Chapter_5

A2 Jan 01/1205-LOEP

MODEL 400/400A MAINTENANCE MANUAL SUPPLEMENT

List of Effective Pages

CH-SE-SU PAGE DATE

05-LOEP 1 Jan 01/12

05-CONTENTS 1 thru 3 Jan 01/12

05-20-00 601 thru 617 Jan 01/12

05-20-01 601 thru 610 Jan 01/12

05-20-02 601 thru 624 Jan 01/12

05-20-03 601 thru 635 Jan 01/12

05-20-04 601 thru 650 Jan 01/12

05-20-05 601 thru 614 Jan 30/09


SUBJECT PAGE

CHAPTER 05 - TIME LIMITS/MAINTENANCE CHECKS

TABLE OF CONTENTS

Jan 01/12 A2 05-CONTENTS

05-20-00

Scheduled Maintenance Checks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .601General Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .601Increased Flight Activity (IFA) Inspection Program. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .601Scheduled Inspection Core Intervals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .602Recommended Inspection Program Transition. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .604

Scheduled Inspections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .604Scheduled Special Inspections. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .605

Service Information Documents . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .608Inspection Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .609

Standard Terms . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .610Inspection Criteria. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .610

Additional Requirements Introduced By Revision Action . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .612Replacement Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .617

05-20-01

Scheduled IFA-Special Inspections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .601A. 200-Hour Intervals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .601B. 200-Flying Hours From The Airplane Build. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .602C. 200-Flying Hours After Control Cable Replacement . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .602D. 600-Hour or 12-Months Initial and 200-Hour or 3-Month Subsequent . . . . . . . . . . . . . . . . . . . . . . . . . . . .603E. One-Year Intervals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .603F. Two-Year Intervals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .604G. Four-Year Intervals. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .604H. Five-Year Intervals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .604I. Six-Year Intervals. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .605J. Eight-Year Intervals. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .605K. Ten-Year Intervals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .605L. Ten-Year Initial and Five-Year Subsequent Intervals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .605M. Twelve-Year Intervals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .605N. 2,400-Hour Intervals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .606O. 3,000-Air Conditioning Operating Hours Intervals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .606P. 4,500-Hours/3,000-Landings Initial and 1,400-Hours/1,400-Landings Subsequent Intervals(RK-1 thru RK-23 without Kit 128-8001 installed) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .606Q. 7,000-Landings Initial and 200-Landings Subsequent Intervals (RK-1 thru RK-352). . . . . . . . . . . . . . . . .606R. 7,200-Hour Initial and 2,400-Hour Subsequent Intervals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .607S. 7,400-Hours/5,000-Landings Initial and 1,400-Hours/1,400-Landings Subsequent Intervals(RK-1 thru RK-23 with Kit 128-8001 installed; RK-24 and After) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .607T. 9,800-Hour Intervals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .607U. 12,200-Hour Intervals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .608V. 12,200-Hour Initial and 3,600-Hour Subsequent Intervals . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .608

05-CONTENTSJan 01/12 A2


SUBJECT PAGE

CHAPTER 05 - TIME LIMITS/MAINTENANCE CHECKSTABLE OF CONTENTS (Continued)

W. Tire Change . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 608

05-20-02

Scheduled IFA-A Inspections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 601Pilot's Compartment. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 601Cabin Section. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 603Forward Fuselage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 604Midfuselage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 606Left-Hand Wing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 607Right-Hand Wing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 608Landing Gear and Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 609Aft Fuselage. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 611Vertical Stabilizer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 612Horizontal Stabilizer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 613Left-Hand Power Plant, Pylon and Nacelle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 614Right-Hand Power Plant, Pylon and Nacelle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 616Left-Hand Thrust Reverser . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 618Right-Hand Thrust Reverser . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 620Engine Ground Run and Operational Checks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 622

05-20-03

Scheduled IFA-B Inspections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 601Pilot's Compartment. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 601Cabin Section. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 604Forward Fuselage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 606Midfuselage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 607Left-Hand Wing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 608Right-Hand Wing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 610Landing Gear and Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 612Aft Fuselage. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 617Vertical Stabilizer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 620Horizontal Stabilizer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 622Left-Hand Power Plant, Pylon and Nacelle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 623Right-Hand Power Plant, Pylon and Nacelle . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 624Engine Ground Run and Operational Checks . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 625


SUBJECT PAGE

CHAPTER 05 - TIME LIMITS/MAINTENANCE CHECKS

TABLE OF CONTENTS (Continued)

Jan 01/12 A2 05-CONTENTS

05-20-04

Scheduled IFA-C Inspections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .601Pilot's Compartment . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .601Cabin Section . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .604Forward Fuselage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .608Midfuselage. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .609Left-Hand Wing . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .611Right-Hand Wing. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .613Landing Gear and Brakes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .615Aft Fuselage . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .617Vertical Stabilizer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .622Horizontal Stabilizer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .623Engine Ground Run and Operational Checks. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .624

05-20-05

Scheduled IFA-D Inspections . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .601

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600600600

SCHEDULED MAINTENANCE CHECKS

GENERAL INFORMATION

Beginning January 2009, Hawker Beechcraft Corporation (HBC) introduced an Airplane Inspection Program for theModel 400A tailored for Increased Flight Activity (IFA). This program is published as a supplement to the Model 400/400A Maintenance Manual and was developed to support owner/operators who fly their airplane(s) 400 hours ormore annually. If the owner/operator meets or exceeds this flight hour utilization, they may continue to use theexisting 200 hour Recommended Inspection Program or they may elect to transition to the new IFA InspectionProgram. Owner/operators who fly 300+ hours or more annually may utilize this program but may not experiencethe maximum operational benefits of the program. Once established on this program, owner/operators mayencounter reduced annual utilization due to airplane major modification, refurbishment or directed operationalreduction. Since this type of low flying activity is usually temporary, it is not necessary to remove the airplane fromthe program.

The IFA Program supplement is compiled to assist the owner/operator and technician with inspecting the airplanebased on this increased activity. Additionally, information is provided to assist the owner/operator with transitioningfrom the existing 200 hour Recommended Inspection Program to the new IFA Inspection Program.

Airplane maintenance records must be documented to identify the owner/operator’s current inspection program. Foradditional guidance, refer to FAR 91.409(f).

Owner/operators who conduct flight operations under 14 CFR Part 91 should refer to Subpart E for additionalguidance and responsibilities regarding maintenance, preventive maintenance and alterations.

Fractional owners and fractional ownership program managers who conduct flight operations under 14 CFR Part 91should refer to Subpart K for additional guidance and responsibilities regarding aircraft maintenance/inspectionprograms.

Owner/operators who conduct flight operations under 14 CFR Part 135 should refer to Subpart J for additionalguidance and responsibilities regarding maintenance, preventive maintenance and alterations.

NOTE: For the purposes of maintenance and inspection tracking, flight hours are defined as the time the airplane’s wheels lift off of the runway until the time the airplane’s wheels touch down on the runway.

INCREASED FLIGHT ACTIVITY (IFA) INSPECTION PROGRAM

The owner/operator is primarily responsible for maintaining the airplane in an airworthy condition, includingcompliance with all applicable Airworthiness Directives as specified in 14 CFR 39. It is further the responsibility ofthe owner/operator to ensure that the airplane is inspected in conformity with the requirements of 14 CFR Part 21,Part 43 and Part 91.

HBC has prepared this inspection guide to assist the owner/operator in meeting the foregoing responsibilities. Thisinspection guide is not intended to be all-inclusive, for no such guide can replace the good judgement of acertificated airframe and power plant mechanic in the performance of his duties. As the one primarily responsiblefor the airworthiness of the airplane, owner/operators should select only qualified personnel to inspect and maintainthe airplane.

While this guide may be used as an outline, detailed information on the many systems and components in theairplane will be found in the various chapters of the maintenance manual and the pertinent supplier publications. Itis also necessary that reference be made the applicable maintenance manuals, HBC Service Bulletins, applicableFAA regulations and publications, supplier’s bulletins and other requirements. It is the responsibility of the airframeand power plant mechanic inspecting or maintaining the airplane to have access to the previously noted documentsand this inspection guide.

05-20-0002Jan 01/12 A2


The time intervals for the recommended inspections and maintenance checks are based on usage under normalenvironmental conditions. Airplanes operated in adverse environmental conditions (desert, tropical, coastal,volcanic and etc.) may require inspection and/or maintenance at more frequent intervals. When operating in adverseenvironmental conditions, accomplish the inspection and/or maintenance detailed within this chapter at intervalsbased on contingencies of field experience by the owner/operators.

HBC’s IFA Inspection Program consists of, but is not limited to, inspection items listed in this inspection guide,applicable Airworthiness Directives (AD) issued against the airframe or any equipment installed therein, conformityto the Type Certificate Data Sheet (TCDS) and all applicable Airworthiness Limitations listed in the Model 400/400AAirworthiness Limitations Manual, Chapter 04-00-02.

The Model 400A IFA Inspection Program is divided into five separate ATA subchapters.

• Chapter 05-20-01 - Scheduled Special Inspections

• Chapter 05-20-02 - Scheduled IFA-A Inspections

• Chapter 05-20-03 - Scheduled IFA-B Inspections

• Chapter 05-20-04 - Scheduled IFA-C Inspections

• Chapter 05-20-05 - Scheduled IFA-D Inspections

NOTE: There are maintenance and inspection tasks required by the Federal Aviation Administration (FAA). These tasks are identified in the Model 400/400A Airworthiness Limitations Manual, Chapter 04-00-02, and should be monitored in addition to the SCHEDULED INSPECTION. Review the Airworthiness Limitation Manual tasks prior to commencing any SCHEDULED INSPECTION.

There are tasks which require more or less frequent inspection than those identified in the SCHEDULED INSPECTION. These tasks are identified in Chapter 05-20-01 - as SCHEDULED SPECIAL INSPECTIONS and should be monitored in addition to the SCHEDULED INSPECTION. Review SCHEDULED SPECIAL INSPECTION tasks prior to commencing any SCHEDULED INSPECTION.

In addition to the inspections prescribed by this IFA Inspection Program, each static pressure system, each altimeter instrument, and each automatic pressure altitude reporting system MUST be tested and inspected at 24-month intervals in compliance with the requirements specified in 14 CFR 91.411 and 91.413 or the applicable regulatory requirement.

SCHEDULED INSPECTION CORE INTERVALS

NOTE: The 12 month calendar interval is applicable to the IFA-A inspection only. The IFA-B, IFA-C and IFA-D inspection requirements do not have calendar intervals.

• IFA-A-Inspection should be completed at the first 400 flight hours or 12 months of service, whichever occurs first and should be completed every 400 flight hours or 12 months thereafter.

• IFA-B-Inspection should be completed at the first 800 flight hours of service and should be completed every 800 flight hours thereafter.

• IFA-C-Inspection will be completed at the first 1600 flight hours of service and should be completed every 1600 flight hours thereafter.

• IFA-D-Inspection will be completed at the first 6400 flight hours of service and should be completed every 3200 flight hours thereafter.

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SCHEDULED INSPECTION core intervals based on calendar time are due no later than the last day of the monthin which the inspection comes due. SCHEDULED INSPECTION core intervals based on flight hours may beexceeded by no more than 40 flight hours. This exceedance is allowed to assist owner/operators with coordinatingoperation and inspection schedules. In no instance should an airplane fly more than 440 flight hours betweenSCHEDULED INSPECTIONS. Any flight hour exceedance used beyond the inspection core interval(s) must besubtracted when computing the next repetitive inspection(s).

Example 1:

• An owner/operator’s airplane is due an IFA-A, IFA-B inspection at 800 flight hours. The IFA-A inspection has a calendar due date of 30 July 2008. The IFA-A, IFA-B inspection was accomplished at 840 flight hours on 18 July 2008.

• The next IFA-A inspection is due at 1200 flight hours (840 hours plus 400 hours, minus 40 hours exceedance = 1200 hours) or 30 July 2009, whichever occurs first.

• The next IFA-B inspection is due at 1600 flight hours (840 hours plus 800 hours, minus 40 hours exceedance = 1600 hours).

Owner/operators who wish to perform an inspection earlier than the inspection core interval(s) may do so withoutHBC concurrence. In such cases, compute the next repetitive inspection(s) due by adding the applicable coreinspection interval to the time the inspection(s) were accomplished.

Example 2:

• An owner/operator’s airplane is due an IFA-A, IFA-B inspection at 800 flight hours. The IFA-A inspection has a calendar due date of 30 July 2008. Due to mission scheduling, the owner/operators elects to perform the IFA-A, IFA-B inspection on 15 May 2008 at 680 hours.

• The next IFA-A inspection is due at 1080 flight hours (680 hours plus 400 hours = 1080 hours) or 30 May 2009, whichever occurs first.

• The next IFA-B inspection is due at 1480 flight hours (680 hours plus 800 hours = 1480 hours).

Chart 601 illustrates the SCHEDULED INSPECTION core intervals in a table format. This chart represents the IFAInspection Program based on a zero time airframe. Due to variations in operational and maintenance scheduling,HBC understands that in service airplanes may have a SCHEDULED INSPECTION accomplished or due at timesother than those indicated in Chart 601. In these cases, it is important that the owner/operator remain within theapplicable core inspection intervals and limitations listed above.

05-20-00Page 604Jan 01/12 A2


RECOMMENDED INSPECTION PROGRAM TRANSITION

Transition from the current 200 hour Recommended Inspection Program to the IFA Inspection Program is theresponsibility of the owner/operator of the airplane. The owner/operator and their elected maintenance facilityshould carefully read and understand the requirements in the IFA Inspection Program before changing inspectionprograms. A transition worksheet (Table 601) has been provided as part of the IFA Inspection Program to assist inrecalculating inspection targets.

SCHEDULED INSPECTIONS

a. Review the airplane’s maintenance records and determine the last compliance date/time of each Scheduled Inspection.

b. Record this information in the applicable blocks on the transition worksheet. See Example 3.

c. Using these figures, recalculate the next inspection(s) due using the inspection core intervals and limitations listed in the IFA Inspection Program.

Chart 601Scheduled Inspections

HOUR INTERVAL IFA-A IFA-B IFA-C IFA-D HOUR INTERVAL IFA-A IFA-B IFA-C IFA-D

400 or 12 months X 6,800 X

800 X X 7,200 X X

1,200 X 7,600 X

1,600 X X X 8,000 X X X

2,000 X 8,400 X

2,400 X X 8,800 X X

2,800 X 9,200 X

3,200 X X X 9,600 X X X X

3,600 X 10,000 X

4,000 X X 10,400 X X

4,400 X 10,800 X

4,800 X X X 11,200 X X X

5,200 X 11,600 X

5,600 X X 12,000 X X

6,000 X 12,400 X

6,400 X X X X 12, 800 X X X X

A2 Jan 01/1205-20-00


Example 3:

• RK-126 has 1820 hours Airframe Total Time. The owner/operator completed an A & B Inspection on 11/18/2008 at 1790 hours Airframe Total Time. The C Inspection was completed on 12/02/2007 at 1408 hours Airframe Total Time. The D Inspection interval has not yet been reached. Using this information from the maintenance records, recalculate the next inspection(s) due using the inspection core intervals in the IFA Inspection Program.

SCHEDULED SPECIAL INSPECTIONS

NOTE: New tasks have been added to the SCHEDULED SPECIAL INSPECTION. Additionally, some previous inspections and inspection core intervals have been re-identified. Carefully review Chapter 05-20-01.

a. Review the airplane’s maintenance records and determine the last compliance date/time of each Scheduled Special Inspections.

b. Record this information in the applicable blocks on the transition worksheet. See Example 4.

c. Using these figures, recalculate the next inspection(s) due using the inspection core intervals and limitations listed in the IFA Inspection Program, Chapter 05-20-01.

SCHEDULED SPECIAL INSPECTION core intervals based on calendar time are due no later than the last day ofthe month in which the inspection comes due. SCHEDULED SPECIAL INSPECTION core intervals based on flighthours may be exceeded by no more than 40 flight hours. Scheduled Special Inspection core intervals based onlanding /cycle count may be exceeded by no more than 30 landings/cycles. This exceedance is allowed to assistowner/operators with coordinating operation and inspection schedules. Any flight hour exceedance used beyond theinspection core interval(s) must be subtracted when computing the next repetitive inspection(s).

Example 3 Table

SCHEDULED INSPECTIONSDATE C/W

HOURS C/W INTERVAL

NEXT DUE

DATE

NEXT DUE

HOURS

IFA-A Inspection 11/18/2008

1790 400 Hours or

12 months

11/30/2009

2190

IFA-B Inspection 11/18/2008

1790 800 Hours N/A 2590

IFA-C Inspection 12/02/2007

1408 1600 Hours N/A 3008

IFA-D Inspection 6400 Hours Initial/

3200 Hours Subsequent

05-20-00Page 606Jan 01/12 A2


Example 4:

For illustration purposes, use the same airplane status as identified in Example 3. Additionally, we consider theairplane has not been modified with Kit 128-9008 (JT15D-5R Conversion). Also, we will calculate the new due date/time for items replaced during the last inspection which include: Main Battery, Wing Flap Cables and Cabin PortableFire Bottle. During the last inspection, all one year inspection items were accomplished as well.

