-15SA engineers at the SPO.

1.3.3.4 - Engineering and maintenance procedures not covered by specific TOs shall conform to the following general TOs: TO 1-1-3 Preparations, Inspections and Repair of Fuel Cells, TO 1-1-8 Applications of Organic Coatings, Aerospace Equipment, TO 1-1-689 Corrosion Prevention & Control, Comprehensive Engine Management System (CEMS) Equipment, TO 1-1-691 Aircraft Weapons Systems Cleaning and Corrosion Control, TO 1-1A-1 General Manual for Structural Repair, TO 1-1A-8 Aircraft Structural Manual, TO 1-1A-9 Aircraft Metals, TO 1-1A-12 Maintenance and Repair of Plastics, TO 1-1A-14 Installation Practices for Electric and Electronic Wiring, TO 1F-15A- 2-00-WD-20-1 General Wiring and Repair Procedures.

1.3.3.5 - Anti-friction bearings removed for maintenance shall be maintained IAW TOs 44B-1-2, 44B-1-3 and 44B-1- 102.

1.3.3.6 - Identification, inspection, installation and replacement of flexible/rigid hose and fittings shall conform to applicable basic TOs or instructions of TOs 1-1A-1, 1-1A-8, 44H3-1-3 and 42E1-1-1.

1.3.3.7 - Obtain and use approved torque values and safety methods from the applicable JGs, -3 series CSTOs or TO 1- 1A-8.

1.3.3.8 - Aircraft weight and balance is specified in TO SR1F-15SA-5. Qualification of weight and balance personnel shall be IAW TO 1-1B-50.

1.3.3.9 - If welding is required, personnel shall be qualified IAW SAE-AMS-1595. Ref AFI 21-105 and TO 00-25-252.

1.3.3.10 - Inspection, test and replacement of vibration isolators (other than engine mounts) shall conform to TO 1-1-19.

1.3.3.11 - Fluids, fuel, oil, grease and paint compounds used shall conform to specifications in TOs for this aircraft.

1.3.3.12 - Inspection, installation, and repair of electrical wiring, conduits, and connectors not specifically covered in the Basic Maintenance Instruction Manuals shall conform to TO 1-1A-14 and TO 8-1-1.

1.3.3.13 - The issue, storage, acceptance, and installation of synthetic rubber parts and other dated items shall be IAW TO 00-20K-1 and the Stock Number Users Directory (SNUD), as applicable. If time replacement interval conflicts between TO 00-20K-1 and SNUD, SNUD shall take precedence.

1.3.3.14 - The ACES II seat and cartridge/propellant actuated items of the emergency egress system shall be removed/installed by certified egress personnel IAW the basic TO 13A5-56-11 and AFI 21-112. Explosive components shall be stored IAW TO 11P3-1-7 and AFMAN 91-201.

NOTE

The cartridge/propellant actuated device items of the emergency egress system shall be removed/installed by qualified egress personnel. Personnel handling explosive components will be qualified IAW AFI 21-112.

1.3.3.15 - Maintain landing gear wheel brakes IAW TOs 4B-1-1 and 4B-1-32.

1.3.3.16 - Aircraft wheels shall be maintained IAW the basic TO and TO 4W-1-61.

1.3.3.17 - Servicing, removal, installation and replacement of tires shall be IAW the basic TO and TO 4T-1-3.

1.3.3.18 - Hydraulic fluid used for servicing the aircraft and in-ground/test equipment shall conform to either MIL-PRF-5606H or MIL-PRF-83282D, as applicable.

1.3.3.19 - Nondestructive Inspection (NDI) methods (TO 33B-1-1 and CSTO SR1F-15SA-36) shall be utilized when:

1.3.3.19.1 - Directed by TOs or this WS, where instructions are not stated in CSTO SR1F-15SA-36.

1.3.3.19.2 - Questionable visual indications of defects are noted.

1.3.3.19.3 - Parts are reworked in any way that could adversely affect the quality of parts such as routing, welding, machining, plating, grinding, heat treating, etc.

1.3.3.20 - Clean and treat transparent surfaces, canopies and windshield IAW the basic TO and TO 1-1A-12.

1.4 – Security

1.4.1 - The SOR shall comply with the security requirements of the Performance Work Statement (PWS) and Standard

Operating Procedures (autos).

1.5 - Quality Control Requirements

1.5.1 - The SOR inspection system shall be IAW AFMCI 21-108.

1.6 - Condemnation & Repair

1.6.1 - The SOR shall not repair items where the cost of parts and labor exceeds 75 percent of the replacement cost of the items IAW TO 00-20-3 unless directed by the PM AND COR.

1.6.2 - The SOR shall have prior approval of the PM AND COR before taking condemnation action.

1.6.3 - All items condemned that contain precious metals/critical alloys and/or all precious metals/critical alloys bearing scrap shall be turned in to the nearest Defense Property Disposal Office in accordance with DOD 4160.21M, Chapter XVIII unless other specific instructions are furnished by the PM AND COR. Part numbers of precious metal/critical alloys such as beryllium, cobalt, nickel, titanium and tungsten are identified in TO 00-25-113.

1.6.4 - The SOR shall not inspect, repair or recondition expendable parts if the parts and labor are equal to or exceeds the Defense Logistics Agency (DLA) or RSAF GOLD unit price.

1.6.5 - When a replacement part or authorized substitute is not available from any source, including local manufacture, in a timely manner resulting in aircraft flow slippage, the SOR shall submit a Nonconformance Report (NCR) to allow engineering evaluation of alternative parts and/or repair via AutoTAR or AF-PLM ETAR.

1.6.6 - If a replacement part requirement is filled outside the normal supply channel i.e. AutoTAR or AF-PLM ETAR, local purchase, local manufacture, etc. the SOR shall submit a Demand History Allocation (DHA) and notify the source of supply IAW AFMCI 21-129, AFMCI 21-130 and AFMCI 21-133.

1.7 - Accessory and Component Reuse, Repair and Replacement

1.7.1 - Accessories and components removed solely for work accessibility shall not be replaced or routed for repair but shall be reinstalled on the aircraft.

1.7.2 - All removed parts and components held for reinstallation shall be inventoried, identified (tagged) with the aircraft serial number, protected, and properly stored to prevent damage and/or loss.

1.7.3 - When inspection, operational check or bench check reveals that an item is defective and intermediate level maintenance will not correct the defect, accessories and components will be replaced with serviceable items. In the event serviceable accessories or components cannot be provided in sufficient time to avoid work stoppage, the SOR may overhaul repairable accessories or components only to the extent required to prevent work stoppage, providing such overhaul or repair is within the maintenance capability and is approved by the PM AND COR.

1.7.4 - Initial local manufacture (LM) items will not be manufactured and cost charged to aircraft without approval of the PM AND COR. Recurring LM items will be IAW G005M System.

1.7.5 - Extreme caution must be taken during reinstallation of connections and cannon plugs to insure that the connections are not damaged.

1.7.6 - Only "A" conditioned assets will be installed on all aircraft. Any deviations will be assessed and require authorization from F-15SA Engineering.

1.8 - Fuel Tank Storage/Preservation

1.8.1 - All drained fuel cells and external and internal tanks shall be treated for storage IAW TO 1-1-3, CSTO SR1F- 15SA-17, and the basic TO.

1.8.2 - Temporary outside storage of aircraft and external tanks shall be IAW TO 1-1-17 and CSTO SR1F-15SA-17.

1.8.3 - Turbo-jet oil and lubricating oil drained for any reason shall not be reused and shall be disposed of as administratively condemned property IAW TO 42B2-1-3. If there is a hydraulic purifier available, purify the hydraulic fluid for reuse. Otherwise, discard IAW TO 42B2-1-3.

1.8.4 - Engines which are to be shipped to another location will be preserved and prepared for shipment IAW TO 2J- 1-18 and CSTO SR1F-15SA-17.

1.9 - Other

1.9.1 - Tab B Maintenance Compression Requirements

1.9.1.1 - Scope

1.9.1.1.1 - This Tab B establishes the maintenance compression requirements for F-15SA aircraft in the event maintenance compression is directed by the System Program Office (SPO) Director. A current detailed plan will be maintained by the SOR. The plan is used to accelerate the shift of work or personnel immediately and shall replace the WS. Plans will be submitted to F-15SA Engineering for evaluation.

1.9.1.1.2 - The aircraft shall be prepared for delivery to the owning RSAF Wing to an operational status according to the requirements outlined herein.

1.9.1.1.3 - The requirements outlined herein shall be complied with for the duration that the maintenance compression is in effect.

1.9.1.1.4 - Replace defective components, unless only minor repair is necessary.

1.9.1.1.5 - Cannibalization will be from aircraft requiring excessive work only.

1.9.1.1.6 - Aircraft shall be processed under one of the following conditions below to permit expedited delivery to the owning RSAF Wing as soon as possible (earliest possible date after induction).

1.9.1.1.6.1 - Condition "A": Aircraft in flight test status/outgoing that is painted.

1.9.1.1.6.2 - Condition "B": Aircraft incoming for shop work that are determined (by examination of the aircraft forms) to be in flyable status will be returned to service (turn around) after compliance with the work detailed below for Condition "B" aircraft.

1.9.1.1.6.3 - Condition "C": Aircraft that can be removed and "buttoned up" from initial PDM cells/stations (in work 4 to 6 workdays) with engines installed and basically satisfactory with minor expenditure of manhours.

1.9.1.1.6.4 - Condition "D": Aircraft in final PDM cells/gates/stations (after fuel system check with engines installed).

1.9.1.1.6.5 - Condition "E": Aircraft requiring major modification (including those in PDM flow already undergoing modification and those in permanent storage).

1.9.1.1.7 - Every effort shall be expended to accomplish required work and delivery of the aircraft to the RSAF in the order of condition listed above. Aircraft requiring the least amount of work shall be processed first.

1.9.1.1.8 - The AF Forms 2691 and 2692, Air Force Technical Order (AFTO) Form 95 and AFTO Form 781 series for the work accomplished shall be maintained and completed IAW Technical Order (TO) 00-20 series. An entry shall be made under remarks on AFTO Form 95 to indicate that the aircraft was processed IAW Maintenance Compression work requirements. All systems that are authorized to be inoperative shall be listed on AFTO Form 781 as inoperative.