Example 4 Table

SCHEDULED SPECIAL INSPECTIONSDATE C/W

HOURS C/W INTERVAL

NEXT DUE

DATE

NEXT DUE

HOURS

200 Hour Interval

Elevator Heater Horn Inspection 11/18/2008

1790 200 Hours N/A 1990

Lubrication Schedule - Main Landing Gear (MLG)

11/18/2008

1790 200 Hours N/A 1990

Lubrication Schedule - Nose Landing Gear (NLG)

11/18/2008

1790 200 Hours N/A 1990

Lubrication Schedule - MLG & NLG Doors 11/18/2008

1790 200 Hours N/A 1990

Thrust Reverser Lubrication 11/18/2008

1790 200 Hours N/A 1990

Lubrication Schedule - Fuel Caps 11/18/2008

1790 200 Hours N/A 1990

Lubrications Schedule - Flap Assembly 11/18/2008

1790 200 Hours N/A 1990

Starter-Generator Inspection 11/18/2008

1790 200 Hours N/A 1990

Entrance Door Steps Inspection 11/18/2008

1790 200 Hours N/A 1990

Engine Igniter Plugs Inspection 11/18/2008

1790 200 Hours N/A 1990

Nacelle Mounted Fuel Filter Element Replacement (JT15D-5R Only)

N/A N/A N/A

Fuel Pump Overtemperature Indicator P/N 3071526 (JT15D-5/5R only)

N/A N/A N/A

Battery (NiCad) N/A N/A N/A

A2 Jan 01/1205-20-00


200 Flying Hours From The Airplane Build

LH & RH Flap Cables & Interconnect Cables (Cable Tension Check)

08/15/1996

202 One Time N/A N/A

LH & RH Spoiler Cables (Cable Tension Check) 08/15/1996

202 One Time N/A N/A

200-Flying Hours After Control Cable Replacement


11/18/2008

1790 200 Hours N/A 1990

LH & RH Spoiler Cables (Cable Tension Check) N/A N/A N/A N/A

Rudder Control Cables (Cable Tension Check) N/A N/A N/A N/A

Elevator Control Cables (Cable Tension Check) N/A N/A N/A N/A

Elevator Servo Cables (Cable Tension Check) N/A N/A N/A N/A

Rudder Servo Cables (Cable Tension Check) N/A N/A N/A N/A

Spoiler Servo Cables (Cable Tension Check) N/A N/A N/A N/A

600- Hours or 12-Months Initial & 200 Hour or 3 Month Subsequent

Main Battery (Capacity Check) 11/18/2008

1790 200 Hours 11/30/2009

1990

One Year Intervals

Model GA-12 Individual Flotation Device (Recertify)

11/18/2008

1790 12 Month 11/30/2009

Flight Data Recorder (Test) N/A N/A N/A N/A

Emergency Locator Transmitter (Inspection) 11/18/2008

1790 12 Month 11/30/2009

Cockpit Portable Fire Extinguisher (Weight Check & Inspection)

11/18/2008

1790 12 Month 11/30/2009

Cabin Portable Fire Extinguisher (Weight Check & Inspection)

11/18/2008

1790 12 Month 11/30/2009

N/A

Standby Power Supply Battery (Capacity Check) 11/18/2008

1790 12 Month 11/30/2009

Example 4 Table (Continued)


HOURS C/W INTERVAL

NEXT DUE

DATE

NEXT DUE

HOURS

05-20-00Page 608Jan 01/12 A2


SERVICE INFORMATION DOCUMENTS

HBC issues several types of service information documents for the benefit of owner/operators. These serviceinformation documents may contain information regarding safety, operation, inspection, maintenance, modificationor general information. The service information documents used by Hawker Beechcraft Corporation, and theirintended purpose, are listed below:

SERVICE BULLETINS

A MANDATORY Service Bulletin (Red Border) contains information pertaining to inspections, repairs, procedures,limitations, or modifications to specific airplanes, engines or appliances for which Hawker Beechcraft Corporationconsiders compliance to be mandatory. Data contained in a MANDATORY Service Bulletin is FAA approved andmay change the airplane’s Type Design.

A RECOMMENDED or OPTIONAL Service Bulletin (no border) contains information pertaining to changes,modifications, improvements or inspections which may benefit the owner/operator. Hawker Beechcraft Corporationstrongly encourages compliance with RECOMMENDED Service Bulletins and owner/operators should give thisdocument a high degree of attention. An OPTIONAL Service Bulletin may be implemented at the owner/operatorsdiscretion. Data contained in a RECOMMENDED and OPTIONAL Service Bulletin is FAA approved and maychange the airplane’s Type Design.

COMMUNIQUE

A SAFETY COMMUNIQUE contains information on an unsafe condition (whether resulting from design,manufacturing, maintenance or pilotage) which requires expeditious transmittal. A SAFETY COMMUNIQUE doesnot authorize change of the airplane’s Type Design.

A MODEL SERIES COMMUNIQUE contains general information of interest to owner/operators and companyAuthorized Service Centers (ASC) related to a specific product model series. Most often, this document is used toshare information related to general practices involving inspection, maintenance and/or operation of the specificproduct. The MODEL SERIES COMMUNIQUE may announce upcoming or newly developed product improvementsor identify part number changes due to supersedure or obsolescence in advance of routine maintenance manual orparts catalog revision. Information presented in MODEL SERIES COMMUNIQUES is considered companyacceptable. The MODEL SERIES COMMUNIQUE does not authorize change to the airplane’s Type Design.

AHRS Power Supply Battery 11/18/2008

1790 12 Month 11/30/2009

Twelve Year Intervals

Cockpit Fire Extinguisher (Hydrostatic Inspect) 02/12/2002

983 12 Year 02/28/2014

N/A

Cabin Fire Extinguisher (Hydrostatic Inspect) 11/18/2008

1790 12 Year 11/30/2020

N/A

Example 4 Table (Continued)


HOURS C/W INTERVAL

NEXT DUE

DATE

NEXT DUE

HOURS

A2 Jan 01/1205-20-00


FIELD SERVICE KIT

A FIELD SERVICE KIT contains approved Type Design data and/or parts assembled to support the previouslyidentified service information documents or it may act as a stand alone document. Data contained in a FIELDSERVICE KITS is FAA approved and may change the airplane’s Type Design. Each FIELD SERVICE KIT isassigned a serial number which should be documented into the airplane maintenance records upon kit completion.

INSPECTION REQUIREMENTS

WARNING: When an airplane has experienced abnormal landing gear procedures of any type, as a safety precaution, place the airplane on jacks prior to performing any inspection or maintenance. Ensure that all three landing gears are down and locked prior to removing the airplane from jacks.

CAUTION: Jacking of an airplane for the purpose of landing gear operation, inspection, servicing or maintenance should be accomplished within an enclosed building or hangar. In the interest of safety, should it become necessary to jack the airplane in the open, wind velocity in any direction and terrain variations must be compensated for prior to jacking the airplane.

NOTE: For U.S. registered airplanes, standard airworthiness certificates remain valid as long as the aircraft meets its approved type design, is in a condition for safe flight and maintenance, preventative maintenance, and alterations are performed in accordance with 14 CFR Parts 21, 43, and 91. Refer to 14 CFR Part 21.181 for more detail.

Information in this section provides specific instructions for the scheduled inspection of the airplane and/orcomponents, which should be accomplished according to the specified intervals in Chapter 05-20-01, 05-20-02, 05-20-03, 05-20-04 and 05-20-05.

Airplane structure and/or components should be sufficiently clean to enable an effective inspection to be performed.

Inspections should make sure systems and/or components are free from any defects likely to affect airworthiness.

Inspections should be performed to a degree sufficient to make sure systems and/or components will remainserviceable until the next applicable inspection is repeated.

Inspections should comply with the minimum standards identified in the STANDARD TERMS and INSPECTIONCRITERIA section below.

Ascertain that all placards and markings are in place and legible, especially those listed in the limitations sectionsof the Airplane Flight Manual (AFM) and the Pilot’s Operating Manual (POM). Replace any placards that have beeninadvertently defaced or removed.

WARNING: When doing any of the inspections/checks contained in this maintenance schedule, obey all of the warnings and cautions stated in the maintenance manual associated with the system or component under inspection/check.

NOTE: Refer to Chapter 06-50-00 for the location of panels and doors needed to gain access to the inspection areas.

Access requirements quoted are minimum requirements. Further dismantling of an item, group or assembly may beconsidered necessary by a licensed airframe and power plant mechanic in order to assure airworthiness.

Due to different equipment fits between airplanes and in order to achieve satisfactory exposure of the area/item tobe inspected, it may be necessary to displace/remove other items, (e.g. electrical cables, tubes, ducts, fittings etc.)which are not stated in the inspection schedule.

05-20-00Page 610Jan 01/12 A2


STANDARD TERMS

WARNING: When doing any of the inspections/checks contained in this maintenance schedule, obey all of the warnings and cautions stated in the maintenance manual for the system or component under inspection/check.

A series of standard terms that are used throughout this inspection program are listed below to indicate theinspection requirements. Their interpretations are as follows:

a. Area Inspection - A visual inspection of a specified item, assembly or installation in a noted area of the airplane relating to an inspection interval and access quoted. Area inspections can be specified as general (Inspect) or detailed.

b. Condition - The visual appearance of an item, assembly or installation which indicates proper installation, presence of all fasteners and hardware (including safeties), security of electrical and bonding connections, as applicable, and absence of leakage or material damage (i.e., cracks, loose fasteners, corrosion, dents, chaf, distortion).

c. Inspect - A general visual inspection (using adequate lighting and viewed at no more than arms length away) to survey the condition of an item, assembly or installation.

d. Detail Inspect - An intensive visual inspection (using adequate lighting and necessary inspections aids such as inspection mirrors, magnification devices, borescopes, HBC approved NDT technique, etc...) to survey the condition of an item, assembly or installation. Removal of the item, assembly or installation may not be necessary if complete visual examination is possible using one or more inspection aids. Surface cleaning and additional access procedures may be required.

e. Check - Make a comparison of a measurement of time, pressure, temperature, resistance, dimension or quantity with a given value for that measurement.

f. Bench Check - This requires the component to be removed from the airplane and checked in accordance with the data contained in the relevant HBC or Supplier Component Maintenance Manual.

g. Functional Test - Make sure, by use of test equipment if necessary, that a complete system functions correctly in accordance with a published functional test procedure.

h. Operational Test - Make sure, without the use of test equipment, that a component within a system OR part of a system operates correctly in accordance with a published functional test procedure.

INSPECTION CRITERIA

a. Metal parts: e.g. applicable to all metal parts, bodies or casings of units in systems and in electrical, instrument and radio installations, metal pipes, ducting, tubes, rods, levers.

1. Inspect for: Cleanliness, external signs of damage, leaks, overheating or discharge. Fluid ingress. Obstruction of drainage or vent holes or overflow pipe orifices. Correct seating and sealing of fairings and serviceability of fasteners. Security of attachment, fasteners, connections, locking and bonding.

2. Freedom from: Distortion, dents, scores, chafing, pulled or missing fasteners, rivets, bolts, screws. Signs of cracks and wear. Separation of bond. Failure of welds and spots welds. Deterioration of protective treatment, and signs of corrosion.

b. Rubber, Fabric, Fiber Glass and Plastic Parts: e.g. coverings, ducting, flexible pipes, flexible mountings, seals, insulation of electrical cables, heater muffs, windows etc.

A2 Jan 01/1205-20-00


1. Inspect for: Cleanliness, cracks, cuts, chafing, kinking, twisting, crushing, contraction - sufficient free length, deterioration, crazing, loss of flexibility (other than fabric covered component), overheating and fluid soakage. Security of attachment (supports, packing and electrical bonding correctly positioned, serviceable and secure) connections and locking.

c. Electrical Wiring, wiring harness, connectors, clamps, backshell, and bonding straps:

1. Inspect for: Cuts or chafing in the wire insulation or conductor; Kinked, twisted, crushed or poorly routed wire strands or wire harness assemblies; Loss of flexibility, overheating or fluid soakage. Security of attachment (supports, clamps, electrical bonding correctly positioned, serviceable and secure connections).

d. Flight control system components (Primary and secondary control systems):

1. Inspect for: Correct alignment, freedom of movement, no interference - no fouling. Signs of bowing or distortion, wear, chafing, scoring or gouging. Fraying. Kinking. Signs of wear. Flattening. Cracks. Loose rivets. Deterioration of protective treatment and signs of corrosion. Electrical bonding straps correctly positioned, undamaged and secure. Attachments, end connections and locking devices secure.

NOTE: Free movement should be established at extreme ranges of travel with full trim applied.

Full travel of the rudder circuit should be confirmed with the pedals at the full forward and full aft adjustment positions.

e. Electrical Motors, Alternators, Generators and Actuators:

1. Inspect for: Cleanliness, obvious damage, signs of overheating, corrosion and security of attachments and connections. If protective covers are required to be removed: cleanliness, scoring, pitting, brush wear and freedom of movement in the brush holders, correct brush seating and armature condition, adequate spring tension. Overheating or arching. Fluid ingress.

f. Relays, Solenoids and Contactors:

1. Inspect for: Cleanliness, obvious damage, signs of overheating or

2. arching, corrosion and security of attachments and connections. If protective covers are required to be removed: cleanliness, pitting or burning of contacts, signs of overheating or arching and security of contacts exposed.

g. Markings, notices, frequency charts, compass corrector cards, warning and caution labels, placards:

1. Inspect for: Proper placard information, legibility and security of attachment.

NOTE: Any other inspection or work requirement not covered by the above standards is specifically written into the attachment.

h. Structural Inspection - e.g. lap joints, butt straps, stringers, frames, bulkheads, ribs, longerons and skins.

1. Inspect for:

a) Lack of adhesion of the paint or sealant. (This could indicate the presence of surface corrosion under the paint film or sealant).

b) Bubbles or eruption of the paint film or sealant. (This condition could indicate local pockets of corrosion and it is important to ascertain, beyond reasonable doubt, that any bubble or eruption found is a build up of paint or sealant and not a build up of corrosion product. If any doubt exists the bubble or eruption should be broken, the area cleaned up and, if satisfactory, the treatment restored).

05-20-00Page 612Jan 01/12 A2


c) Signs of corrosion on the edge of any member where it joins the skin. (If corrosion is found, the suspect are of the joint must be cleaned of all paint. If corrosion is confirmed and it penetrates between the faying surfaces of the joint, the affected area must be visually examined by removing bolts or rivets to check the extent of corrosion and to assist in repair).

d) Any areas exhibiting signs of possible cracking or corrosion should be stripped of paint and inspected further using fluorescent penetrant.

ADDITIONAL REQUIREMENTS INTRODUCED BY REVISION ACTION

Unless otherwise directed by applicable civil aviation regulatory notification or HBC Service Bulletin, additionalinspection requirement(s) introduced into the IFA Inspection Program by publication revision action should beaccomplished at the next SCHEDULED INSPECTION.

For example, if the IFA Inspection Program were revised and the revision introduced new SCHEDULEDINSPECTION requirement(s) to the IFA-B inspection, then the new requirement(s) would need to be accomplishedat the first IFA-B inspection following release of the revision.

Additional SCHEDULED SPECIAL INSPECTION requirements introduced into the IFA Inspection Program bypublication revision action should be accomplished at the calendar/flight hour interval specified in the revision. If theairplane has already exceeded the specified calendar/flight hour interval prior to the release of the revision, theadditional inspection requirement(s) should be accomplished at the next SCHEDULED INSPECTION.

For example, if the IFA Inspection Program SCHEDULED SPECIAL INSPECTION was revised and introduced newlanding gear inspection requirement(s) at 7000 landings, then the new inspection requirement(s) would need to beaccomplished when the airplane reached 7000 landing. If an airplane has more than 7000 landings at the time ofthe release of the revision, then the new 7000 landing requirement(s) would need to be accomplished at the nextSCHEDULED INSPECTION.

A2 Jan 01/1205-20-00


Table 601Transition Conversion


HOURS C/W INTERVAL

NEXT DUE

DATE

NEXT DUE

HOURS

IFA-A Inspection 400 Hours or

12 months

IFA-B Inspection 800 Hours

IFA-C Inspection 1600 Hours

IFA-D Inspection 6400 Hours Initial/

3200 Hours Subsequent


HOURS C/W INTERVAL

NEXT DUE

DATE

NEXT DUE

HOURS

200 Hour Interval

Elevator Heater Horn Inspection

Lubrication Schedule - Main Landing Gear (MLG)

Lubrication Schedule - Nose Landing Gear (NLG)

Lubrication Schedule - MLG & NLG Doors

Thrust Reverser Lubrication

Lubrication Schedule - Fuel Caps

Lubrications Schedule - Flap Assembly

Starter-Generator Inspection

Entrance Door Steps Inspection

Engine Igniter Plugs Inspection

Nacelle Mounted Fuel Filter Element Replacement (JT15D-5R Only)

Fuel Pump Overtemperature Indicator P/N 3071526 (JT15D-5/5R only)

Battery (NiCad)

05-20-00Page 614Jan 01/12 A2


200 Flying Hours From The Airplane Build


LH & RH Spoiler Cables (Cable Tension Check)

200-Flying Hours After Control Cable Replacement


LH & RH Spoiler Cables (Cable Tension Check)

Rudder Control Cables (Cable Tension Check)

Elevator Control Cables (Cable Tension Check)

Elevator Servo Cables (Cable Tension Check)

Rudder Servo Cables (Cable Tension Check)

Spoiler Servo Cables (Cable Tension Check)

600- Hours or 12-Months Initial & 200 Hour or 3 Month Subsequent

Main Battery (Capacity Check)

One Year Intervals

Model GA-12 Individual Flotation Device (Recertify)

Flight Data Recorder (Test)

Emergency Locator Transmitter (Inspection)

Cockpit Portable Fire Extinguisher (Weight Check & Inspection)

Cabin Portable Fire Extinguisher (Weight Check & Inspection)

Standby Power Supply Battery (Capacity Check)

AHRS Power Supply Battery

Table 601Transition Conversion (Continued)


HOURS C/W INTERVAL

NEXT DUE

DATE

NEXT DUE

HOURS

A2 Jan 01/1205-20-00


Two Year Intervals

Altimeter, ATC Transponder & Air Data Computer (Recertify)

Mach Overspeed Warning System (Functional Test)

Cockpit Voice Recorder Underwater Locator Beacon (RK-36 and After) (Functional Test)

Air Data System Inspection (RVSM Airplanes Only)

Flight Data Recorder Underwater Locator Beacon (RK-36 and After) (Functional Test)

Four Year Intervals

Oxygen Valve - Passenger Oxygen Control Valve (O-Ring Replacement & Lube)

Five Year Intervals

Model XF-35 Life Preservers (P/N P01074-113)

Six Year Intervals

Underwater Locator Beacon (RK-36 and After) (Battery Replacement)

Crew Oxygen Mask BE Aerospace Sweep-On 2000 (Overhaul)

Eight Year Intervals

Passenger Oxygen Mask BE Aerospace P/N 174080 (Overhaul/Replace)

Ten Year Intervals

SCV-37 Flotation Vest (P/N HS3701C) (Recertify)

Model XF-35 Life Preserver (P/N P01074-201)



HOURS C/W INTERVAL

NEXT DUE

DATE

NEXT DUE

HOURS

05-20-00Page 616Jan 01/12 A2


Protective Breathing Equipment (PBE) AVOX Systems P/N 802300-14 (Replace)

Ten Year Initial & Five Year Subsequent

Wing-to-Fuselage Attach Bolt (Inspection)

Twelve Year Intervals

Cockpit Fire Extinguisher (Hydrostatic Inspect)

Cabin Fire Extinguisher (Hydrostatic Inspect)

3,000-Air Conditioner Operating Hours

Drive Motor (Overhaul)

7,000-Landings Initial & 200-Landings Subsequent Intervals (RK-1 thru RK-352)

Main Landing Gear Fitting Assembly & Mid Fuselage Main Landing Gear Uplock Fitting (Inspection)

9800-Hour Intervals

Airborne Flight Information System (AFIS) Wiring (Inspection)

12,200-Hour Intervals

Collins Servo Mount Slip Clutch (Test)

12,200 Hour Initial & 3,600 Hour Subsequent

Airborne Flight Information System (AFIS) Antenna Feed-Through (Inspection)



HOURS C/W INTERVAL

NEXT DUE

DATE

NEXT DUE

HOURS

A2 Jan 01/1205-20-00


REPLACEMENT PARTS

Use only parts obtained from sources approved by Hawker Beechcraft Corporation, in connection with themaintenance and repair of Hawker Beechcraft Corporation airplanes.