1.9.1.1.9 - All other aircraft records, forms and publications shall be brought up to date, unless otherwise directed, and shall be returned with the aircraft. For identity of other forms and applicable directives related thereto refer to WS, Section I, paragraph 1.3.1.

1.9.1.1.10 - To provide a combat ready weapon system, aircraft systems/subsystems must be operational IAW the requirements of the Minimum Essential Subsystem List (MESL) provided in the appropriate AFI 21-103 supplement addendum.

1.9.1.2 - Specific Work Requirements

1.9.1.2.1 - Aircraft Condition "A"

1.9.1.2.1.1 - Accomplish preflight and Postflight inspections IAW applicable TOs and correct SOF discrepancies prior to delivery of the aircraft to the using RSAF Wing.

1.9.1.2.2 - Aircraft Condition "B"

1.9.1.2.2.1 - Review the aircraft maintenance records to determine the status and flying condition of the aircraft.

1.9.1.2.2.2 - Accomplish preflight and Postflight inspections IAW applicable TOs and correct SOF discrepancies and Red X items revealed during inspection or examination of the records prior to delivery of the aircraft to the using RSAF Wing.

1.9.1.2.3 - Aircraft Condition "C"

1.9.1.2.3.1 - Reinstall all removed components IAW applicable TOs and visually inspect all affected areas before aircraft close.

1.9.1.2.3.2 - Perform fuel system pressure check IAW applicable TOs. NOTE: The aircraft should be completely reassembled and be in Condition "D" status.

1.9.1.2.3.3 - Aircraft Condition "D"

1.9.1.2.3.4 - Rig and operationally check landing gear, wheel brakes, aileron, rudder, stabilator, and flaps IAW applicable TOs.

1.9.1.2.3.5 - Perform fuel system leak/operational check IAW applicable TOs

1.9.1.2.4 - Aircraft Condition "E"

1.9.1.2.4.1 - When compression action is directed, a repair status of the aircraft must be conducted to determine the major repair tasks that must be fully accomplished while others may be curtailed or omitted. Technical assistance in evaluation of repair requirements can be obtained from F-15SA Engineering.

1.9.1.3 – Aircraft Finishing

1.9.1.3.1 - Aircraft in Conditions "A", "C", "D", and "E".

1.9.1.3.1.1 - Inspect interior of aircraft and remove all loose debris, such as: filings, chips, loose hardware, etc..

1.9.1.3.1.2 - Apply aircraft insignia and call letters conforming with TOs 1-1-8 and CSTO SR1F-15SA-23, if removed. Touch-up if illegible. No other markings shall be required unless otherwise directed.

1.9.1.3.2 - Aircraft in Condition "B" (Turnaround) shall be returned as received.

1.9.1.3.3 - Weight and Balance

1.9.1.3.3.1- Weigh aircraft and complete the weight and balance records IAW the provisions in CSTO SR1F-15SA-5 and TO 1-1B-50 only when work accomplished affects weight and balance, when weighing of aircraft is necessary to ensure SOF, or when requested on an AFTO Form 103 and approved.

1.9.1.4 - Flight Test and Government Acceptance

1.9.1.4.1 - Aircraft in Conditions "A", "C", "D", and "E" shall have the following accomplished:

1.9.1.4.1.1 - If applicable, depreserve engines IAW TO 2J-1-18.

1.9.1.4.1.2 - If applicable, service all systems IAW applicable TOs.

1.9.1.4.1.3 - Accomplish a preflight launch and end of runway inspection IAW applicable TOs. Correct all discrepancies determined to affect SOF.

1.9.1.4.1.4 - Due to work assignment (Condition "A" through "E") of the aircraft, flight testing of each aircraft shall be as determined by the SPO. The SPO shall determine whether to utilize RSAF flight test pilots or pick-up pilots to accomplish flight testing as circumstances dictate. The SPO shall also determine if the pick-up pilot can perform the test flight in the local area and continue to their destination if the aircraft is determined to be satisfactory.

1.9.1.4.1.5 - Accomplish thru-flight inspection IAW applicable TOs. Correct all discrepancies determined to affect SOF.

1.9.1.4.1.6 - The inventory referenced in AFI 21-103 shall be held to MINIMUM combat readiness essentials on Conditions "A", "C", "D", and "E" aircraft. Every effort shall be made to accomplish inventory at the same time until flight inspection is accomplished. Aircraft in Condition "B" shall not require inventory when they do not go into shops for maintenance and modification.

1.9.1.4.2 - Aircraft in Condition "B" shall not normally be test flown unless work performed falls under the provisions of TO 1-1-300 and SR1F-15SA-6.

1.9.1.5 - Technical Orders and Other AF Directive Requirement

1.9.1.5.1 - Immediate Action CSTCTOs shall be accomplished as applicable to Condition "A", "B", "C", "D", and "E" aircraft.

1.9.1.5.2 - Urgent Action CSTCTOs shall be accomplished as applicable to Condition "A", "C", "D", and "E" aircraft, except when the aircraft have progressed to completion and would require disassembly or constitute a delay that is contrary to the maintenance compression policy.

1.9.1.5.3 - Routine and Other CSTCTOs shall be subject to compliance only when time shall permit and when disassembly and work is to be accomplished on the item and is not cause for delaying the aircraft.