Genuine Hawker Beechcraft Corporation parts are produced and inspected under rigorous procedures to insureairworthiness and suitability for use in Hawker Beechcraft Corporation airplane applications. Parts purchased fromsources other than those approved by Hawker Beechcraft Corporation, even though outwardly identical inappearance, may not have the required tests and inspections performed, may be different in fabrication techniquesand materials, and may be dangerous when installed in an airplane.

Salvaged airplanes parts, reworked parts obtained from sources not approved by the HAwker BeechcraftCorporation or parts, components or structural assemblies, the service history of which is unknown or cannot beauthenticated, may have been subjected to unacceptable stresses or temperatures or have other hidden damage,not discernible through routine visual or usual nondestructive testing techniques. This may render the part,component or structural assembly, even though originally manufactured by the Hawker Beechcraft Corporation,unsuitable and unsafe for airplane use.

Hawker Beechcraft Corporation expressly disclaims any responsibility for malfunctions, failures, damage or injurycaused by use of parts not approved by the Hawker Beechcraft Corporation.

Any maintenance requiring the disconnection and reconnection of flight control cables, plumbing, electricalconnectors or wiring requires identification of each side of the component being disconnected to facilitate correctreassembly. At or prior to disassembly, components should be color coded, tagged or properly identified in a awaythat will be obvious how to correctly reconnect the components. After reconnection of any component, remove allidentification tags. Check all associated systems for correct function prior to returning the airplane to service.

Tire Change

Nose Wheel (Inspection/Lube)

Main Wheels (Inspection/Lube)



HOURS C/W INTERVAL

NEXT DUE

DATE

NEXT DUE

HOURS

A2 Jan 01/1205-20-01


60060060005-20-01

SCHEDULED IFA-SPECIAL INSPECTIONS

SCHEDULED IFA-SPECIAL INSPECTIONS

TASKCODE DATE MECH INSP

A. 200-HOUR INTERVALS

H300011 H300012

1. Perform ELEVATOR HORN INSPECTION/CHECK (Ref. Chapter 30-12-00).

H120035 H120036

2. Perform LUBRICATION SCHEDULE - MAIN LANDING GEAR (Ref. Chapter 12-20-00).

H120041 3. Perform LUBRICATION SCHEDULE - NOSE LANDING GEAR (Ref. Chapter 12-20-00).

H120042 4. Perform LUBRICATION SCHEDULE - MAIN LANDING GEAR AND NOSE LANDING GEAR DOORS (Ref. Chapter 12-20-00).

H120037 H120038

5. Perform THRUST REVERSER LUBRICATION - Guide rod cleaning and lubrication (Ref. Chapter 78-30-00).

H120043 H120044

6. Perform LUBRICATION SCHEDULE - FUEL CAPS (Ref. Chapter 12-20-00).

H120039 H120040

7. Perform LUBRICATION SCHEDULE - FLAP ASSEMBLY (Ref. Chapter 12-20-00).

H240019 H240020

8. STARTER-GENERATOR (Generator removal is not necessary.) (Ref. Chapter 80-10-00).

a. Inspect for security and visible damage.

b. Inspect brushes for wear.

c. Inspect electrical connections for security, wear, deterioration and damage.

H520019 9. ENTRANCE DOOR STEPS

a. Visually inspect for cracks, loose or missing fasteners, any indication of structural damage and proper operation.

b. Visually inspect step cable for condition.

H740003 H740004

10. ENGINE IGNITOR PLUGS - Inspect for wear and condition. Refer to Pratt & Whitney JT15D-5/-5R Maintenance Manual, Chapter 74-20-02.

05-20-01Page 602Jan 01/12 A2


A. 200-HOUR INTERVALS (Continued)

H730001 H730002

11. NACELLE MOUNTED FUEL FILTER ASSEMBLY, P/N 307618 (JT15D-5R Only) - Check filter for foreign matter. Replace filter if necessary. Refer to Pratt & Whitney JT15D-5/-5R Maintenance Manual, Chapter 73-10-13.

H730003 H730004

12. FUEL PUMP OUTLET FILTER, P/N 3059778 (JT15D-5 and JT15D-5R) - Check for foreign matter and/or distortion. Install new filter at each inspection. Refer to Pratt & Whitney JT15D-5/-5R Maintenance Manual, Chapter 73-10-02.

H730007 H730008

13. FUEL PUMP OVERTEMPERATURE INDICATOR, P/N 3071526 (JT15D-5R Only) - Inspect position of indicator. If extended, refer to Pratt & Whitney JT15D-5/-5R Maintenance Manual, Chapter 74-00-00.

H240021 14. BATTERY (Ni-Cad only) - Check electrolyte level and charge (deep cycle if necessary). Refer to Chapter 24 in the Component Maintenance Manual, P/N 128-590001-81 or subsequent.

B. 200-FLYING HOURS FROM THE AIRPLANE BUILD

H270057 H270058

1. LH and RH FLAP CABLES AND INTERCONNECT CABLES - Check cable tensions (Ref. Chapter 27-50-00).

H270059 H270060

2. LH and RH SPOILER CABLES - Check cable tension (Ref. Chapter 27-60-00).

C. 200-FLYING HOURS AFTER CONTROL CABLE REPLACEMENT

H270048 H270049

1. LH and RH FLAP CABLES AND INTERCONNECT CABLES - Check cable tensions (Ref. Chapter 27-50-00).

H270050 H270051

2. LH and RH SPOILER CABLES - Check cable tension (Ref. Chapter 27-60-00).

H270052 3. RUDDER CONTROL CABLES - Check cable tensions (Ref. Chapter 27-20-00).

H270054 4. ELEVATOR CONTROL CABLES - Check cable tensions (Ref. Chapter 27-30-00).

H270055 5. ELEVATOR SERVO CABLES - Check cable tensions (Ref. Chapter 22-13-00).

H270053 6. RUDDER SERVO CABLES - Check cable tensions (Ref. Chapter 22-13-00).

SCHEDULED IFA-SPECIAL INSPECTIONS (Continued)


A2 Jan 01/1205-20-01


C. 200-FLYING HOURS AFTER CONTROL CABLE REPLACEMENT (Continued)

H270056 7. SPOILER SERVO CABLES - Check cable tension (Ref. Chapter 22-13-00).

D. 600-HOUR OR 12-MONTHS INITIAL AND 200-HOUR OR 3-MONTH SUBSEQUENT

H243026 1. MAIN BATTERY - Perform the EMERGENCY CAPACITY TEST in accordance with battery manufacturer’s maintenance recommendations.

E. ONE-YEAR INTERVALS

H256030thru

H256040

1. INDIVIDUAL FLOATATION DEVICE (Model Number GA-12) - Recertify device once a year after being placed in service.

H313005 2. FLIGHT DATA RECORDER (if applicable) - Perform the FLIGHT DATA RECORDER (FDR) INSPECTION CHECK (Ref. Chapter 31-30-00).

H250018 3. EMERGENCY LOCATOR TRANSMITTER (If installed) - Inspect the ELT as required by 14 CFR 91.207 (d) for:

a. Proper installation.

b. Battery corrosion.

c. Operation of controls and crash sensor.

d. The presence of sufficient signal radiated from it’s antenna.

Refer to the Artex Maintenance Manual, Document Numbers 570-1015 or 570-5000 or subsequent, for the appropriate ELT model number.

H262001 4. COCKPIT PORTABLE FIRE EXTINGUISHER - Inspect weight, operating pressure and condition.

H262002 5. CABIN PORTABLE FIRE EXTINGUISHER - Inspect weight, operating pressure and condition.

H240012 6. STANDBY POWER SUPPLY BATTERY (JET Model PS835) - Perform battery capacitance test (Ref. Chapter 24-30-02 in the Component Maintenance Manual, 128-590001-81 or subsequent.



05-20-01Page 604Jan 01/12 A2


E. ONE-YEAR INTERVALS (Continued)

H240013 7. AHRS POWER SUPPLY BATTERY (JET Model PS835) - Perform battery capacitance test (Ref. Chapter 24-30-02 in the Component Maintenance Manual, 128-590001-81 or subsequent.

F. TWO-YEAR INTERVALS

H340012H340013H340014

1. ALTIMETER, ATC TRANSPONDER AND AIR DATA COMPUTER - Check per current CFR's.

H340006 2. MACH OVERSPEED WARNING SYSTEM - Perform functional test by use of pitot/static tester (Ref. AIR-SPEED AND MACH WARNING TEST, Chapter 34-12-00).

H230005 3. COCKPIT VOICE RECORDER UNDERWATER LOCATOR BEACON (RK-36 and After) - Functional test. Refer to the Dukane (Seacom Division) Technical Manual in Chapter 23 of the Component Maintenance Manual, P/N 128-590001-81 or subsequent for test procedures.

H340007 4. AIR DATA SYSTEM (RVSM Only) (RK-1 thru RK-299 that have complied with Service Bulletin No. 34-3431; RK-300 and After) - Measure step height of the Static port. Check air data system for RVSM accuracy (Ref. Chapter 34-10-01).

H313011 5. FLIGHT DATA RECORDER UNDERWATER LOCATOR BEACON (RK-36 and After) - Functional test. Refer to the Dukane (Seacom Division) Technical Manual in Chapter 23 of the Component Maintenance Manual, P/N 128-590001-81 or subsequent for test procedures.

G. FOUR-YEAR INTERVALS

H350003 1. OXYGEN VALVE - Refer to PASSENGER OXYGEN CONTROL VALVE O-RING REPLACEMENT (Ref. Chapter 35-21-00).

H. FIVE-YEAR INTERVALS

H256030.1 thru

H250040.1

1. LIFE PRESERVER (Model XF-35 - P/N P01074-113) - Recertify preserver every five years after being placed in service.



A2 Jan 01/1205-20-01


I. SIX-YEAR INTERVALS

H312020 1. UNDERWATER LOCATOR BEACON (RK-36 and After) - Replace battery. Refer to the Dukane (Seacom Division) Technical Manual in Chapter 23 of the Component Maintenance Manual, P/N 128-590001-81 or subsequent for test procedures.

H350010 2. CREW OXYGEN MASK (BE AEROSPACE, SWEEP-ON 2000) - Perform overhaul six years from date of manufacture or last overhaul.

H350013 3. OXYGEN CYLINDER REGULATOR (P/N 172400) - Overhaul during oxygen cylinder hydrostatic inspection, but no later than six years from date of manufacturer or last overhaul.

J. EIGHT-YEAR INTERVALS

H350011 1. PASSENGER OXYGEN MASK (BE AEROSPACE, P/N 174080 and 174095) - Overhaul or replace.

K. TEN-YEAR INTERVALS

H256030.2 thru

H256040.2

1. SCV-37 FLOATATION VEST (P/N HS3701C) - Recertify vest every ten years after being placed in service.

H256030.3thru

H256040.3

2. LIFE PRESERVER (Model XF-35 - P/N P01074-201) - Recertify preserver every ten years after being placed in service.

H350012 3. PROTECTIVE BREATHING EQUIPMENT (PBE) AVOX SYSTEMS (P/N 802300-14) - Replace every ten years from date of manufacture.

L. TEN-YEAR INITIAL AND FIVE-YEAR SUBSEQUENT INTERVALS

H570008 1. WING-TO-FUSELAGE ATTACH BOLTS - Detail inspect for corrosion, wear and any evidence of damage. Magnetic particle inspect for cracks (Ref. Chapter 57-40-00).

M. TWELVE-YEAR INTERVALS

H262005 1. COCKPIT FIRE EXTINGUISHER - Hydrostatically test cylinder.

H262006 2. CABIN FIRE EXTINGUISHER - Hydrostatically test cylinder.



05-20-01Page 606Jan 01/12 A2


N. 2,400-HOUR INTERVALS

H550016 1. HORIZONTAL STABILIZER INTERNAL STRUCTURE (Airplanes modified by Kit 128-6200) - Detail inspect for cracks, corrosion, missing fasteners and evidence of structural damage using either the radiographic (X-Ray) or borescope inspection procedure (Ref. Chapter 55-10-00).

O. 3,000-AIR CONDITIONING OPERATING HOURS INTERVALS

H210037 1. DRIVE MOTOR - Perform overhaul of the drive motor per the Chapter 21-00-12, Section 7.1.2 in the Component Maintenance Manual, 128-590001-81 or subsequent.

P. 4,500-HOURS/3,000-LANDINGS INITIAL AND 1,400-HOURS/1,400-LANDINGS SUBSEQUENT INTERVALS (RK-1 THRU RK-23 WITHOUT KIT 128-8001 INSTALLED)

H322113H322213

1. MAIN LANDING GEAR RETRACTION CYLINDER (P/N 45AS38515) - Perform Eddy current inspection of the retraction cylinder mounting lug for evidence of cracks in accordance with Chapter 20-80-03. Removal of the spherical bearing is not required. Refer to Figure 601.

H322013 2. NOSE LANDING GEAR RETRACTION CYLINDER (P/N 45AS39503) - Perform Eddy current inspection of the retraction cylinder mounting lug for evidence of cracks in accordance with Chapter 20-80-03. Removal of the spherical bearing is not required. Refer to Figure 602.

Q. 7,000-LANDINGS INTERVAL AND 200-LANDINGS SUBSEQUENT INTERVALS (RK-1 THRU RK-352)

H531095 1. MAIN LANDING GEAR FITTING ASSEMBLY (P/N 45A33506) INSPECTION (RK-1 THRU RK-352) - Perform a detail visual inspection and a borescope inspection. Refer to the MAIN LANDING GEAR FITTINGS - INSPECTION/CHECK, Chapter 53-40-00.

NOTE

Replacement of NAS1203 and NAS1204 bolts with HL21PB Hi-Lokbolts in the Main Landing Gear Fitting Assembly is terminating actionfor the 200 hour subsequent interval. Refer to Chapter 53-40-00,Figure 601, Detail C, Bolts A and B.



A2 Jan 01/1205-20-01


Q. 7,000-LANDINGS INTERVAL AND 200-LANDINGS SUBSEQUENT INTERVALS (RK-1 THRU RK-352) (Continued)

H531096 2. MID FUSELAGE MAIN LANDING GEAR UPLOCK FITTING (P/N 45A33480) INSPECTION (RK-1 THRU RK-604) - Perform a detail visual inspection and a borescope inspection. Refer to the MAIN LANDING GEAR FITTINGS - INSPECTION/CHECK, Chapter 53-40-00.

NOTE

Replacement of the Mid Fusealge Main Landing Gear Uplock FittingP/N 45A33480 with P/N 128-430003 is terminating action for the 200hour subsequent interval.

R. 7,200-HOUR INITIAL AND 2,400-HOURS SUBSEQUENT INTERVALS

H550015 1. HORIZONTAL STABILIZER RIB INSPECTION (P/N 45A21112-5, 45A21113-5, 45A21101-11, 45A21116-5, 45A21117-5) - Perform radiographic (X-Ray) inspection of the horizontal stabilizer rib assemblies in accordance with Chapter 55-10-00. As an alternate means of inspection, a borescope inspection may be performed in accordance with Chapter 55-10-00.

S. 7,400-HOURS/5,000-LANDINGS INITIAL AND 1,400-HOURS/1,400-LANDINGS SUBSEQUENT INTERVALS (RK-1 THRU RK-23 WITH KIT 128-8001 INSTALLED; RK-24 AND AFTER)

H322114H322214

1. MAIN LANDING GEAR RETRACTION CYLINDER (P/N 45AS38515) - Perform Eddy current inspection of the retraction cylinder mounting lug for evidence of cracks in accordance with Chapter 20-80-03. Removal of the spherical bearing is not required. Refer to Figure 601.

H322014 2. NOSE LANDING GEAR RETRACTION CYLINDER (P/N 45AS39503) - Perform Eddy current inspection of the retraction cylinder mounting lug for evidence of cracks in accordance with Chapter 20-80-03. Removal of the spherical bearing is not required. Refer to Figure 602.

T. 9,800-HOUR INTERVALS

H341176 1. AIRBORNE FLIGHT INFORMATION SYSTEM (AFIS) WIRING (RK-483 and After - Optional) - Visually inspect for signs of chafing, security and corrosion.



05-20-01Page 608Jan 01/12 A2


U. 12,200-HOUR INTERVALS

H220001 1. COLLINS SERVO MOUNT SLIP CLUTCH - Test the Collins servo mount slip clutches in the elevator, rudder and spoiler servo mounts per the Rockwell-Collins Beechjet Avionics System Manual (P/N 523-0775807) Section 5.2.2 SVO-85 ( ) Servo/SMT-85 ( )/-87 ( ) Servo Mount.

V. 12,200-HOUR INITIAL AND 3,600-HOUR SUBSEQUENT INTERVALS

H341177 1. AIRBORNE FLIGHT INFORMATION SYSTEM (AFIS) ANTENNA FUSELAGE FEED-THROUGH (FS 378.54 - lower fuselage (RK-483 and After - Optional) - Detail inspect for corrosion and wear. Using Eddy current method (with a surface probe) inspect for cracks and any indication of structural damage. Antenna removal is required (Ref. Chapter 34-59-00).

W. TIRE CHANGE- Accomplish at every tire change. Refer to the Model MU-300/400/400A Component Maintenance Manual.

H3200NO 1. NOSE WHEEL

a. Inspect wheel for cracks and damage in accordance with Chapter 32-46-12 in the Component Maintenance Manual, 128-590001-81 or subsequent.

b. Clean and inspect wheel bearings and cones, lubricate wheel bearings (Ref. Chapter 12-20-00).

c. Inspect axle, caps and spacers for corrosion and condition.

H3200LHH3200RH

2. MAIN WHEELS

a. Inspect wheel for cracks and damage in accordance with Chapter 32-40-54 or 32-40-99 in the Component Maintenance Manual, 128-590001-81 or subsequent.

b. Clean and inspect wheel bearings and cones, lubricate wheel bearings (Ref. Chapter 12-20-00).

c. Check wheel brake disc drive keys for loose and missing hardware.

d. Inspect axle, nut and spacers for corrosion and condition.

e. Perform HUBCAP INSPECTION (Ref. Chapter 32-40-00).



A2 Jan 01/1205-20-01


MLG Retraction Actuator (P/N 45AS38515)(RK-1 and After)

Figure 601

05-20-01Page 610Jan 01/12 A2


NLG Retraction Actuator (P/N 45AS39503)(RK-1 and After)

Figure 602

A2 Jan 01/1205-20-02


60060060005-20-0

SCHEDULED IFA-A INSPECTIONS

PILOT'S COMPARTMENT



A. PILOT'S COMPARTMENT

H350005 1. PILOT'S AND COPILOT'S OXYGEN SYSTEM - Perform FLIGHT CREW MASK - INSPECTION/CHECK (Ref. Chapter 35-11-00)

H350006 2. PROTECTIVE BREATHING EQUIPMENT (PBE) P/N 802300-XX (If Installed) - Inspect in accordance with AVOX SYSTEMS Instruction 89253.01 (Ref. Chapter 35 in the Component Maintenance Manual, P/N 128-590001-81 or subsequent).

H270006 3. CONTROL COLUMN (Above Floor Panels)

a. Inspect for condition and freedom of movement.

b. Inspect wire harness on forward side of the control column for damage and security.

H270047 4. CONTROL YOKE - Inspect for condition and freedom of movement.

H270001 5. RUDDER PEDALS (Above Floor Panels) - Inspect for condition and freedom of movement.

H250001 6. PILOT'S AND COPILOT'S SEATS

a. Inspect upholstery, safety belts and shoulder harness for condition and proper operation of shoulder harness inertial reels.

b. Inspect seat adjusting mechanisms for proper locking.

H250002 7. SMOKE GOGGLES - Inspect goggles and storage box for condition.

H530004 8. CENTER PEDESTAL

a. Inspect thrust levers and thrust reversers for condition and freedom of movement.

b. Inspect pedestal switches and components for condition.

H330006 9. COCKPIT ADVISORY, CAUTION AND WARNING LIGHTS - Inspect all for condition and operation.

05-20-02Page 602Jan 01/12 A2


A. PILOT'S COMPARTMENT (Continued)

H340005 10. FLIGHT INFORMATION DISPLAYS AND INSTRUMENTS

a. Inspect all for condition.

b. Check oxygen and nitrogen operating pressures.

H120001 11. Lubricate items as specified in Chapter 12.

SCHEDULED IFA-A INSPECTIONS (Continued)


A2 Jan 01/1205-20-02


CABIN SECTION



A. CABIN SECTION

H330001 1. CABIN INTERIOR LIGHTS - Inspect all for condition and operation.

2. EMERGENCY LIGHTING SYSTEM

H330007 a. (RK-1 thru RK-109, except RK-98) - Move the EMER LT switch to the TEST/ON position and ensure emergency lighting illuminates. Return EMER LT switch to the OFF position.

H330003 b. (RK-98, RK-110 and After) - Perform EMERGENCY LIGHTING SYSTEM OPERATIONAL INSPECTION (Ref. Chapter 33-51-00).

H350007 3. PORTABLE OXYGEN & MASK (If Installed) - Inspect for condition and operating pressure.

H250004 4. PASSENGER AND TOILET SEAT

a. Inspect upholstery, safety belts and shoulder harness for condition and proper operation of shoulder harness inertia reels.

b. Inspect seat adjusting mechanisms for proper locking (toilet seat exempt).

c. Inspect shoulder harness attachment post for worn or missing grommet and proper engagement with seat belt.

d. Check toilet servicing.


05-20-02Page 604Jan 01/12 A2


FORWARD FUSELAGE



A. FORWARD FUSELAGE

H340001 1. PITOT/STATIC SYSTEM

a. Drain any moisture from pitot and static plumbing drain valves.

b. Inspect static ports for obstruction.

H340010 2. PITOT TUBES

a. Perform PITOT TUBE INSPECTION (Ref. Chapter 34-12-00).

b. Perform UNPAINTED SURFACE INSPECTION (Ref. Chapter 12-20-00).

H340003 3. AOA TRANSMITTER PROBE - Inspect for cleanliness of air inlet ports (if cone-type probe), evidence of overheating or damage and freedom of probe rotation.

H530006 4. RADOME AND lightning DIVERTER STRIPS

a. Inspect for condition.

b. Inspect radome erosion boot for condition, if installed.

H530015 5. FUSELAGE SKIN AND ACCESS DOORS (Exterior inspection only, panel removal is not required) - Inspect for condition.

H350004 6. OXYGEN SYSTEM

a. (RK-156 thru RK-389 with Kit 128-5600 Installed, RK-390 and After) - Inspect oxygen service door, hinge and latch for condition and proper operation.

b. Inspect green overboard discharge disk for presence and condition.

H520003 7. LANDING LIGHT AND DOORS - Inspect door, hinge and light assembly for condition.

H560001 8. WINDSHIELD AND FLIGHT COMPARTMENT WINDOWS - Inspect for pits, scratches, crazing, delamination and proper sealing (Ref. Chapter 56-00-00).

A2 Jan 01/1205-20-02


A. FORWARD FUSELAGE (Continued)

H560002 9. WINDSHIELD EXTERNAL FRAME AND PROTECTORS

a. Inspect for condition and proper sealing.

b. Perform the UNPAINTED SURFACE INSPECTION (Ref. Chapter 12-20-00).

H300007 10. WINDSHIELD WIPERS (RK-1 thru RK-242 without Kit 128-5405 installed) - Inspect wiper arms and blades for condition.

H560004 11. WINDSHIELD SURFACE SEAL COATING (RK-1 thru RK-242 with Kit 128-5405 installed; RK-243 and After) - Inspect and if required, reapply the Surface Seal Coating in accordance with Chapter 56 in the Component Maintenance Manual, P/N 128-590001-81 or subsequent.

H230001 12. ANTENNA - Inspect antennas and fillet seal for cracks, corrosion, burns, security and evidence of damage (Ref. Figure 602).




05-20-02Page 606Jan 01/12 A2


MIDFUSELAGE



A. MIDFUSELAGE

H560005 1. PASSENGER COMPARTMENT WINDOWS - Inspect for cracks, delamination and sealant condition.

H280001 2. FUEL STORAGE AREA - Inspect for evidence of fuel leakage from underside of the fuselage.

H280002 3. FUEL SYSTEM PLUMBING AND COMPONENT MOUNTING (RK-1 thru RK-507 without Kit 128-9008 installed) (Gain access through panels 311AB and 312AB) - Inspect for condition and leakage.

H280003 4. FUEL FILTER ELEMENT (RK-1 thru RK-507 without Kit 128-9008 installed) - Replace filter and clean filter bowl (Ref. FUEL FILTER REMOVAL, Chapter 28-21-00).

H280005 5. MOTIVE-FLOW SHUTOFF VALVE, CROSSFEED VALVE, AND FUEL SHUTOFF VALVE (RK-1 thru RK-507 without Kit 128-9008 Installed) - Inspect for condition and leakage.



A2 Jan 01/1205-20-02


LEFT-HAND WING



A. LEFT-HAND WING

H570102 1. WING SKIN (Exterior inspection only, fairing removal is not required) - Inspect skin for condition.

H570107 2. WING FUEL STORAGE AND INSPECTION ACCESS PANELS (Exterior inspection only, panel removal is not required) - Inspect for condition and evidence of fuel leakage.

H570103 3. FUEL TANK FILLER RECEPTACLE

a. Inspect fuel cap, fuel cap lanyard and fuel cap adapter assembly for condition.

b. Inspect fuel cap latching mechanism for proper operation.

H570104 4. WING TIP AND LENS COVER


b. Inspect static wick for condition and evidence of lightning strike.

H330013 5. ANTI-COLLISION LIGHT ASSEMBLY - Inspect for condition.

H570106 6. WING LEADING AND TRAILING EDGE ASSEMBLIES



H270102 7. WING FLAPS SYSTEM (Flaps Extended) - (External Inspection Only) - Inspect for condition.

H270103 8. ROLL TRIM TAB, HINGE AND COUNTERBALANCE (External Inspection Only)



H270104 9. SPOILER PANELS AND HINGES - Inspect panels, hinges and bonding straps for condition.


05-20-02Page 608Jan 01/12 A2


RIGHT-HAND WING



A. RIGHT-HAND WING

H570202 1. WING SKIN (Exterior inspection only, fairing removal is not required) - Inspect skin for condition.

H570207 2. WING FUEL STORAGE AND INSPECTION ACCESS PANELS (Exterior inspection only, panel removal is not required) - Inspect for condition and evidence of fuel leakage.

H570203 3. FUEL TANK FILLER RECEPTACLE

a. Inspect fuel cap, fuel cap lanyard and fuel cap adapter assembly for condition.


H570204 4. WING TIP AND LENS COVER



H330012 5. ANTI-COLLISION LIGHT ASSEMBLY - Inspect for condition.

H570206 6. WING LEADING AND TRAILING EDGE ASSEMBLIES



H270202 7. WING FLAPS SYSTEM (Flaps Extended) - (External Inspection Only) - Inspect for condition.

H270203 8. ROLL TRIM TAB, HINGE AND COUNTERBALANCE (External Inspection Only)



H270204 9. SPOILER PANELS AND HINGES - Inspect panels, hinges and bonding straps for condition.


A2 Jan 01/1205-20-02


LANDING GEAR AND BRAKES



A. LANDING GEAR AND BRAKES

H320001 1. NOSE WHEEL AND TIRE

a. Check tire for correct inflation, wear, damage or deterioration.

b. Check wheel for condition and missing or broken wheel tie bolts and nuts.

H320002 2. NOSE LANDING GEAR STRUT ASSEMBLY - Check for proper nitrogen servicing and signs of fluid leakage (Ref. Chapter 12-10-00).

H320030 3. NOSE LANDING GEAR SHIMMY DAMPER

a. Inspect shimmy damper for condition.

b. Check shimmy damper servicing (Ref. Chapter 32-20-00).

H520004 4. NOSE LANDING GEAR DOORS

a. Inspect doors and hinges for condition.

b. Inspect the uplock hook emergency release cable and linkage for condition and routing (Ref. Figure 601, Detail A and C).

H320104 5. LEFT MAIN WHEEL


b. Check for missing or broken wheel tie bolts and nuts.

H320204 6. RIGHT MAIN WHEEL


b. Check for missing or broken wheel tie bolts and nuts.

H320105 7. LEFT BRAKE ASSEMBLY - Check brake wear indicator pin. Refer to the appropriate MAIN LANDING GEAR BRAKE WEAR LIMITS procedure (Ref. Chapter 32-40-00).

H320205 8. RIGHT BRAKE ASSEMBLY - Check brake wear indicator pin. Refer to the appropriate MAIN LANDING GEAR BRAKE WEAR LIMITS procedure (Ref. Chapter 32-40-00).

05-20-02Page 610Jan 01/12 A2


A. LANDING GEAR AND BRAKES (Continued)

H320039 9. BRAKE SYSTEM ACCUMULATOR - Check accumulator pre-charge pressure.

H320106 10. LEFT MAIN LANDING GEAR STRUT ASSEMBLY - Check for proper nitrogen servicing and signs of fluid leakage (Ref. Chapter 12-10-00).

H320206 11. RIGHT MAIN LANDING GEAR STRUT ASSEMBLY - Check for proper nitrogen servicing and signs of fluid leakage (Ref. Chapter 12-10-00).

H520105 12. LEFT MAIN LANDING GEAR DOORS



H520205 13. RIGHT MAIN LANDING GEAR DOORS



H320009 14. LANDING GEAR EXTENSION/RETRACTION SYSTEM - Perform NORMAL EMERGENCY EXTENSION RETRACTION VERIFICATION CHECK (Ref. Chapter 32-30-00). NOTE: This check is not required if the LANDING GEAR FUNCTIONAL TEST is performed.




A2 Jan 01/1205-20-02


AFT FUSELAGE



A. AFT FUSELAGE

H530021 1. FUSELAGE SKIN, ACCESS DOORS AND FAIRINGS (Exterior inspection only, panel removal is not required)


b. Inspect doors, hinges and latches for condition and proper operation.

H210003 2. ENVIRONMENTAL CONTROL UNIT (ECU) AND DUCTING - Clean or replace coalescer sock.

H290001 3. HYDRAULIC RESERVOIR - Check hydraulic fluid level.

H260002 4. FIRE EXTINGUISHER SYSTEM

a. Inspect fire extinguisher containers for proper pressure (Ref. Chapter 26-20-00, Chart 201).

b. Inspect red overboard discharge disk for presence condition.

H532001 5. TAIL CONE - Inspect tail cone and anti-collision light for condition.

H520007 6. FUEL TANK FILLER RECEPTACLE AND DOOR

a. Inspect fuel cap, fuel cap lanyard and fuel cap adapter for condition.




05-20-02Page 612Jan 01/12 A2


VERTICAL STABILIZER



A. VERTICAL STABILIZER

H550001 1. STABILIZER SKIN, LEADING EDGE AND ACCESS PANELS (Exterior inspection only, panel removal is not required) - Inspect skin for condition.

H330004 2. FORWARD RECOGNITION LIGHT ASSEMBLY - Inspect for condition.

H270251 3. VERTICAL STABILIZER TIP FAIRINGS



c. Check tail navigation light and cap assembly (P/N 45A23325) for security and cracks.

H550002 4. RUDDER ASSEMBLY (Exterior inspection only, panel removal is not required) - Inspect skin and static wicks for condition and evidence of lightning strike.


A2 Jan 01/1205-20-02


HORIZONTAL STABILIZER


TASKCODE A DATE MECH INSP

A. HORIZONTAL STABILIZER

H550004 1. STABILIZER SKIN, LEADING EDGES AND ACCESS PANELS (Exterior inspection only, panel removal is not required)

a. Inspect for condition. X


X

H330005 2. TAIL FLOOD LIGHTS - Inspect for condition. X

H550005 3. ELEVATOR ASSEMBLY (Exterior inspection only, panel removal is not required) - Inspect skin and static wicks for condition and evidence of lightning strike.

X

H120010 4. Lubricate items as specified in Chapter 12. X

05-20-02Page 614Jan 01/12 A2


LEFT-HAND POWER PLANT, PYLON AND NACELLE

NOTE: The JT15D-5/-5R engine inspection requirements must be completed at this interval. Refer to JT15D-5/-5R Pratt and Whitney Maintenance Manual, Chapter 72-00-00.



A. LEFT-HAND POWER PLANT, PYLON AND NACELLE

H540101 1. PYLON SKIN (Exterior inspection only, panel removal is not required) - Inspect for condition.

H540102 2. NACELLE

a. Inspect all cowlings for condition.

b. Ensure all 1/4-turn fasteners are present and secured.

c. Inspect fastener holes for cracks and elongation.

H540103 3. ENGINE INLET



H520120 4. OIL FILLER DOOR - Inspect door, hinge and latch for condition and proper operation (Ref. Chapter 06-50-00, Figure 14, panels 410D/420D).

H520119 5. REMOTE OIL ACCESS DOOR (RK-78, RK-87 thru RK-390, RK-392 with Kit 128-9007-0001 Installed, RK-391, RK-393 and After) - Inspect door, hinge and latch for condition and proper operation (Ref. Chapter 06-50-00, Figure 14, panels 410E/420E).

H720001 6. ENGINE CONTROLS AND CABLE - Check for full travel and freedom of movement, damage and wear, evidence of moisture ingress and proper safeties.

H720005 7. ENGINE ACCESSORIES - Inspect all for condition.

H720013 8. ENGINE ISOLATOR MOUNTS - Inspect for corrosion, damage, and deterioration of rubber isolators. (Engine removal is not necessary.)

H720004 9. FUEL AND HYDRAULIC LINES - Inspect for condition and deterioration.

A2 Jan 01/1205-20-02


A. LEFT-HAND POWER PLANT, PYLON AND NACELLE (Continued)

H260106 10. ENGINE FIRE EXTINGUISHER TUBING AND DETECTOR LOOP

a. Inspect extinguisher discharge tubing for condition and obstruction.

b. Perform FIRE DETECTOR SENSOR CABLE INSPECTION procedure (Ref. Chapter 26-10-00).

H720006 11. ELECTRICAL HARNESS - Inspect connectors, terminals and wires for condition, deterioration and evidence of arcing or overheating.

H710102 12. BLEED AIR SYSTEM

a. Inspect bleed air tube assemblies and nacelle anti-ice duct for condition.

b. Inspect nacelle anti-ice pressure regulator shutoff valve and mount structure for condition.




05-20-02Page 616Jan 01/12 A2


RIGHT-HAND POWER PLANT, PYLON AND NACELLE




A. RIGHT-HAND POWER PLANT, PYLON AND NACELLE

H540201 1. PYLON SKIN (Exterior inspection only, panel removal is not required) - Inspect for condition.

H540202 2. NACELLE

a. Inspect all cowlings for condition.

b. Ensure all 1/4-turn fasteners are present and secured.

c. Inspect fastener holes for cracks and elongation.

H540203 3. ENGINE INLET



H520220 4. OIL FILLER DOOR - Inspect door, hinge and latch for condition and proper operation (Ref. Chapter 06-50-00, Figure 14, panels 410D/420D).

H520219 5. REMOTE OIL ACCESS DOOR (RK-78, RK-87 thru RK-390, RK-392 with Kit 128-9007-0001 Installed, RK-391, RK-393 and After) - Inspect door, hinge and latch for condition and proper operation (Ref. Chapter 06-50-00, Figure 14, panels 410E/420E).

H720008 6. ENGINE CONTROLS AND CABLE - Check for full travel and freedom of movement, damage and wear, evidence of moisture ingress and proper safeties.