1.9.1.5.4 - Condition "B" aircraft should not be processed in work and therefore should not be delayed for CSTCTO compliance other than Immediate Action CSTCTOs directed for compliance by the SPO.

1.9.1.5.5 - Applicable regulation is AFMCI 21-118, Aircraft and Missile Maintenance Production/Compression Report (AMREP) System.

2.0 - Receipt of Aircraft at Facility

2.1 - Handling and Safety

2.1.1 - Render Safe

2.1.1.1 - Grounding for dissipation of static electricity shall be IAW TO 00-25-172.

2.1.1.2 - The following hazardous equipment shall be made safe and handled IAW cited TOs.

2.1.1.2.1 - Impulse cartridges for external stores MK-1 Mod 3, MK-2 Mod 1, ARD 446-1, and ARD 863-1 shall be removed IAW TO 11A-1-33, CSTO SR1F-15SA-33-1-2, and stored IAW TO 11A18-7-7 and AFMAN 91-201.

Personnel shall be qualified IAW AFI 23-106 and AFI 21-112.

2.1.1.2.2 - Fire extinguisher cartridges shall be removed IAW CSTO SR1F-15SA-2-26JG-20-1

2.1.1.2.3 - If the gun is installed, make safe for maintenance. Check gun, install safety pin, no ammo in gun, gun bay, and cavity of door 45. Install clearing sector tool. Reference CSTO SR1F-15SA-2-05JG-10-1.

2.1.1.2.4 - Pylons shall be de-armed, removed and stored for reinstallation IAW CSTO SR1F-15SA-2-94JG-32-1 once external tanks are removed.

2.1.1.2.5 - Dearm and make safe all munitions and explosive devices. WARNING All munitions shall be removed by the using activity prior to aircraft input. Should munitions be found aboard aircraft, the maintenance facility shall notify the PM AND COR.

2.1.1.2.6 - Transport munitions to and from approved munitions storage areas as required.

2.1.1.3 - Foreign Object Damage prevention to jet engines, tires and aircraft flight surfaces shall be IAW AFI 21-101.

2.1.1.4 - Drain/purge oxygen system IAW CSTO SR1F-15SA-2-35JG-11-1, and TOs 1F-15-3, 15X-1-1.

2.1.2 - Parking, Towing, Jacking

2.1.2.1 - The SOR shall handle, park, service, tow, dock, jack and moor aircraft IAW CSTOs SR1F-15SA-2-07JG-00-1, SR1F-15SA-2-09JG-00-1, SR1F-15SA-2-10JG-00-1, SR1F-15SA-3-1 and 1F-15-3 as required. Comply with all aircraft ground safety instructions as directed in applicable CSTOs and TOs.

2.1.2.2 - Qualification of personnel operating or moving aircraft shall conform to AFI 11-218, AFI 11-205, and AFMC Supplement 1 to AFI 11-218.

2.1.2.3 - Quality control of gaseous and liquid aviators breathing oxygen shall be IAW MIL-PRF-27210.

2.1.2.4 - Aircraft placed in hangars shall conform to the requirements specified in Appendix A, Industrial Safety and Health Requirements.

2.1.3 - Joint Oil Analysis Program

2.1.3.1 - Perform a Joint Oil Analysis Program (JOAP) sample within thirty minutes of engine shutdown after aircraft arrival IAW CSTO SR1F-1SA-2-05JG-00-2.

2.1.3.2 - Perform the lab test of the JOAP sample IAW TOs 33-1-37-1, 33-1-37-2, and 33-1-37-3.

2.1.4 – Fuel

2.1.4.1 - Handle and store fuel according to TOs 00-25-172, 42B-1-1, 42B1-1-1, MIL-STD-1518C and AFOSH 127-43.

2.1.4.2 - All personnel engaged in fuel system maintenance and repair shall be qualified IAW the basic TOs and TO 1-1- 3.

2.1.4.3 - Defuel, purge and perform an explosive vapor level check as required to ensure the aircraft is safe for work IAW TO 1-1-3, CSTOs SR1F-15SA-2-12JG-10-2, and SR1F-15SA-2-12JG-11-1. Serviceable fuel shall be recorded on AFTO Form 781-2 and credited to the aircraft when servicing.

2.1.4.4 - Temporary outside storage of aircraft and external tanks shall be IAW TO 1-1-17 and CSTO SR1F-15SA-17.

2.1.5 - Receiving Aircraft

2.2 - Inventory

2.2.1 - Accomplish inventory inspection IAW AFI 21-103.

2.2.2 - Remove all classified equipment and store IAW applicable CSTOs and TOs.

2.2.3 - Record and process inventory IAW CSTO SR1F-15SA-21.

2.2.4 - Loose equipment shall be inventoried, tagged with aircraft serial number, inspected and stored in a secure area and returned with the same aircraft in the condition as received. NOTE: Notify SPO of shortages and advise if command should or should not ship shortages to SOR. Shortages, except those which occur while aircraft is at the SOR shall not be made up.

2.2.5 - Manufacture metal tags for all parts removed from the aircraft to identify the parts and indicate the aircraft serial number on the tag so the reinstallation of the part may be made to the same aircraft.