H720009 7. ENGINE ACCESSORIES - Inspect all for condition.

H720012 8. ENGINE ISOLATOR MOUNTS - Inspect for corrosion, damage, and deterioration of rubber isolators. (Engine removal is not necessary.)

H720010 9. FUEL AND HYDRAULIC LINES - Inspect for condition and deterioration.

A2 Jan 01/1205-20-02


A. RIGHT-HAND POWER PLANT, PYLON AND NACELLE (Continued)

H260206 10. ENGINE FIRE EXTINGUISHER TUBING AND DETECTOR LOOP

a. Inspect extinguisher discharge tubing for condition and obstruction.

b. Perform FIRE DETECTOR SENSOR CABLE INSPECTION procedure (Ref. Chapter 26-10-00).

H720011 11. ELECTRICAL HARNESS - Inspect connectors, terminals and wires for condition, deterioration and evidence of arcing or overheating.

H710202 12. BLEED AIR SYSTEM

a. Inspect bleed air tube assemblies and nacelle anti-ice duct for condition.

b. Inspect nacelle anti-ice pressure regulator shutoff valve and mount structure for condition.




05-20-02Page 618Jan 01/12 A2


LEFT-HAND THRUST REVERSER

NOTE: Refer to Chapter 78 of the Component Maintenance Manual, P/N 128-590001-81 or subsequent for the following.



A. LEFT-HAND THRUST REVERSER

H290104 1. HYDRAULIC LINES - Inspect for condition and deterioration.

H780105 2. UPPER AND LOWER DOORS

a. Inspect for condition, evidence of door twisting, and faired position of the doors in the stowed position.

b. Measure bumper pad thickness. (Ref. Chapter 78-30-07 in the Component Maintenance Manual, P/N 128-590001-81 or subsequent).

H780101 3. STANGS AND DOORS



H780106 4. FAN DUCT ASSEMBLY - Inspect for condition.

H780102 5. MECHANICAL ACTUATING MECHANISM

a. Inspect support assemblies, carriage, links, levers, cams, cam followers and support bracket for cracks, evidence of damage, freedom of movement and security of installation. Ensure driver-link attach bolt does not rotate.

b. Check link bearings and door-bushing carriage-guide rods, linkage pivot points and cam follower for freedom of rotation.

c. Measure deflection of driver links. (Ref. Chapter 78-30-07 in the Component Maintenance Manual P/N 128-590001-81 or subsequent).

H780109 6. HYDRAULIC ACTUATOR - Inspect for hydraulic leaks, damaged pushrod, damaged flexible hoses and security of installation.

A2 Jan 01/1205-20-02


A. LEFT-HAND THRUST REVERSER (Continued)

H780103 7. DEPLOY AND STOW LIMIT SWITCHES

a. Inspect wiring and switches for condition and deterioration.

b. Perform THRUST REVERSER STOW LIMIT SWITCHES CHECK (Ref. Chapter 78-30-00).

H760104 8. THROTTLE FEEDBACK CABLE - Inspect for condition and freedom of movement.

H760105 9. FEEDBACK BRACKET ASSEMBLY

a. Inspect for condition and alignment.

b. Inspect the lever and spindle for wear and alignment.

c. Inspect the resilience of the spring.

H780108 10. THRUST REVERSER

a. Perform NORMAL THRUST REVERSER SYSTEM CHECK (Ref. Chapter 78-30-00).

b. Perform EMERGENCY STOW SYSTEM TEST (Ref. Chapter 78-30-00).




05-20-02Page 620Jan 01/12 A2


RIGHT-HAND THRUST REVERSER

NOTE: Refer to Chapter 78 of the Component Maintenance Manual, P/N 128-590001-81 or subsequent for the following.



A. RIGHT-HAND THRUST REVERSER

H290204 1. HYDRAULIC LINES - Inspect for condition and deterioration.

H780205 2. UPPER AND LOWER DOORS

a. Inspect for condition, evidence of door twisting, and faired position of the doors in the stowed position.

b. Measure bumper pad thickness. (Ref. Chapter 78-30-07 in the Component Maintenance Manual, P/N 128-590001-81 or subsequent).

H780201 3. STANGS AND DOORS



H780206 4. FAN DUCT ASSEMBLY - Inspect for condition.

H780202 5. MECHANICAL ACTUATING MECHANISM

a. Inspect support assemblies, carriage, links, levers, cams, cam followers and support bracket for cracks, evidence of damage, freedom of movement and security of installation. Ensure driver-link attach bolt does not rotate.

b. Check link bearings and door-bushing carriage-guide rods, linkage pivot points and cam follower for freedom of rotation.

c. Measure deflection of driver links. (Ref. Chapter 78-30-07 in the Component Maintenance Manual, P/N 128-590001-81 or subsequent).

H780209 6. HYDRAULIC ACTUATOR - Inspect for hydraulic leaks, damaged pushrod, damaged flexible hoses and security of installation.

A2 Jan 01/1205-20-02


A. RIGHT-HAND THRUST REVERSER (Continued)

H780203 7. DEPLOY AND STOW LIMIT SWITCHES

a. Inspect wiring and switches for condition and deterioration.

b. Perform THRUST REVERSER STOW LIMIT SWITCHES CHECK (Ref. Chapter 78-30-00).

H760204 8. THROTTLE FEEDBACK CABLE - Inspect for condition and freedom of movement.

H760205 9. FEEDBACK BRACKET ASSEMBLY

a. Inspect for condition and alignment.

b. Inspect the lever and spindle for wear and alignment.

c. Inspect the resilience of the spring.

H780208 10. THRUST REVERSER

a. Perform NORMAL THRUST REVERSER SYSTEM CHECK (Ref. Chapter 78-30-00).

b. Perform EMERGENCY STOW SYSTEM TEST (Ref. Chapter 78-30-00).




05-20-02Page 622Jan 01/12 A2


ENGINE GROUND RUN AND OPERATIONAL CHECKS

NOTE: Observe all operating limitations in the Model 400A FAA Approved Airplane Flight Manual.



A. ENGINE GROUND RUN AND OPERATIONAL CHECKS

H710001 1. ENGINE SYSTEMS - NOTE: Observe ENGINE GROUND OPERATING PROCEDURES (Ref. Chapter 71-00-00).

a. Perform NORMAL PERFORMANCE CHECK and record data on Engine Run Check Record Sheet (Ref. Chapter 71-00-00).

b. Perform THRUST LEVER AGREEMENT (Ref. Chapter 71-00-00).

c. Perform ENGINE INSTRUMENT AGREEMENT (Ref. Chapter 71-00-00).

d. Perform MAX POWER CHECK IN REVERSION MODE (Ref. Chapter 71-00-00).

H210019 2. CABIN PRESSURE CONTROL SYSTEM - Perform CABIN PRESSURIZATION SYSTEM OPERATIONAL TEST (Ref. Chapter 21-30-00).

A2 Jan 01/1205-20-02


Nose and Main Landing Gear - Uplock Emergency Release Cable End Inspection(RK-1 and After)

Figure 601

CD

B

B

C

A

DETAIL A

DETAIL D

DETAIL B DETAIL CRK05B 086098AA.AI

NOTE: ARROWS SHOW POINTS OF INSPECTION

05-20-02Page 624Jan 01/12 A2


Antenna Locator(RK-1 and After)

Figure 602

RK27B 063119AA.AI

GPS (SINGLE)

MARKER BEACON

NO. #1 TRANSPONDER

NO. #2 TRANSPONDER

NO. 1 VHF

NO. #1 TRANSPONDER

NO. #2 TRANSPONDER

TCAS

TCASNO. 2 DME

NO. 1 DME

FLITEFONE (OPTIONAL)

AFIS (OPTIONAL)

NO. 2 VHF

ADF

HF (OPTIONAL)

VOR/LOC (ONE ON EACH SIDE OF VERTICAL STABILIZER)

GPS (DUAL)

RADAR ALTIMETER (TRANSMIT) RADAR

ALTIMETER (RECEIVE)

A2 Jan 01/1205-20-03


60060060005-20-0

SCHEDULED IFA-B INSPECTIONS

PILOT'S COMPARTMENT




H350001 1. PILOT'S AND COPILOT'S OXYGEN SYSTEM - Perform the appropriate FLIGHT CREW OXYGEN SYSTEM OPERATIONAL CHECK (Ref. Chapter 35-11-00).

H350002 2. PASSENGER OXYGEN SYSTEM - Perform PASSENGER OXYGEN SYSTEM CHECK (Ref. Chapter 35-21-00).

H320013 3. MASTER BRAKE CYLINDERS (Above Floor Panels) - Clean piston rod surfaces and upper surface of cylinder bodies and inspect for condition.

H320041 4. MANUAL BRAKE SYSTEM - Perform BRAKE MIXING VALVE FUNCTIONAL CHECK (Ref. Chapter 32-40-00).

H110001 5. INTERIOR PLACARDS AND DECALS - Inspect for security, presence and legibility. Refer to the appropriate Model 400A Pilots Operating Manual, Section 2, Operating Limitations.

H240001 6. ELECTRICAL COMPONENTS - AREA INSPECTION - (Accessible without interior disassembly) - Inspect for condition and evidence of overheating.

H210016 7. COCKPIT SIDE WINDOW DEFOG BLOWER - Perform COCKPIT SIDE WINDOW DEFOG BLOWER TEST (Ref. Chapter 30-40-00).

H330008 8. FLIGHT COMPARTMENT LIGHTING - Perform FLIGHT COMPARTMENT LIGHTS FUNCTIONAL TEST (Ref. Chapter 33-11-00).

H330009 9. EXTERIOR LIGHTING - Perform EXTERIOR LIGHTS ADJUSTMENT AND TEST (Ref. Chapter 33-40-00).

H260006 10. FIRE DETECTION SYSTEM - Perform FIRE DETECTION SYSTEM OPERATIONAL TEST (Ref. Chapter 26-10-00).

H300006 11. HORIZONTAL STABILIZER DEICE SYSTEM - Perform Horizontal Stabilizer Deice System OPERATIONAL TEST (Ref. Chapter 30-12-00).

H230004 12. COCKPIT WARNING SYSTEM - Perform COCKPIT VOICE RECORDER FUNCTIONAL TEST (Ref. Chapter 23-70-00).

05-20-03Page 602Jan 01/12 A2



H340008 13. STALL WARNING SYSTEM

a. Perform stall warning system - SELF TEST (Ref. Chapter 34-11-00).

b. Perform FAULT INDICATOR TEST (Ref. Chapter 34-11-00).

H250009 14. RELIEF TUBE - If installed, inspect plumbing and storage box for condition.

H760004 15. CENTER PEDESTAL

a. Perform THRUST LEVER OPERATIONAL CHECK (Ref. Chapter 76-10-00).

b. Perform THRUST STOP MECHANISM OPERATIONAL CHECK (Ref. Chapter 76-10-00).

H210028 16. PRESSURIZATION CONTROL COMPONENTS AIR FILTERS/SCREENS

a. Perform CABIN ALTITUDE (CABIN PRESSURE LOW) SWITCH (S092) FUNCTIONAL TEST (Ref. Chapter 21-30-00).

b. CABIN AIR PRESSURE CONTROLLER FILTER - Clean or replace filter as necessary (Ref. Chapter 21-30-00).

c. SOLENOID VALVE (S2) AIR FILTER - Perform the SOLENOID VALVE (S2) AIR FILTER servicing procedure and inspect filter for condition (Ref. Chapter 21-30-00).

d. OUTFLOW/SAFETY VALVE STATIC PORT SCREENS (RK-49 and After) - Perform the OUTFLOW/SAFETY VALVE STATIC PORT SCREENS servicing procedure and inspect screens for condition (Ref. Chapter 21-30-00).

e. CABIN HIGH PRESSURE SWITCH AIR FILTER (RK-93 and After) - Perform the CABIN HIGH PRESSURE SWITCH AIR FILTER servicing procedure and inspect screen for condition (Ref. Chapter 21-30-00).

H210006 17. AIR-CONDITIONING CONTROL SWITCH PANEL (copilots sidepanel) (RK-78, RK-87 and After) - Inspect for condition and operation.

SCHEDULED IFA-B INSPECTIONS (Continued)


A2 Jan 01/1205-20-03



H210017 18. CEILING AIR OUTLET SHUTOFF VALVE (RK-1 thru RK-97 and RK-99 thru RK-109) - Perform the appropriate CEILING AIR OUTLET SHUTOFF VALVE TEST procedure (Ref. Chapter 21-20-00).

H340004 19. PRIMARY FLIGHT DISPLAY (PFD) AND MULTIFUNCTION DISPLAY (MFD) COOLING FANS - Inspect screens for lint, carpet fibers and indication of blockage.

H341101 20. AIRBORNE FLIGHT INFORMATION SYSTEM (AFIS) (RK-483 and After - Optional) - Inspect the Data Base Unit (DBU) for proper mounting and security of attachment (Ref. Chapter 34-59-00).




05-20-03Page 604Jan 01/12 A2


CABIN SECTION



A. CABIN SECTION

1. EMERGENCY LIGHTING SYSTEM

H330010 a. (RK-1 thru RK-109, except RK-98) - Perform the complete EMERGENCY LIGHT POWER SUPPLY FUNCTIONAL TESTING AND CHARGING PROCEDURE (Ref. Chapter 33-50-00).

H330011 b. (RK-98, RK-110 and After) - Perform Emergency Lighting System FUNCTIONAL TEST PROCEDURES (Ref. Chapter 33-51-00).

H250003 2. DIVIDER AND PARTITIONS (Removal not required) - Inspect for condition.

H250005 3. REFRESHMENT CENTER AND STORAGE CABINETS (Removal not required) - Inspect for condition.

H520009 4. ENTRANCE DOOR LATCH AND LOCK MECHANSIM - Inspect operation of entrance door latch mechanism and ensure proper function of lock mechanism (Ref. Figure 601).

H520008 5. DOOR WARNING SYSTEM - Perform DOOR WARNING SYSTEM CHECK (Ref. Chapter 52-70-00).

H520010 6. EMERGENCY EXIT LATCH AND LOCK MECHANSIM - Inspect operation of emergency exit door latch mechanism and ensure proper function of lock mechanism.

H110002 7. INTERIOR PLACARDS AND DECALS - Inspect for security, presence and legibility. Refer to the appropriate Model 400A Pilots Operating Manual, Sections 2, Operating Limitations.

H240005 8. ELECTRICAL COMPONENTS - AREA INSPECTION - (Accessible without interior disassembly) - Inspect for condition and evidence of overheating.

H350008 9. PASSENGER OXYGEN SYSTEM - Inspect each passenger oxygen mask assembly and supply tubing for condition and deterioration of its elastomeric and vinyl components.

H240015 10. GENERATOR CONTROL UNITS (GCU) - Inspect both GCUs and electrical connectors for condition and security of connection.

5A2 Jan 01/1205-20-03


A. CABIN SECTION (Continued)

H210001 11. FWD & AFT EVAPORATOR BOX ASSEMBLIES (RK-78, RK-87 and After) - Inspect intake air filter for cleanliness and condition.

H210035 12. OVERHEAD AIR OUTLET

a. Inspect for condition and mechanical operation.

b. (RK-78, RK-87 thru RK-109, except RK-98) - Assure outlets do not fully close.

H250010 13. PASSENGER AND TOILET SEAT - Perform operational check of the toilet assembly flushing system (Ref. Chapter 38, Component Maintenance Manual, P/N 128-590001-81.




05-20-03Page 606Jan 01/12 A2


FORWARD FUSELAGE



A. FORWARD FUSELAGE

H110003 1. EXTERIOR PLACARDS AND DECALS - Inspect for security, presence and legibility (Ref. Chapter 11-22-00).

H520002 2. AVIONICS ACCESS DOORS - Inspect doors and seals for condition.

H240016 3. ELECTRICAL AND AVIONICS COMPONENTS - AREA INSPECTION (Forward of the pressure bulkhead; Avionics removal not required) - Inspect for condition and evidence of overheating.

H340011 4. PITOT, STATIC AND AOA SENSOR - Perform PITOT/STATIC AND AOA HEATING SYSTEM OPERATIONAL CHECK (Ref. Chapter 30-30-00).

H530033 5. RVSM REGION - Perform RVSM REGION INSPECTION to verify the area is free from damage, deterioration or repair.

H210002 6. OUTFLOW SAFETY VALVE POPPET SEATS (as viewed from nose avionics compartment) - Inspect for condition and contamination. Clean with isopropyl alcohol if necessary.

H350009 7. OXYGEN SYSTEM - Detail inspect oxygen cylinder, regulator, and plumbing for condition.

H320014 8. NITROGEN SYSTEM - Detail inspect nitrogen cylinder, plumbing and valve for condition.

H530001 9. FUSELAGE MOISTURE DRAIN HOLE - Inspect drain holes for obstruction.

H300008 10. WINDSHIELD WIPERS (RK-1 thru RK-242 without Kit 128-5405 installed) - Perform WIPER ON WET GLASS OPERATIONAL TEST (Ref. Chapter 30-40-00).

H300009 11. WINDSHIELD HEAT - Perform windshield heat OPERATIONAL TEST (Ref. Chapter 30-40-00).


A2 Jan 01/1205-20-03


MIDFUSELAGE



A. MIDFUSELAGE

H320015 1. BRAKE SYSTEM - Inspect power brake valve, parking brake valves and accumulator for condition.


H530003 3. WING/FUSELAGE FILLET (Exterior inspection only, fillet removal is not required) - Inspect for condition.

H280006 4. FUEL SYSTEM PLUMBING AND COMPONENT MOUNTING (RK-106 thru RK-507 with Kit 128-9008 installed; RK-508 and After) (Gain access through panels 311AB and 312AB) - Inspect for condition and leakage.

H280007 5. MOTIVE-FLOW SHUTOFF VALVE, CROSSFEED VALVE, AND FUEL SHUTOFF VALVE (RK-106 thru RK-507 with Kit 128-9008 Installed; RK-508 and After) - Inspect for condition and leakage.

H270008 6. SPOILER OPERATION

a. Perform Spoiler OPERATIONAL CHECK (Ref. Chapter 27-60-00). NOTE: Not required if the complete SPOILER CONTROL SYSTEM FUNCTIONAL TEST procedure is performed.

b. Inspect spoiler servo cables for condition, routing and broken strands.

c. Perform SPOILER SERVO OPERATIONAL CHECKOUT (Ref. Chapter 22-13-00).

H270118 7. SPEED BRAKE OPERATION - Perform Speed Brake OPERATIONAL TEST (Ref. Chapter 27-60-00). NOTE: Not required if the complete SPEED BRAKE SYSTEM ADJUSTMENT/TEST procedure is performed.


05-20-03Page 608Jan 01/12 A2


LEFT-HAND WING



A. LEFT-HAND WING


H270109 2. WING FLAPS SYSTEM (Flaps Extended)

a. Detail inspect flap actuator, flap drive linkage and all control levers for condition and seized bearings.

b. Inspect flap hydraulic plumbing for routing and condition.

c. Inspect flap position transmitter for condition and seized linkage.

d. Inspect flap follow-up switch for condition and seized linkage.

e. Detail inspect flap cables, flap interconnect cables and pulleys for condition, routing and broken strands. NOTE: Closely examine the flap cables at the middle control lever where they pass through the stopper fittings for evidence of slippage or corrosion. (No inter strand corrosion permitted, Ref. Chapter 20-10-08).

f. Detain inspect main flap rollers, main flap tracks, attachments and push-pull rods for condition, seized bearings and sufficient engagement of rod ends.

g. Detain inspect aft flap rollers, aft flap tracks, attachments and push-pull rods for condition, seized bearings and sufficient engagement of rod ends.

H270111 3. FLAP OPERATION (Perform in conjunction with RH wing inspection) - Perform the flap system OPERATIONAL TEST (Ref. Chapter 27-50-00). NOTE: Not required if the complete FLAP CONTROL SYSTEM FUNCTIONAL TEST is performed.

H270113 4. ROLL TRIM ACTUATOR, ATTACHMENT, DRIVE LINKAGE, POTENTIOMETER and NEUTRAL SWITCH - Inspect for condition, seized bearings and sufficient engagement of rod ends (Ref. Chapter 27-10-00, Figure 202).

H270105 5. ROLL TRIM OPERATION - Perform the ROLL TRIM SYSTEM OPERATIONAL TEST (Ref. Chapter 27-10-00). NOTE: Not required if the complete ROLL TRIM TESTING procedure is performed.

A2 Jan 01/1205-20-03


A. LEFT-HAND WING (Continued)

H270115 6. SPOILER SECTOR AND PUSHRODS - Detail inspect for condition, seized bearings and sufficient engagement of rod ends (Ref. Chapter 27-60-00, Figure 211).

H270116 7. SPOILER CABLES - Detail inspect cables and pulleys for proper routing and condition (No inter strand corrosion permitted, Ref. Chapter 20-10-08).

H270147 8. LEFT SPOILER BRACKET SUPPORT FITTING (P/N 45A62036) - Detail inspect for cracks and any other indications of structural damage. (Disassembly is not required). (Ref. IPC Figure 27-60-20-01).

H570112 9. SPOILER BRACKET (P/N 45A10152) REAR SPAR AREA (WCS 2513) - Inspect bracket for security and cracking. Pay particular attention to the area surrounding the bracket holes and mounting hardware (Ref. Figure 609).




05-20-03Page 610Jan 01/12 A2


RIGHT-HAND WING



A. RIGHT-HAND WING


H270209 2. WING FLAPS SYSTEM (Flaps Extended)

a. Detail inspect flap actuator, flap drive linkage and all control levers for condition and seized bearings.

b. Inspect flap hydraulic plumbing for routing and condition.

c. Inspect flap position transmitter for condition and seized linkage.

d. Inspect flap follow-up switch for condition and seized linkage.

e. Detail inspect flap cables, flap interconnect cables and pulleys for condition, routing and broken strands. NOTE: Closely examine the flap cables at the middle control lever where they pass through the stopper fittings for evidence of slippage or corrosion. (No inter strand corrosion permitted, Ref. Chapter 20-10-08).

f. Detain inspect main flap rollers, main flap tracks, attachments and push-pull rods for condition, seized bearings and sufficient engagement of rod ends.

g. Detain inspect aft flap rollers, aft flap tracks, attachments and push-pull rods for condition, seized bearings and sufficient engagement of rod ends.

H270211 3. FLAP OPERATION (Perform in conjunction with LH wing inspection) - Perform the flap system OPERATIONAL TEST (Ref. Chapter 27-50-00). NOTE: Not required if the complete FLAP CONTROL SYSTEM FUNCTIONAL TEST is performed.

H270213 4. ROLL TRIM ACTUATOR, ATTACHMENT, DRIVE LINKAGE, POTENTIOMETER and NEUTRAL SWITCH - Inspect for condition, seized bearings and sufficient engagement of rod ends (Ref. Chapter 27-10-00, Figure 202).

H270205 5. ROLL TRIM OPERATION - Perform the ROLL TRIM SYSTEM OPERATIONAL TEST (Ref. Chapter 27-10-00). NOTE: Not required if the complete ROLL TRIM TESTING procedure is performed.

A2 Jan 01/1205-20-03


A. RIGHT-HAND WING (Continued)

H270215 6. SPOILER SECTOR AND PUSHRODS - Detail inspect for condition, seized bearings and sufficient engagement of rod ends (Ref. Chapter 27-60-00, Figure 211).

H270216 7. SPOILER CABLES - Detail inspect cables and pulleys for proper routing and condition (No inter strand corrosion permitted, Ref. Chapter 20-10-08).

H270247 8. RIGHT SPOILER BRACKET SUPPORT FITTING (P/N 45A62036) - Detail inspect for cracks and any other indications of structural damage. (Disassembly is not required) (Ref. IPC Figure 27-60-20-01).

H570212 9. SPOILER BRACKET (P/N 45A10152) REAR SPAR AREA (WCS 2513) - Inspect bracket for security and cracking. Pay particular attention to the area surrounding the bracket holes and mounting hardware (Ref. Figure 609).




05-20-03Page 612Jan 01/12 A2






H320040 1. LANDING GEAR SYSTEM

a. Perform LANDING GEAR FUNCTIONAL TEST (Ref. Chapter 32-00-00).

b. Perform nose steering NEUTRAL POSITION CHECK (Ref. Chapter 32-50-00).

H320020 2. NOSE LANDING GEAR STRUT ASSEMBLY

a. Detail inspect strut assembly for security, wear, cracks, loose or missing fasteners and any evidence of damage or corrosion.

b. Inspect hydraulic actuator cylinder and hydraulic lines for condition and routing.

H320037 3. NOSE WHEEL AND TIRE

a. Clean and inspect wheel bearings and cones. Re-lubricate wheel bearings (Ref. Chapter 12-20-00).

b. Inspect axle, caps and spacers for condition and corrosion.

H320017 4. NOSE LANDING GEAR DRAG STRUT ASSEMBLY

a. Detail inspect for condition.

b. Inspect downlock hydraulic actuator cylinder and hydraulic lines for condition and routing.

c. Inspect bearings in the lower drag strut for slippage (Ref. Figure 602).

d. Inspect downlock switch and bracket for proper mounting and condition.

H320018 5. NOSE LANDING GEAR UPLOCK ASSEMBLY

a. Detail inspect uplock hook mechanism for condition and freedom of movement.

b. Inspect uplock hydraulic actuator cylinder and hydraulic lines for condition and routing.

c. Inspect uplock switch and bracket for proper mounting and condition.

A2 Jan 01/1205-20-03



H320003 6. NOSE LANDING GEAR WHEEL WELL

a. Inspect attach fittings, support structure and keels skins for cracks, loose or missing fasteners, corrosion and evidence of damage.

b. Inspect wire harness for condition, deterioration and routing.

H520005 7. NOSE LANDING GEAR DOORS - Detail inspect door linkage installation for condition, seized bearings and sufficient engagement of rod ends

H320019 8. NOSE LANDING GEAR EMERGENCY EXTENSION CABLE - Inspect for condition and proper routing.

H320038 9. NOSE WHEEL STEERING SYSTEM -

a. Detail inspect cam assembly, lever assembly and steering rod for condition, seized bearings and freedom of movement.

b. Perform NOSE GEAR TORQUE ARM ASSEMBLY CHECK (Ref. Chapter 32-50-00).

H320124 10. LEFT MAIN LANDING GEAR STRUT ASSEMBLY


b. Inspect hydraulic actuator cylinder and hydraulic lines for corrosion.

H320125 11. LEFT MAIN WHEEL


b. Inspect wheel brake disc drive keys for loose and missing hardware.

c. Inspect axle, nut and spacer for condition and corrosion.

H320109 12. LEFT BRAKE ASSEMBLY - Detail inspect brake assembly for condition.

H290101 13. LEFT BRAKE HYDRAULIC/PNEUMATIC LINES AND HOSES - Inspect for condition and routing on the strut and in the wheel well.



05-20-03Page 614Jan 01/12 A2



H320120 14. LEFT LANDING GEAR SAFETY SWITCH - Inspect switch, linkage, mounting and wire harness for condition.

H320121 15. LEFT MAIN LANDING GEAR SIDE STRUT ASSEMBLY

a. Detail inspect side strut assembly for condition.

b. Inspect bearings in the lower side strut assembly, balancer arm and link assembly for slippage (Ref. Figure 603).

c. Inspect downlock actuator, hydraulic plumbing and downlock mechanism for condition and routing.

d. Inspect downlock switch, mount hardware and wire harness for condition and routing.

H320107 16. LEFT MAIN ACTUATOR BRACKET - Detail inspect for evidence of interference between the actuator bracket and the wing spar (i.e. paint damage) (Ref. Figure 604). Replace if interference is found.

H320122 17. LEFT MAIN LANDING GEAR AND DOOR UPLOCK HOOK AND UPLOCK ASSEMBLIES

a. Inspect hydraulic uplock cylinder and hydraulic plumbing for condition and routing.

b. Detail inspect uplock hook mechanism for condition and freedom of movement.

c. Inspect uplock switch, mount bracket and wire harness for condition and routing.

H320108 18. LEFT MAIN WHEEL WELL AND AREA INSPECTION (Panel Removal Not Required)

a. Inspect wheel well area structure and skin for cracks, loose and missing fasteners, corrosion and evidence of damage.

b. Inspect wire harness for condition, routing and evidence of tire rub.



A2 Jan 01/1205-20-03



H320224 19. RIGHT MAIN LANDING GEAR STRUT ASSEMBLY


b. Inspect hydraulic actuator cylinder and hydraulic lines for corrosion.

H320225 20. RIGHT MAIN WHEEL


b. Inspect wheel brake disc drive keys for loose and missing hardware.

c. Inspect axle, nut and spacer for condition and corrosion.

H320209 21. RIGHT BRAKE ASSEMBLY - Detail inspect brake assembly for condition.

H290201 22. RIGHT BRAKE HYDRAULIC/PNEUMATIC LINES AND HOSES - Inspect for condition and routing on the strut and in the wheel well.

H320220 23. RIGHT LANDING GEAR SAFETY SWITCH - Inspect switch, linkage, mounting and wire harness for condition.

H320221 24. RIGHT MAIN LANDING GEAR SIDE STRUT ASSEMBLY

a. Detail inspect side strut assembly for condition.

b. Inspect bearings in the lower side strut assembly, balancer arm and link assembly for slippage (Ref. Figure 603).

c. Inspect downlock actuator, hydraulic plumbing and downlock mechanism for condition and routing.

d. Inspect downlock switch, mount hardware and wire harness for condition and routing.

H320207 25. RIGHT MAIN ACTUATOR BRACKET - Detail inspect for evidence of interference between the actuator bracket and the wing spar (i.e. paint damage) (Ref. Figure 604). Replace if interference is found.



05-20-03Page 616Jan 01/12 A2



H320222 26. RIGHT MAIN LANDING GEAR AND DOOR UPLOCK HOOK AND UPLOCK ASSEMBLIES

a. Inspect hydraulic uplock cylinder and hydraulic plumbing for condition and routing.

b. Detail inspect uplock hook mechanism for condition and freedom of movement.

c. Inspect uplock switch, mount bracket and wire harness for condition and routing.

H320208 27. RIGHT MAIN WHEEL WELL AND AREA INSPECTION (Panel Removal Not Required)

a. Inspect wheel well area structure and skin for cracks, loose and missing fasteners, corrosion and evidence of damage.

b. Inspect wire harness for condition, routing and evidence of tire rub.

H320026 28. ANTI-SKID SYSTEM

a. Perform WHEEL SPEED TRANSDUCER INSPECTION (Ref. Chapter 32-40-00). NOTE: This check is not required if the complete BRAKE SYSTEM FUNCTIONAL TESTING procedure in Chapter 32-40-00 is performed.

b. Perform ANTI-SKID RESPONSE CHECK (Ref. Chapter 32-40-00). NOTE: This check is not required if the complete BRAKE SYSTEM FUNCTIONAL TESTING procedure in Chapter 32-40-00 is performed.

c. Perform FAILURE DETECTION CIRCUIT CHECK (Ref. Chapter 32-40-00). NOTE: This check is not required if the complete BRAKE SYSTEM FUNCTIONAL TESTING procedure in Chapter 32-40-00 is performed.

d. Perform TOUCH-DOWN PROTECTION CIRCUIT CHECK (Ref. Chapter 32-40-00). NOTE: This check is not required if the complete BRAKE SYSTEM FUNCTIONAL TESTING procedure in Chapter 32-40-00 is performed.




A2 Jan 01/1205-20-03


AFT FUSELAGE



A. AFT FUSELAGE


H530002 2. DORSAL FIN AND VENTRAL FIN - (Exterior inspection only, panel removal not required) - Inspect fins for condition (Ref. Chapter 53-50-00).

H520006 3. BAGGAGE DOORS - Inspect baggage door seals for condition.

H240002 4. BATTERY INSTALLATION

a. Inspect battery installation for condition.

b. Inspect battery terminal connector for security of connection, corrosion and evidence of overheating. Disassemble and clean if corrosion is noted.

H240008 5. BATTERY, EXTERNAL POWER AND GENERATOR GROUNDING TERMINALS AND HARDWARE - Inspect for security of connection, corrosion and evidence of overheating. Disassemble and clean if corrosion is noted, or if generator load split is noted (Ref. Chapter 20-20-03). Access through panels 311FL and 312DR as shown in Chapter 06-50-00.

H520011 6. EXTERNAL POWER RECEPTACLE

a. Inspect for security, corrosion and evidence of overheating. Disassemble and clean if corrosion is noted.

b. Inspect main junction electrical components for condition and evidence of overheating.

H240009 7. ELECTRICAL COMPONENTS - AREA INSPECTION - Inspect aft fuselage area electrical components for condition and evidence of overheating.

H290003 8. HYDRAULIC PACKAGE FLUID FILTER ELEMENTS - Replace (Ref. Chapter 29-10-00).

H290004 9. HYDRAULIC PACKAGE AIR FILTER - Clean (Ref. Chapter 29-10-00 in the Component Maintenance Manual, P/N 128-590001-81 or subsequent).

H290002 10. HYDRAULIC PACKAGE, SYSTEM PLUMBING, COMPONENTS - Detail inspect for condition and cleanliness.

05-20-03Page 618Jan 01/12 A2


A. AFT FUSELAGE (Continued)

H210018 11. ENVIRONMENTAL CONTROL UNIT (ECU) AND DUCTING (Panels 311RL and 312FR removed) - Detail inspect ECU, bleed air manifold assembly and associated ducting for condition and evidence of hot air leakage (where visible) (Ref. Figure 608).

H780004 12. THRUST REVERSER CONTROL VALVE, ISOLATION VALVE, PRESSURE SWITCH, CHECK VALVE AND HYDRAULIC LINES - Inspect all for condition and cleanliness.


a. Perform NACELLE FIRE EXTINGUISHER CONTAINER INSPECTION (Ref. Chapter 26-20-00)

b. Inspect fire extinguisher discharge plumbing for condition.

H270024 14. CONTROL CABLES

a. Inspect thrust control cables and bellcranks for condition and routing.

b. Inspect rudder control cables, pulleys, guard pins and brackets from the aft pressure bulkhead to the rudder quadrant for condition, routing and broken strands.

c. Inspect rudder servo, servo cables and cable blocks for condition, routing, slippage and broken strands.

d. Perform RUDDER SERVO OPERATIONAL CHECKOUT (Ref. Chapter 22-13-00).

e. Inspect elevator control cables, pulleys, guard pins and brackets from the aft pressure bulkhead to the elevator quadrant for condition, routing and broken strands.

f. Inspect elevator servo, servo cables and cable blocks for condition, routing, slippage and broken strands.

g. Perform ELEVATOR SERVO OPERATIONAL CHECKOUT (Ref. Chapter 22-13-00).

H530007 15. AFT FUSELAGE BAGGAGE PANELS

a. Inspect baggage compartment composite panels for condition and oil or grease contamination.

b. Inspect baggage compartment panels and supporting frame structure velcro fastener material for condition.



A2 Jan 01/1205-20-03



H210011 16. VAPOR CYCLE COOLING SYSTEM (RK-78, RK-87 and After)

a. Inspect compressor/condenser module assembly and ducting for condition (compressor/condenser module not removed).

b. Inspect wire harness and grounding points (airframe and module) for condition and evidence of overheating.

c. Inspect remote refrigerant servicing assembly and refrigerant system plumbing (from the rear pressure bulkhead to the compressor/condenser module) for condition and routing.

d. Inspect remote refrigerant servicing placard for presence and legibility.

e. Inspect circuit breakers, fuses, load shed module and wiring for condition and evidence of overheating.

H530005 17. COMPRESSOR/CONDENSER INLET AND EXHAUST PORTS - Inspect inlet and exhaust ports for condition and obstruction.

H341178 18. AIRBORNE FLIGHT INFORMATION SYSTEM (AFIS) (Optional Equipment - RK-483 and After) - Inspect the Data Management Unit (DMU), the Configuration Module, and the mount rack for proper mounting and security of attachment (Ref. Chapter 34-59-00).




05-20-03Page 620Jan 01/12 A2


VERTICAL STABILIZER





H550007 2. VERTICAL STABILIZER SIDE RAILS AND ROLLER - (Ref. Chapter 55-30-00).

a. Perform SIDE RAIL INSPECTION.

b. Perform SIDE ROLLER BRACKET ASSEMBLY INSPECTION.

H270028 3. ELEVATOR QUADRANT ASSEMBLY, PUSHROD AND CONNECTING HARDWARE, STOP BOLTS AND DOWN SPRING - Detail inspect for condition, seized bearings, freedom of movement and sufficient engagement of rod ends.