2.3 – Preservation

2.3.1 - Remove and preserve engines and Jet Fuel Starter (JFS), and Fuel Flow Transmitters IAW TO 2J-1-18, CSTOs SR1F-15SA-17, SR1F-15SA-2-71JG-03-1, SR1F-15SA-2-80JG-10-1, SR1F-15SA-2-73JG-31-1, and other applicable TOs and CSTOs. Remove the AMAD driveshafts while removing the engines IAW TO SR1F-15SA-2-83JG-10-1.

2.3.2 - Turbo-jet oil and lubricating oil drained for any reason shall not be reused and shall be disposed of as administratively condemned property IAW TO 42B2-1-3. If there is a hydraulic purifier available, purify the hydraulic fluid for reuse. Otherwise, discard IAW TO 42B2-1-3.

2.3.3 - Engines which are to be shipped to another location shall be preserved and prepared for shipment IAW TO 2J-1- 18 and CSTO SR1F-15SA-17.

3.0 - Work Requirements

3.1 - General Aircraft

3.1.1 - The following inspections and maintenance shall be accomplished in accordance with appropriate technical orders and Air Force publications listed in Section 5 of this WS. The discrepancies noted because of this inspection shall be corrected to the degree which shall result in a serviceable condition. All items removed to facilitate inspection, or other reasons, shall be reinstalled unless replacement is otherwise directed. NOTE: In the event work required by this specification cannot be accomplished, contact the SPO for assistance in resolving the problem.

3.1.2 - Sealant and coating systems shall be mechanically or chemically removed in accordance with TOs 1-1-691, 1- 1-8, 1-1-3, and CSTO SR1F-15SA-23 as necessary to accomplish the inspection requirements of this WS.

3.1.3 - Accomplish the following Tabs as directed by this WS.

3.1.3.1 - Accomplish Analytical Condition Inspection (ACI) when required in accordance with TAB A of this WS.

3.1.3.2 - Accomplish maintenance compression requirements when directed by the SPO IAW AFI 21-102 and AFMCI 21-118 as defined in TAB B of this WS.

3.1.3.3 - Accomplish painting IAW TAB C of this WS.

3.1.3.4 - Accomplish work requirements IAW TAB D of this WS.

3.1.3.5 - Accomplish corrosion treatment requirements in accordance with TAB E of this WS.

3.1.4 - The following shops and offices shall be maintained to support the F-15SA aircraft: Sealant Shop, Oxygen/Nitrogen Shops, Lubricant Shop, Hazardous Material Handling, Tool Crib, Local Manufacture, Tire Shop and Vault. Other shops shall be supported as necessary.

3.1.6 - Install rubber protection on aircraft doors, panels, and surfaces which pose a hazard to equipment and personnel.

3.1.7 - Perform Lower Explosives Limit (LEL) check IAW CSTO SR1F-15SA-2-28GS-00-1 and TO 1-1-3 prior to beginning work on each shift.

3.1.8 - Perform explosive vapor level check IAW TO 1-1-3 on each wing leading edge through drain holes and wing tips using an R-2 combustible and toxic gas indicator or equivalent prior to applying electrical power at predock, after initial refueling and initially at functional test. If the fire safe reading contained in TO 1-1-3 cannot be obtained or if there is evidence of leakage, make repairs per applicable technical manuals.

3.1.9 - In the event special condition items (such as: hard landings, landing gear removals, operation under extremely dusty conditions, etc.) are encountered during processing of aircraft and/or listed as outstanding discrepancies on 781 forms upon receipt of aircraft, the applicable inspection requirements of CSTO SR1F-15SA-6 shall be accomplished and corrective action taken as directed by the SPO.

3.1.10 - Complete all Individual Aircraft Tracking (IAT) and CSTO SR1F-15SA-6 Section II Part B inspections below unless told otherwise. Also reference Attachment 2 for the complete list of 100% required IATs to be inspected. Input the results of all IAT and CSTO SR1F-15SA-6 Section II Part B inspection results into the Boeing BPN WebSAFE AFTO Form 3 link IAW CSTO SR1F-15SA-6. Document the repair and/or replacement actions taken with the P/N and/or hole numbers using the number system outlined in CSTO SR1F-15SA-36. If the hole numbers do not exist, provide a description of the repair location. NOTE: For aircraft stated to complete IAT when called out in CSTO SR1F- 15SA-6S-xxxx, the IAT inspection shall be completed for the calendar quarters that the aircraft will be at the depot and for one quarter after delivery.

3.1.11 - Incoming repairs on accessible internal wing torque box structure, fuselage longerons, machined bulkheads or formers, and any aircraft structure with Class 1, 2, or 3 stress intensity as defined by 1F-15E-3-2 requires an NCR for engineering disposition except for repairs installed by CSTCTOs, which do not require a NCR for engineering disposition. In addition, FS 415 doubler repair and FS 626 bulkhead preventative repair do not require NCR submission for engineering disposition. NCRs shall also be submitted for non-standard or non-compliant CSTO SR1F-15SA-3 TO series structural repairs. Safety-of-Flight (SOF) conditions shall be corrected as determined and approved by F-15SA Engineering. Any of these incoming repairs (SOF or non-SOF) that require action will be repaired as directed by the SPO.