H270027 4. ELEVATOR CABLES (Where accessible through access panels)

a. Detail inspect cables for proper routing, corrosion and broken strands.

b. Inspect pulleys and brackets for condition and security.

H550003 5. RUDDER HINGES AND BOLTS, TORQUE TUBE AND BELLCRANK, STOP BOLTS AND RUDDER COUNTER-BALANCE - Detail inspect for condition, seized bearings, freedom of movement and sufficient engagement of rod ends.

H270005 6. RUDDER TRIM TAB AND HINGE - Inspect for condition.

H270037 7. RUDDER TRIM ACTUATOR AND LINKAGE - Inspect for condition.

H270250 8. RUDDER OPERATION - Perform OPERATIONAL TEST (Ref. Chapter 27-20-00). NOTE: This check is not required if the complete RUDDER CONTROL SYSTEM FUNCTIONAL TEST is performed.

H270030 9. RUDDER TRIM OPERATION

a. Perform RUDDER TRIM OPERATIONAL TEST (Ref. Chapter 27-20-00). NOTE: This check is not required if the complete RUDDER TRIM SYSTEM ADJUSTMENT/TEST procedure is performed.

A2 Jan 01/1205-20-03


A. VERTICAL STABILIZER (Continued)




05-20-03Page 622Jan 01/12 A2






H270031 1. ELEVATOR HINGES AND BOLTS, TORQUE TUBE AND HORN LEVER, LEVER AND LINK ASSEMBLY, STOP BOLTS AND HEATER HORN/COUNTER BALANCE - Detail inspect for condition, seized bearings, freedom of movement and sufficient engagement of rod ends (Ref. Figure 605, Sheet 1).

H270032 2. ELEVATOR OPERATION

a. Perform elevator NEUTRAL POSITION CHECK, Step a. and b. (Ref. Chapter 27-30-00). NOTE: This check is not required if the complete ELEVATOR ADJUSTMENT/TEST procedure in Chapter 27-30-00 is performed.

b. Perform elevator OPERATIONAL TEST (Ref. Chapter 27-30-00). NOTE: This check is not required if the complete ELEVATOR ADJUSTMENT/TEST procedure in Chapter 27-30-00 is performed.

H270034 3. PITCH TRIM ACTUATOR AND ATTACH BRACKET ASSEMBLY - Detail inspect pitch trim actuator and attach bracket assembly for condition (Ref. Chapter 27-40-00, Figure 210).

H270002 4. PITCH TRIM POSITION TRANSMITTER AND LINKAGE - Inspect for condition.

H270035 5. PITCH TRIM OPERATION

a. Perform TAKEOFF WARNING HORN CHECK (Ref. Chapter 27-40-00). NOTE: This check is not required if the complete PITCH TRIM SYSTEM FUNCTIONAL TEST procedure is performed.

b. Perform NORMAL OPERATIONAL TEST (Ref. Chapter 27-40-00). NOTE: This check is not required if the complete PITCH TRIM SYSTEM FUNCTIONAL TEST procedure is performed.

c. Perform EMERGENCY OPERATIONAL TEST (Ref. Chapter 27-40-00). NOTE: This check is not required if the complete PITCH TRIM SYSTEM FUNCTIONAL TEST procedure is performed.


A2 Jan 01/1205-20-03


LEFT-HAND POWER PLANT, PYLON AND NACELLE




A. LEFT-HAND POWER PLANT, PYLON AND NACELLE

H540104 1. PYLON NACELLE SEAL - Inspect for condition.

H540105 2. ENGINE/PYLON FIREWALL

a. Inspect firewall area for condition and presence/condition of sealant (Ref. Figure 607).

b. Inspect pylon bleed air, fuel, hydraulic and electrical plumbing and wire harnesses for condition and deterioration.


H300105 4. NACELLE ANTI-ICING DUCT

a. Detail inspect nacelle anti-ice temperature switch, piccolo tube and clamps (where visible) for condition.

a. Perform ENGINE AIR INTAKES - FUNCTIONAL TEST WITHOUT ENGINE OPERATION (Ref. Chapter 30-20-00).

b. Perform NACELLE ANTI-ICING DUCT VISUAL INSPECTION (Ref. Chapter 30-20-00).

05-20-03Page 624Jan 01/12 A2


RIGHT-HAND POWER PLANT, PYLON AND NACELLE




A. RIGHT-HAND POWER PLANT, PYLON AND NACELLE

H540204 1. PYLON NACELLE SEAL - Inspect seal for condition.

H540205 2. ENGINE/PYLON FIREWALL

a. Inspect firewall area for condition and presence/condition of sealant (Ref. Figure 607).

b. Inspect pylon bleed air, fuel, hydraulic and electrical plumbing and wire harnesses for condition and deterioration.


H300205 4. NACELLE ANTI-ICING DUCT

a. Detail inspect nacelle anti-ice temperature switch, piccolo tube and clamps (where visible) for condition.

a. Perform ENGINE AIR INTAKES - FUNCTIONAL TEST WITHOUT ENGINE OPERATION (Ref. Chapter 30-20-00).

b. Perform NACELLE ANTI-ICING DUCT VISUAL INSPECTION (Ref. Chapter 30-20-00).

A2 Jan 01/1205-20-03







H210022 1. CABIN PRESSURE CONTROL SYSTEM - Perform CABIN PRESSURE CONTROL SYSTEM CHECK (Ref. Chapter 21-00-00).

H210020 2. ENVIRONMENTAL CONTROL UNIT - Perform REFRIGERATION UNIT OPERATIONAL CHECK (Ref. Chapter 21-50-00). NOTE: Not required if ENVIRONMENTAL SYSTEM CHECK (RK-1 AND AFTER) is performed.

H360001 3. BLEED AIR SYSTEM CHECK VALVES - Perform BLEED AIR SYSTEM CHECK VALVE OPERATIONAL CHECK (Ref. Chapter 21-10-00).

H300010 4. WING LEADING EDGE ANTI-ICE SYSTEM - Perform WING LEADING EDGE ANTI-ICE ADJUSTMENT/TEST (Ref. Chapter 30-10-00).

H240011 5. INVERTER SYSTEM - Perform INVERTER SYSTEM FUNCTIONAL TEST (Ref. Chapter 24-20-00).

05-20-03Page 626Jan 01/12 A2


Entrance Door Inspection(RK-1 and After)

Figure 601

A2 Jan 01/1205-20-03


Nose Landing Gear Bearing Inspection(RK-1 and After)

Figure 602

05-20-03Page 628Jan 01/12 A2


Main Landing Gear Bearing Inspection(RK-1 and After)

Figure 603

A2 Jan 01/1205-20-03


Main Landing Gear Fittings Inspection(RK-1 and After)

Figure 604

RJ05B 023366AB.AI

B A

DETAIL B

DETAIL A


NOTE: CHECK FOR INTERFERENCE BETWEEN ACTUATOR BRACKET AND WING SPAR.

05-20-03Page 630Jan 01/12 A2


Horizontal Stabilizer (Hinges and Hinge Bolts) Inspection(RK-1 and After)

Figure 605 (Sheet 1 of 2)

A2 Jan 01/1205-20-03


Horizontal Stabilizer (Elevator Linkage) Inspection(RK-1 and After)

Figure 605 (Sheet 2 of 2)

05-20-03Page 632Jan 01/12 A2


Horizontal Stabilizer Front and Rear Spar and Fitting Inspection(RK-1 and After)

Figure 606

A2 Jan 01/1205-20-03


Pylon Firewall Inspection(RK-1 and After)

Figure 607

RK05B 086010AA.AI

B

A

DETAIL A

DETAIL B

05-20-03Page 634Jan 01/12 A2


Bleed Air Components Inspection(RK-1 and After)

Figure 608

A

DETAIL ARK05B 060906AB.AI

312FR*

311RL*

NOTE: *RK-24 AND AFTER ONLY.

A2 Jan 01/1205-20-03


Spoiler Bracket (P/N 45A10152), Rear Spar Area (WCS 2513)(RK-1 and After)

Figure 609

A2 Jan 01/1205-20-04


60060060005-20-0

SCHEDULED IFA-C INSPECTIONS

PILOT'S COMPARTMENT




H560007 1. WINDSHIELD GLASS AND FRAME (Interior windshield trim panels removed)

a. Detail inspect windshield frame for cracks or structural damage, loose or missing fasteners and evidence of water leakage.

b. Detail inspect (using an optical prism) the periphery of the windshield screen and mounting holes for cracks or evidence of damage. (Refer to ASTM F2108-06 - Standard Practice for Inspection of Transparent Parts by Prism).

c. Inspect windshield seal, P/N 45A97010, for evidence of migration from under the windshield.

H530010 2. FLOOR PANELS

a. Inspect for corrosion and structural damage.

b. Detail inspect floor support assembly for corrosion and structural damage (Ref. Figure 601).

H270061 3. CONTROL COLUMN (Below Floor Panels)

a. Perform CONTROL COLUMN FREE PLAY CHECK (Ref. Chapter 27-30-00).

b. Detail inspect control columns, torque tube assembly and push rods for condition, interference, freedom of movement, seized bearings and sufficient engagement of rod ends (Ref. Chapter 27-30-00, Figure 206).

c. Detail inspect spoiler bellcranks and spoiler push rods for condition, interference, freedom of movement, seized bearings and sufficient engagement of rod ends.

H270039 4. FLIGHT CONTROL SECTOR MODULE

a. Detail inspect sector module assembly, control cables and push rods for condition, routing, freedom of movement, seized bearings and sufficient engagement of rod ends (Ref. Chapter 27-20-00, Figure 207).

05-20-04Page 602Jan 01/12 A2



H270039 4. FLIGHT CONTROL SECTOR MODULE (Continued)

b. Detail inspect rudder bungee and spoiler feel spring assembly for condition.

c. Detail inspect idler pulley and bracket installation (P/N 45A61341) for condition, cable routing, guide pin installation and freedom of movement.

H270042 5. RUDDER PEDALS (Below Floor Panels) (Ref. Chapter 27-20-00, Figure 207)

a. Detail inspect rudder pedals, rudder torque tube assembly and rudder and steering push rods for condition, freedom of movement. seized bearings and sufficient engagement of rods ends.

b. Detail inspect rudder bungee and feel spring assembly, bellcranks and push rods for condition, freedom of movement, seized bearings and sufficient engagement of rod ends.

c. Detail inspect brake master cylinders and hoses for condition and interference.

d. Detail inspect brake mixer valves and plumbing for condition.

H320032 6. EMERGENCY BRAKE - Detail inspect emergency brake lever and control cable mechanism, control valve assembly, springs and plumbing for condition.

H320023 7. EMERGENCY LANDING GEAR

a. Detail inspect emergency landing gear extension T-handle and cable assembly, forward quadrant assembly, attaching control cables and cable terminals, and support structure for condition (Ref. Figure 602).

b. Detail inspect emergency door close T-handle and cable assembly and plumbing for condition.

H760001 8. THRUST LEVER QUADRANT, FORWARD THRUST CONTROL CABLE, FORWARD BELLCRANK AND ENGINE CONTROL ROD ASSEMBLIES - Detail inspect for condition, routing, freedom of movement, seized bearings and sufficient engagement of rods ends.

SCHEDULED IFA-C INSPECTIONS (Continued)


A2 Jan 01/1205-20-04



H210036 9. VENTILATION BLOWER SYSTEM

a. Detail inspect ventilation blower and ducting for condition.

b. Perform VENTILATION BLOWER CHECK (Ref. Chapter 21-21-00).

H210029 10. CABIN PRESSURE CONTROL FILTER CARTRIDGE ASSEMBLY (Below Floor Panels) - Replace filter cartridge.

H210030 11. PRESSURIZATION CONTROL SYSTEM - Inspect plumbing for condition and routing.

H530013 12. MOISTURE DRAIN HOLES AND VALVES

a. Inspect drain holes for obstruction.

b. Inspect drain valves for condition.

H240004 13. ELECTRICAL EQUIPMENT (SIDE JUNCTION) PANEL, POWER RELAY PANEL, RESISTOR RELAY (LOAD SHED) PANEL, CIRCUIT BREAKER PANELS and ASSOCIATED WIRING - Detail inspect for condition, deterioration and evidence of overheating.

H240017 14. ELECTRICAL WIRING AND CONNECTORS (Below Floor Panels) - Detail inspect for condition, deterioration and evidence of overheating.

H280027 15. FUEL QUANTITY INDICATORS - Perform DRY CALIBRATION - WING AND FUSELAGE FUEL QUANTITY (Ref. Chapter 28-41-00).




05-20-04Page 604Jan 01/12 A2


CABIN SECTION



A. CABIN SECTION

H530029 1. FLOOR PANELS - Detail inspect for corrosion and structural damage.

H520032 2. MOISTURE DRAIN HOLES AND VALVES

a. Inspect drain holes for obstruction.

b. Inspect drain holes for condition.

H250007 3. SEAT RAILS AND ATTACHMENTS - Detail inspect seat rails and their attachments for condition and structural damage (Ref. Figure 603).

H520014 4. EMERGENCY EXIT DOOR (Emergency exit door removed)

a. Detail inspect emergency exit door seal for condition and deterioration.

b. Detail inspect emergency exit door latching mechanism and lock for condition.

c. Detail inspect the perimeter of emergency exit door (including attaching frames, intercostals, gussets, and skin) for cracks, loose or missing fasteners and any indication of structural damage (Ref. Figure 604).

d. Detail inspect the perimeter of fuselage emergency exit opening (including attaching frames, intercostals, gussets, and skin) for cracks, loose or missing fasteners and any indication of structural damage (Ref. Figure 605).

e. Detail inspect the fuselage emergency exit frame reinforcement clips for condition (Ref. Figure 605).

f. Detail inspect the emergency exit door inner skin and skin splices for condition.

H520015 5. MAIN ENTRANCE DOOR

a. Detail inspect main entrance door latching mechanism and lock for condition, security and wear (Ref. Figure 606).

b. Inspect door lock switches and wiring for condition.

A2 Jan 01/1205-20-04



H520015 5. MAIN ENTRANCE DOOR (Continued)

c. Inspect travel of entrance door lock switches. Refer to ENTRANCE DOOR LOCK SWITCHES ADJUSTMENT, Chapter 52-10-00.

H530011 6. FUSELAGE INNER SKIN AND SPLICE - Detail inspect fuselage inner skin and skin splice for condition (Ref. Figure 607).

H530012 7. AFT PRESSURE BULKHEAD

a. Detail inspect cabin side of aft pressure bulkhead structure for cracks, loose or missing fasteners, corrosion and evidence of structural damage (Ref. Figure 608).

b. Detail inspect aft pressure bulkhead check valves [F.S. 322.4 (8190)] for condition, obstruction and freedom of movement (Ref. Figure 609).

H240014 8. ELECTRICAL COMPONENTS - AREA INSPECTION (With Interior Panels Removed)

a. Inspect cabin sidewall and toilet area electrical components, wiring and connectors for condition, deterioration and evidence of overheating.

b. Detail inspect L/H and R/H control junction boxes for condition and indication of damage to the PCB cards, mounting or surrounding support structure. (Removal of junction boxes not required)

c. Inspect PCB electrical wiring and connectors for condition, deterioration and evidence of overheat.

H210023 9. ENVIRONMENTAL SYSTEM

a. Perform WING ANTI-ICE OUTER CONTAINMENT DUCT PRESSURE SWITCH FUNCTIONAL TEST (Ref. Chapter 30-10-00).

b. Detail inspect wing anti-ice and conditioned air ducting for condition, specified clearance from insulation materials and wire harnesses, deterioration and evidence of overheating. NOTE: Assure specified clearances are maintained the entire length of the ducting.



05-20-04Page 606Jan 01/12 A2



H210008 10. VAPOR CYCLE COOLING SYSTEM - EVAPORATORS (RK-78, RK-87 and After)

a. Inspect forward and aft evaporator module plumbing and wiring for condition within cabin area and at the aft pressure bulkhead pass through locations.

b. Detail inspect the forward and aft evaporator Lexan housing assemblies at the junction of the shroud assembly and the escutcheon for signs of separation, cracks and condensate leakage (Ref. Enviro Systems CMM, Chapter 21-00-12 in the Component Maintenance Manual, 128-590001-81 or subsequent).

c. Inspect the forward and aft evaporator coil fins for damage and cleanliness.

d. Inspect the forward and aft evaporator blower motor, wheel and scroll for cleanliness, smooth (vibration free) operation (Ref. Enviro Systems CMM, Chapter 21-00-12, Section 3.3 in the Component Maintenance Manual, 128-590001-81 or subsequent).

e. Inspect the forward and aft evaporator module cold air ducting for condition.

f. Inspect the forward and aft evaporator drain outlets and tubing for obstruction and ensure drain tubing routing will allow complete moisture drainage.

g. Verify 25 ± 5°F drop across the forward and aft evaporator coils (Ref. Enviro Systems CMM, Chapter 21-00-12 Section 12.1 in the Component Maintenance Manual, 128-590001-81 or subsequent).

H280011 11. FUSELAGE AUXILIARY FUEL STORAGE AREAS

a. Detail inspect fuel cell interior for condition, evidence of fuel cell detachment and foreign material.

b. (RK-106 thru RK-507 with Kit 128-9008 and 128-9009 Installed; RK-508 thru RK-529 with Kit 128-9009 Installed; RK-530 and After) - Detail inspect fuel cell interior for indication of fungal or microbial contamination (Ref. Chapter 28-11-00).

c. Detail inspect fuel vent valves and vent float valves for condition and freedom of movement.



A2 Jan 01/1205-20-04



H280011 11. FUSELAGE AUXILIARY FUEL STORAGE AREAS (Continued)

d. Detail inspect fuel vent plumbing, support brackets, hoses, clamps, bonding jumpers and clamshell couplings for condition.

e. Detail inspect fuel probe, mount bracket and wire harness for condition (located in the right fuel cell only).

f. Detail inspect interconnect tubes, hoses, clamps and bonding jumpers for condition.

g. Inspect fuel storage area access doors and nutplates for condition.

H280018 12. FUSELAGE AUXILIARY FUEL TANK ASSEMBLY (P/N 128-920185-1, -7, -19 and 128-920186-1, -7, -19) - Inspect the Auxiliary Fuel Tank Assembly (Outer Tank Structure Only) for corrosion, fatigue, cracks, loose or failed fasteners and general condition. Use borescope as necessary. (Ref. Figure 610).