3.2 - Specific Work Requirements

3.2.1 - Part A Depot Maintenance

3.2.1.1 - Predock and Disassembly

3.2.1.1.1 - Aircraft (including wings) shall be subjected to a general condition inspection (visual) prior to disassembly and after depaint (especially looking in all corrosion prone areas IAW CSTO SR1F-15SA-23) to determine obvious discrepancies, deterioration (structures, inlets, paint, flight controls, landing gear, canopy, etc.) wear, tear, and cleanliness. Skins shall be inspected for cracks, buckled skins, missing or loose fasteners, and corrosion. Repair, remove and replace, or remove and route for repair as directed by the SPO those items identified as unserviceable or missing because of findings from the general condition inspection and approved for work by SPO and this WS.

3.2.1.1.2 - Prior to depainting the aircraft, document the location of loose or working fasteners on the aircraft, (including intakes) and components (wing, stabilizers, ramps, etc.). Identify all fasteners with dark residue around fastener. In some cases, the residue streaks behind the fastener. This is an indication there has been movement of the fastener in the structure. The documentation should have the bad fasteners clearly marked (preferably a photograph with the fasteners circled). Provide all documentation to F-15SA SPO engineering. This condition must be repaired IAW CSTO SR1F-15SA-3-2. If no specific repair exists submit an NCR for engineering disposition.

3.2.1.1.3 - Install protective covers on canopies (inside and outside), L/R Engine Intake and Exhaust, Pitot Probes, Angle of Attack Probes, and tape Plenum Chamber Holes IAW applicable TOs and CSTOs.

3.2.1.1.4 - Inspect engines for Foreign Object Damage (FOD) and any other visible damage. FOD shall immediately be brought to the attention of F-15SA Planning and F-15SA SPO. Defects shall be worked that are within the capabilities of the SOR and applicable technical orders.

3.2.1.1.5 - Extend Speedbrake and install Safety Strut, P/N 68D050011-1005 IAW CSTO SR1F-15SA-2-05JG-10-1.

3.2.1.1.6 - Temporarily remove canopy IAW CSTO SR1F-15SA-2-95JG-21-2 to accommodate aft seat removal and temporarily install canopy prior to depaint. Once aircraft is depainted, remove canopy IAW

CSTO SR1F-15SA-2-95JG-21-2.

3.2.1.1.7 - Remove ejection seat(s) IAW CSTO 1F-15SA-2-95JG-11-1. Ejection seats shall be transported on Ejection Seat Support Dolly, P/N 64A127J1-1.

3.2.1.1.8 - Ensure necessary components are removed from the aircraft prior to depainting the aircraft and depaint the aircraft and removed components IAW TAB C of this WS.

3.2.1.1.8.1 - Remove left and right ailerons IAW CSTO SR1F-15SA-2-27JG-11-2.

3.2.1.1.8.2 - Remove left and right aileron actuators IAW CSTO SR1F-15SA-2-27JG-11-2.

3.2.1.1.8.3 - Remove left and right flaps IAW CSTO SR1F-15SA-2-27JG-50-1.

3.2.1.1.8.4 - Remove left and right flap actuators IAW CSTO SR1F-15SA-2-27JG-50-1.

3.2.1.1.8.5 - Remove speedbrake IAW CSTO SR1F-15SA-2-27JG-60-1.

3.2.1.1.8.6 - Remove left and right horizontal stabilators IAW CSTO SR1F-15SA-2-27JG-41-2 and turn them into supply. Requisition new left and right horizontal stabilators with gridlock components.

3.2.1.1.8.7 - Remove left and right rudder/rudder drive fitting assemblies IAW TO 1F-15E-2-27JG-20-3. Inspect rudders to determine if they are two-bolt configuration, P/N 68A240001-1019. If they are not, replace with two-bolt configuration, P/N 68A240001-1019, and rudder drive fitting.

3.2.1.1.9 - Remove the ammo drum IAW SR1F-15SA-2-94JG-50-2 to facilitate other maintenance.

3.2.1.1.10 - Remove left and right wing IAW CSTO SR1F-15SA-3-6 and transport wings to wing backshop area IAW CSTOs 1F-15-3 and SR1F-15SA-6 to complete wing maintenance. Complete an AFTO Form 238 for all removed wings, recording the wing serial number, aircraft serial number, flight hours of the aircraft and any other important information as required by this WS. Use CSTO 1F-15SA-101 for instructions on how to complete the form. Provide the form to F-15SA Engineering within one working day of removal of the wings from the aircraft. Wings removed from Flight Data Recorder (FDR) aircraft will be marked "FDR Wing." If a wing change must be made due to long lead time parts, the new wing will be equipped with the appropriate equipment as per CSTO SR1F-15SA-3-6.

3.2.1.1.11 - Remove the radome from the aircraft IAW CSTO SR1F-15SA-3-4. Retain the radome for reinstallation.

3.2.1.1.12 - Remove glideslope antenna from the radome IAW CSTO SR1F-15SA-2-34JG-30-1.

3.2.1.1.13 - Remove left and right main landing gear (MLG) IAW CSTO SR1F-15SA-2-32JG-10-1.

3.2.1.1.14 - Remove nose landing gear (NLG) IAW CSTO SR1F-15SA-2-32JG-20-1.

3.2.1.1.15 - Remove nose landing gear drag brace IAW CSTO SR1F-15SA-2-32JG-20-2.

3.2.1.1.16 - Remove all doors, covers, and removable panels for access into areas requiring work in accordance with this WS.

3.2.1.1.17 - Remove the left and right variable ramp inlet assembly IAW CSTO SR1F-15SA-2-71JG-60-2. Turn in the first and third ramps into supply and order serviceable ramps from supply. Retain the second variable ramp for reinstallation. Depaint and paint the second variable ramp IAW CSTO SR1F-15SA-23.

3.2.1.1.18 - Remove the left and right diffuser ramps IAW CSTO SR1F-15SA-2-71JG-60-2. Turn diffuser ramps in to supply and order serviceable ramps from supply.

3.2.1.1.19 - Remove left and right Utility Hydraulic pumps IAW CSTO SR1F-15SA-2-29JG-11-2.

3.2.1.1.20 - Remove Power Control (PC) System 1 hydraulic pump IAW CSTO SR1F-15SA-2-29JG-10-1.

3.2.1.1.21 - Remove Power Control (PC) System 2 hydraulic pump IAW CSTO SR1F-15SA-2-29JG-10-2.

3.2.1.1.22 - Remove left and right Airframe Mounted Accessory Drive (AMAD) IAW CSTO SR1F-15SA-2-83JG-20-1.

3.2.1.1.23 - Remove left and right utility pump manifolds IAW TO CSTO SR1F-15SA-2-29JG-11-2.

3.2.1.1.24 - Remove Power Control (PC) System 1 pump manifold IAW CSTO SR1F-15SA-2-29JG-10-1.

3.2.1.1.25 - Remove Power Control (PC) System 2 pump manifold IAW CSTO SR1F-15SA-2-29JG-10-2.

3.2.1.1.26 - Remove left and right Integrated Drive Generator (IDG) IAW TO CSTO SR1F-15SA-2-24JG-10-1.

3.2.1.1.27 - Remove Central Gearbox (CGB) IAW TO CSTO SR1F-15SA-2-80JG-12-1.

3.2.1.2 - Wings

3.2.1.2.1 - Remove wings from aircraft. Complete an AFTO Form 238 for all removed wings recording the wing serial number, aircraft serial number, flight hours of the aircraft and any other important information as required by this WS. Use CSTO SR1F-15SA-101 for instructions on how to complete the form. Provide the AFTO Form 238 to F-15SA Engineering within one working day of removal of the wings from the aircraft.

3.2.1.2.2 - Visually inspect all wing to fuselage attach lug bushings at F.S. 509.5 through 626.9 for corrosion, galling, fretting, and any other unsatisfactory conditions that may exist. Measure the inside diameters of each bushing to ensure proper sizes per CSTO SR1F-15SA-3-6 Figure 2-1.

3.2.1.2.2.1 - Replace all wing-to-fuselage pins. Enter the data for parts replaced into the Boeing BPN WebSAFE Replaced part tool link, https://bpn.boeing.com/WebSAFE-Saudi/ReplacedPart/. If all pins are not replaced, submit an NCR for engineering disposition to the SPO.

3.2.1.2.2.2 - Replace all wing-to-fuselage bolts. Enter the data for parts replaced into the Boeing BPN WebSAFE Replaced Parts Tool link, https://bpn.boeing.com/WebSAFE-Saudi/ReplacedPart/. If all bolts are not replaced, submit an NCR for engineering disposition to the SPO.

3.2.1.2.2.3 - NDI all fuselage attach lugs IAW CSTO SR1F-15SA-36. Input the results to the Boeing BPN WebSAFE AFTO Form 3 link IAW CSTOs SR1F-15SA-6 and SR1F-15SA-101 to report that the inspection was performed and report any discrepancies and/or repair actions. Alternatively, provide the AFTO Form 3 to F-15SA SPO Engineering within 1 working day of completion of the inspections.

3.2.1.2.4 - Transport wing(s) to appropriate shop for remainder of the wing work.

3.2.1.2.5 - Refer to TAB D for wing work on wing serial numbers A24-0001 and up. Accomplish ACI on wings as necessary IAW Tab A.

3.2.1.2.5.1 - TAB D Wing Work

3.2.1.2.5.1.1 - General:

3.2.1.2.5.1.1.1 - The information contained in this section is not intended to be all inclusive nor to distract from procedures outlined in technical orders, specifications, standards and drawings listed in Section 5 of the WS, except where specifically noted herein.

3.2.1.2.5.1.1.2 - Repair of the wing includes all actions necessary to return them to the output configuration set forth in section 3.4.

3.2.1.2.5.1.1.3 - All major structural repairs shall be performed with wing assembly installed in the wing vertical overhaul frame, P/N 168110001 or the modified vertical overhaul frame, P/N X8526568 IAW TO 1F-15E-3-6 for work on the inboard and outboard torque box skins and ribs, and replacement of the outboard trailing edge box assembly. No other fixtures, frames or holding frames shall be used for this purpose.

3.2.1.2.5.1.1.4 - The SOR shall inspect all leading edge and trailing edge components. All wiring, tubing, and associated components in all open areas of the wing shall be visually inspected. All defective items shall be evaluated IAW applicable tech data and repaired or replaced as required

3.2.1.2.5.1.1.5 - Any damage to the wings caused by the SOR shall be corrected by the SOR at no cost to the Government.

3.2.1.2.5.1.1.7 - Wings removed from aircraft having a Flight Data Recorder (FDR) will be marked “FDR wing” and shall be reinstalled on the aircraft they were removed from. If a wing change has to be made due to long lead time parts, then the new wing will be equipped with the appropriate equipment as per TO 1F-15E-3-6.

3.2.1.2.5.1.2 - Specific Work Requirements:

3.2.1.2.5.1.2.1 - The SOR shall accomplish a pressure and leak test IAW TO 1F-15-3 and Drawing 200810782. All leaks shall be permanently repaired IAW TO 1-1-3, SR1F-15SA-3-5 and TO 1F-15E-3-6.

3.2.1.2.5.1.2.2 - Permanently and legibly mark each repaired end item with the SOR identification. This identification marking shall display the SOR name, the Air Force contract number, and date of repair. The wing “Identification Data Plate” located under door 58 L/R shall be maintained. If the plate is replaced, all data, including original serial number, shall be stamped on a new plate and the wing shall be identified IAW the latest incorporated TCTO. If the data plate is missing, search the inboard trailing edge box area under door 138 L/R for a “parts installed list” to obtain the serial number and contact the F-15 Engineering. If the “identification data plate” and the “parts installed list” have different serial numbers, immediately contact F-15 Engineering.

NOTE: When reviewing ID plate under door 138(L/R) the wing serial number must contain A24-XXXX. If not, contact F-15 Engineering.

3.2.1.2.5.1.2.2.1 - Perform a fluorescent penetrant inspection of the fuel transfer holes in the intermediate spar 68A112103 and main spar 68A112105 for cracks IAW CSTO SR1F-15SA-36. Use the eddy current inspection on the two small holes with the fastener holes around them to find cracks in the structure IAW CSTO SR1F-15SA-36.

3.2.1.2.5.1.2.3 - Visually inspect all accessible hydraulic lines, actuators and hydraulic pumps, reservoirs, for defective clamps, loose fittings, and chafing. Repair and/or replace items as required.

3.2.1.2.5.1.2.3.1 - Replace all ST9M529 plastic and ST9M494H-T steel support clamps with an equivalent size M85052/1-xx or 9M972-xxN support clamps on all hydraulic lines.

3.2.1.2.5.1.2.3.2 - Replace all seal rings on all fuel lines, vent lines and conduits while the wing is open for work.

3.2.1.2.5.1.2.4 - Remove the inboard leading edge. Remove the outboard leading edge. Do not remove the two leading edges while connected to each other (at the same time) since this could damage the leading edges and may necessitate replacement.

3.2.1.2.5.1.2.5 - Remove the wing tips.

3.2.1.2.5.1.2.5.1 - Inspect wing tips to determine if they are gridlock wing tips, P/N 68B117000. If they are gridlock wing tips, visually inspect and repair as necessary. If the wing tips are honeycomb, replace with gridlock wing tips, P/N 68B117000-101 L/H or 68B117000-102 R/H. If no gridlock wing tips are available, contact F-15 Engineering for disposition.

3.2.1.2.5.1.2.6 - Accomplish the following to prepare the wing for work in the overhaul frame.

3.2.1.2.5.1.2.6.1 - Transport the wing from the aircraft to the wing shop.

3.2.1.2.5.1.2.6.2 - Cap all plumbing. Store all loose plumbing in proper location within the parts cabinet.

3.2.1.2.5.1.2.6.3 - Temporarily install all major torque box skin panels by installing every 5th fastener. Temporarily install the trailing edge panels.

3.2.1.2.5.1.2.6.4 - Secure the leading-edge assembly to the wing for transport to the building housing the vertical overhaul frame.

3.2.1.2.5.1.2.6.5 - Install the wing in the wing overhaul frame, RE1681100001 or the modified overhaul frame IAW

TO 1F- 15E-3-6.

3.2.1.2.5.1.2.6.6 - Remove the temporarily installed skin panels and visually inspect the wing (shakedown) for obviously damaged parts and for existing repairs.

3.2.1.2.5.1.3 - The following work shall be accomplished on all wings except as noted.

3.2.1.2.5.1.3.1 - Remove the upper inboard forward and aft torque box skins to gain access for accomplishing inspections required by this WS.

3.2.1.2.5.1.3.2 - Inspect the main spar fuel vent hole IAW CSTO SR1F-15SA-36. Removal of fuel line tubing may be required to access the hole. Input the results to the Boeing BPN WebSAFE AFTO Form 3 link.

3.2.1.2.5.1.3.2.1 - Perform a fluorescent penetrant inspection of the fuel transfer holes in the main spar 68A112105 for cracks IAW CSTO SR1F-15SA-36. Use the eddy current inspection on the two small holes with the fastener holes around them to find cracks in the structure IAW CSTO SR1F-15SA-36.

NOTE: Enter the required information on the Boeing BPN WebSAFE AFTO Form 3 Link signifying completion of…