H270041 13. ELEVATOR, RUDDER AND SPOILER CONTROL CABLES, PULLEYS AND BRACKETS - Detail inspect for condition, routing and broken cable strands.

H320031 14. EMERGENCY LANDING GEAR CABLES - Perform EMERGENCY LANDING GEAR SYSTEM CABLE TENSION CHECK (Ref. Chapter 32-30-00).

H290006 15. HYDRAULIC PLUMBING - Detail inspect for condition and leakage.




05-20-04Page 608Jan 01/12 A2


FORWARD FUSELAGE



A. FORWARD FUSELAGE

H240007 1. ELECTRICAL AND AVIONICS COMPONENTS - AREA INSPECTION (Forward of the pressure bulkhead; Avionics removal not required)

a. Detail inspect electrical and avionics components, wiring and connectors for condition, deterioration and evidence of overheating.

b. Detail inspect avionics shelves and mounting for condition.

c. Detail inspect pitot and static system plumbing for condition, deterioration and routing.

d. Detail inspect plumbing, coax and wiring for condition at the forward pressure bulkhead feed through locations.

H530014 2. FORWARD PRESSURE BULKHEAD

a. Detail inspect forward pressure bulkhead and center windshield post attachment for cracks, loose or missing fasteners, corrosion and evidence of structural damage (Ref. Figure 611).

b. Detail inspect nose landing gear wheel well stringers located in the upper corners for cracks (Ref. Figure 612).


A2 Jan 01/1205-20-04


MIDFUSELAGE



A. MIDFUSELAGE

H280012 1. MID- FUSELAGE FUEL STORAGE AREAS

a. Detail inspect fuel cell interior for condition, evidence of fuel cell detachment and foreign material.

b. (RK-106 thru RK-507 with Kit 128-9008 and 128-9009 Installed; RK-508 thru RK-529 with Kit 128-9009 Installed; RK-530 and After) - Detail inspect fuel cell interior for indication of fungal or microbial contamination (Ref. Chapter 28-11-00).

c. Detail inspect transfer pumps, fuel level float switches and mount brackets for condition and obstruction.

d. Detail inspect engine fuel feed plumbing, transfer fuel plumbing and check valve and motive flow plumbing for condition.

e. Detail inspect fuel vent float valve assembly for condition and freedom of movement.

f. Detail inspect fuel vent plumbing, support brackets, hoses, clamps, bonding jumpers and clamshell couplings for condition.

g. Detail inspect inboard and outboard fuel probes, mount brackets and wire harness conduit for condition (located in left fuel cell only).

h. Detail inspect interconnect tubes, hoses, clamps and bonding jumpers for condition.

i. Detail inspect interconnect tube check valves for condition and freedom of movement.

j. Detail inspect acceleration check valves for condition and freedom of movement.

k. Inspect fuel storage area access door and nutplates for condition.

H280025 2. FUEL FILL SYSTEM FLAME ARRESTOR (P/N 128-920212) - Remove and inspect for cracks and obstruction.

05-20-04Page 610Jan 01/12 A2


A. MIDFUSELAGE (Continued)

H270038 3. SPOILER SYSTEM

a. Inspect spoiler mixer assembly, push rods and left and right sector assembly for condition, freedom of movement, seized bearings and sufficient engagement of rod ends.

b. Inspect speed brake actuator, hydraulic plumbing and limit switches condition.

c. Perform the complete SPOILER CONTROL SYSTEM FUNCTIONAL TEST (Ref. Chapter 27-60-00).

d. Perform SPOILER SERVO CABLE TENSION ADJUSTMENT (Ref. Chapter 22-13-00).

e. Perform spoiler SERVO CABLE CLEARANCE CHECK (Ref. Chapter 22-13-00).

f. Perform the complete SPEED BRAKE SYSTEM ADJUSTMENT/TEST procedure (Ref. Chapter 27-60-00).

H530016 4. FRAME REINFORCEMENT CLIPS (45A33273), FS 279.4 (7096) - Detail inspect for cracks and any indication of structural damage (Ref. Figure 613).

H530017 5. EMERGENCY GEAR DOWN BRACKET ASSEMBLY ATTACH CLIP, FS 279.4 (7096) - Detail inspect for cracks and any indication of structural damage (Ref. Figure 614).

H530018 6. KEEL STRUCTURE - Inspect keel for cracks, loose or missing fasteners and evidence of structural damage (Ref. Figure 615).

H570009 7. WING ATTACH FITTINGS

a. Inspect for exfoliation, corrosion, wear and installed condition.

b. Inspect adjacent area for corrosion and any evidence of structural damage.

H530019 8. FUSELAGE SKIN - Detail inspect for cracks, loose or missing fasteners and indications of structural damage, especially around entrance door and escape hatch corners.

H530020 9. LOWER FRAME AND SPLICE, FS 307.2 (7803) - Detail inspect for cracks and any indication of structural damage (Ref. Figure 616).




A2 Jan 01/1205-20-04


LEFT-HAND WING



A. LEFT-HAND WING

H270062 1. FLAP OPERATION (Perform in conjunction with RH wing) - Perform the complete FLAP CONTROL SYSTEM FUNCTIONAL TEST (Ref. Chapter 27-50-00).

H270143 2. SPOILER FAIRLEADS, WS 54.2 (1377) - Inspect for fraying, wear and security (Ref. Figure 617).

H270114 3. ROLL TRIM OPERATION - Perform the complete ROLL TRIM TESTING procedure (Ref. Chapter 27-10-00).

H570111 4. WING FUEL STORAGE AREA INSPECTION

a. Detail inspect integral wing tank ribs, stringers and skins for cracks, loose or missing fasteners, corrosion, deteriorated sealant and evidence of structural damage. Ensure compartments are free of foreign materials.

b. (RK-106 thru RK-507 with Kit 128-9008 and 128-9009 Installed; RK-508 thru RK-529 with Kit 128-9009 Installed; RK-530 and After) - Detail inspect integral wing tank compartments for indication of fungal or microbial contamination (Ref. Chapter 28-11-00).

c. Detail inspect wing ribs at BP 35(890), WS 50.6 (1285) and WCS 65.4 (1660) and drain holes on stringers for cracks, loose or missing fasteners and any indication of structural damage. (Ref. Figure 618).

H280126 5. FUEL LEVEL CONTROL SHUT-OFF VALVE (P/N 1323-518100M2) - Inspect for condition, obstruction and freedom of movement. Ensure presence of two washers on each mounting bolt (Ref. Figure 619).

05-20-04Page 612Jan 01/12 A2


A. LEFT-HAND WING (Continued)

H280116 6. FUEL VENT SYSTEM

a. Inspect the inboard forward wing float vent valve for condition, deterioration and freedom of movement.

b. Inspect the inboard aft wing float vent valve for condition, deterioration and freedom of movement.

c. Inspect the wing surge space vent valve and flapper valve for condition, deterioration and freedom of movement.

d. Inspect fuel vent plumbing, hoses, clamps and bonding jumpers for condition and deterioration.

H280106 7. FUEL COLLLECTOR TANK

a. Detail inspect fuel tank structure for cracks, loose or missing fasteners and evidence of structural damage.

b. Inspect collector tank flapper valves (P/N 16C112) for condition, obstruction and freedom of movement.

c. Detail inspect electric boost pump, primary jet pump, inlet screens and pump mounting brackets for condition and obstruction.

d. Inspect low level float switch (P/N 45A48013) for condition, obstruction and freedom of movement.

e. Detail inspect electric boost pump plumbing, primary jet pump plumbing, manifold, check valves, clamps and bonding jumpers for condition.

f. Detail inspect forward and aft transfer jet pumps and pick-up tubes for condition and obstruction.


h. Perform PRESSURE RELIEF VALVE OPERATIONAL CHECK AND REPAIR (Ref. Chapter 28-11-00).

H280117 8. WING OVERPRESSURE SWITCH - Remove and perform WING OVERPRESSURE SWITCH TEST (Ref. Chapter 28-41-00).




A2 Jan 01/1205-20-04


RIGHT-HAND WING



A. RIGHT-HAND WING

H270062 1. FLAP OPERATION (Perform in conjunction with LH wing) - Perform the flap system OPERATIONAL TEST (Ref. Chapter 27-50-00).

H270243 2. SPOILER FAIRLEADS, WS 54.2 (1377) - Inspect for fraying, wear and security (Ref. Figure 617).

H270214 3. ROLL TRIM OPERATION - Perform the complete ROLL TRIM TESTING procedure (Ref. Chapter 27-10-00).

H570211 4. WING FUEL STORAGE AREA - AREA INSPECTION

a. Detail inspect integral wing tank ribs, stringers and skins for cracks, loose or missing fasteners, corrosion, deteriorated sealant and evidence of structural damage. Ensure compartments are free of foreign materials.

b. (RK-106 thru RK-507 with Kit 128-9008 and 128-9009 Installed; RK-508 thru RK-529 with Kit 128-9009 Installed; RK-530 and After) - Detail inspect integral wing tank compartments for indication of fungal or microbial contamination (Ref. Chapter 28-11-00).

c. Detail inspect wing ribs at BP 35 (890), WS 50.6 (1285) and WCS 65.4 (1660) and drain holes on stringers fro cracks, loose or missing fasteners and any indication of structural damage. (Ref. Figure 618).

H280226 5. FUEL LEVEL CONTROL SHUT-OFF VALVE (P/N 1323-518100M2) - Inspect for condition, obstruction and freedom of movement. Ensure presence of two washers on each mounting bolt (Ref. Figure 619).

05-20-04Page 614Jan 01/12 A2


A. RIGHT-HAND WING (Continued)

H280216 6. FUEL VENT SYSTEM

a. Inspect the inboard forward wing float vent valve for condition, deterioration and freedom of movement.

b. Inspect the inboard aft wing float vent valve for condition, deterioration and freedom of movement.

c. Inspect the wing surge space vent valve and flapper valve for condition, deterioration and freedom of movement.

d. Inspect fuel vent plumbing, hoses, clamps and bonding jumpers for condition and deterioration.

H280206 7. FUEL COLLECTOR TANK

a. Detail inspect fuel tank structure for cracks, loose or missing fasteners and evidence of structural damage.

b. Inspect collector tank flapper valves (P/N 16C112) for condition, obstruction and freedom of movement.

c. Detail inspect electric boost pump, primary jet pump, inlet screens and pump mounting brackets for condition and obstruction.

d. Inspect low level float switch (P/N 45A48013) for condition, obstruction and freedom of movement.

e. Detail inspect electric boost pump plumbing, primary jet pump plumbing, manifold, check valves, clamps and bonding jumpers for condition.

f. Detail inspect forward and aft transfer jet pumps and pick-up tubes for condition and obstruction.


h. Perform PRESSURE RELIEF VALVE OPERATIONAL CHECK AND REPAIR (Ref. Chapter 28-11-00).

H280217 8. WING OVERPRESSURE SWITCH - Remove and perform WING OVERPRESSURE SWITCH TEST (Ref. Chapter 28-41-00).




A2 Jan 01/1205-20-04






H320123 1. LEFT MAIN GEAR ATTACH FITTINGS, SUPPORTING SPARS, RIB AND UPLOCK FITTING - Inspect rear spar and fitting for cracks, missing fasteners, corrosion and evidence of structural damage (Ref. Figure 620).

H520113 2. LEFT MAIN LANDING GEAR DOOR BEAMS AND FITTINGS - Detail inspect the beams and fittings for cracks, loose or missing fasteners and evidence of damage.

H320126 3. LEFT MAIN WHEEL WELL - AREA INSPECTION (Panels Removed)

a. Inspect fuel plumbing and fittings for condition and evidence of damage.

b. Inspect fuel transfer low pressure switch (S129) and mounting for condition.

c. Inspect electrical wire harnesses for condition and deterioration.

d. Inspect MLG inboard door actuator and plumbing for condition and evidence of leakage.

e. Inspect emergency landing gear extension cables. pulleys and bellcranks for condition, routing and broken strands.

H320223 4. RIGHT MAIN GEAR ATTACH FITTINGS, SUPPORTING SPARS, RIB AND UPLOCK FITTING - Inspect rear spar and fitting for cracks, missing fasteners, corrosion and evidence of structural damage (Ref. Figure 620).

H520213 5. RIGHT MAIN LANDING GEAR DOOR BEAMS AND FITTINGS - Detail inspect the beams and fittings for cracks, loose or missing fasteners and evidence of damage.

H320226 6. RIGHT MAIN WHEEL WELL - AREA INSPECTION (Panels Removed)

a. Inspect fuel plumbing and fittings for condition and evidence of damage.

b. Inspect fuel transfer low pressure switch (S129) and mounting for condition.

05-20-04Page 616Jan 01/12 A2



H320226 6. RIGHT MAIN WHEEL WELL - AREA INSPECTION (Panels Removed) (Continued)

c. Inspect electrical wire harnesses for condition and deterioration.

d. Inspect MLG inboard door actuator and plumbing for condition and evidence of leakage.

e. Inspect emergency landing gear extension cables. pulleys and bellcranks for condition, routing and broken strands.

H320024 7. BRAKE SYSTEM

a. Perform PARKING BRAKE SYSTEM FUNCTIONAL CHECK (POWER MODE) (Ref. Chapter 32-40-00).

b. Perform EMERGENCY BRAKE SYSTEM FUNCTIONAL CHECK (Ref. Chapter 32-40-00).

c. Perform POWER BRAKE ANIT-SKID CONTROL VALVE FILTER CLEANING (Ref. Chapter 32-40-00).

d. Perform BRAKE SYSTEM FUNCTIONAL TESTING procedure (Ref. Chapter 32-40-00).




A2 Jan 01/1205-20-04


AFT FUSELAGE



A. AFT FUSELAGE

H530034 1. FUSELAGE SKIN - Detail inspect for cracks, loose or missing fasteners and indication of structural damage.

H210010 2. ENVIRONMENTAL CONTROL UNIT (ECU) AND DUCTING

a. Remove ECU (also known as Refrigeration Unit) and detail inspect the primary and secondary heat exchanger for condition, corrosion and obstruction (Ref. Chapter 21-50-00).

b. Remove and inspect bleed air check valves (P/N 45AS63023) for condition and freedom of movement.

c. Inspect ECU ram air inlet and discharge ducts for condition and obstruction.

d. (RK-1 thru RK-109, except RK-98) - Detail inspect duct temperature sensors, high limit temperature sensors, pressure regulator and associated plumbing for condition, cracks or eroded housings and evidence of air leakage (Ref. Figure 621 and Figure 622).

e. (RK-98, RK-110 and After) - Detail inspect duct temperature sensors, high limit temperature sensors and their associated wiring and plumbing for condition and evidence of air leakage.

f. Inspect conditioned air ducting, plenums and insulation material for condition and evidence of air leakage.

g. Inspect aft fuselage insulation blanket for torn or punctured material and evidence of hot air leakage (sooting and/or discoloration). Investigate potential leaks.

h. Inspect the four thermal switches (S187) (S188) (S189) (S190) and wire harnesses for condition, obstruction and deterioration.

i. Perform BLEED AIR HIGH TEMPERATURE SWITCH(350 °F) OPERATIONAL CHECK (Ref. Chapter 21-50-00).

j. Perform BLEED AIR OVERTEMPERATURE SWITCH (400 °F) OPERATIONAL CHECK (Ref. Chapter 21-50-00).

05-20-04Page 618Jan 01/12 A2



H210010 2. ENVIRONMENTAL CONTROL UNIT (ECU) AND DUCTING (Continued)

k. BLEED AIR OVERPRESSURE SWITCH - Perform BLEED AIR OVERPRESSURE SWITCH OPERATIONAL CHECK (Ref. Chapter 21-50-00).

H280019 3. AFT FUSELAGE FUEL STORAGE AREA

a. Remove and inspect aft fuselage safety foam for condition and deterioration (Ref. Chapter 28-11-00).

b. Detail inspect fuel cell interior for condition, evidence of fuel cell detachment and foreign material.

c. (RK-106 thru RK-507 with Kit 128-9008 and 128-9009 Installed; RK-508 thru RK-529 with Kit 128-9009 Installed; RK-530 and After) - Detail inspect fuel cell interior for indication of fungal or microbial contamination (Ref. Chapter 28-11-00).

d. Detail inspect fuel vent valve for condition and freedom of movement.

e. Detail inspect fuel vent interconnect tube, clamps, and bonding jumpers for condition.

f. Detail inspect flapper check valve, interconnect tube, hoses, clamps and bonding jumpers for condition.

g. Inspect fuel storage area access door and nutplates for condition.

H280020 4. FILLER TANK FUEL STORAGE AREA

a. Remove and inspect filler tank safety foam for condition and deterioration (Ref. Chapter 28-11-00).

b. Detail inspect fuel cell interior for condition, evidence of fuel cell detachment and foreign material.

c. (RK-106 thru RK-507 with Kit 128-9008 and 128-9009 Installed; RK-508 thru RK-529 with Kit 128-9009 Installed; RK-530 and After) - Detail inspect fuel cell interior for indication of fungal or microbial contamination (Ref. Chapter 28-11-00).

d. Detail inspect fuel vent valve for condition and freedom of movement.



A2 Jan 01/1205-20-04



H280020 4. FILLER TANK FUEL STORAGE AREA (Continued)

e. Detail inspect fuel vent interconnect tube, clamps, and bonding jumpers for condition.

f. Detail inspect acceleration check valve, interconnect tube, hoses, clamps and bonding jumpers for condition.

g. Inspect fuel storage area access door and nutplates for condition.

H280008 5. FLAME ARRESTER (P/N 128-920211) - Remove and inspect for cracks and obstructions.

H280009 6. ANTI-VAPOR SYSTEM - Detail inspect anti-vapor system flex ducts for condition and absence of trapped fluid.

H280010 7. VENT SURGE TANK - Inspect vent surge tank and plumbing for condition.

H530022 8. FORWARD ENGINE CARRY-THROUGH BEAM - Using a borescope, detail inspect the yoke/carry-through beam joints for cracks, loose or missing fasteners (Ref. Figure 623).

H260004 9. FIRE DETECTION SYSTEM - Perform FIRE DETECTION SYSTEM FUNCTIONAL TEST (RK-1 AND AFTER) (Ref. Chapter 26-10-00).


a. Perform FIRE EXTINGUISHER ACTUATOR CARTRIDGE/SQUIB INSPECTION (Ref. Chapter 26-20-00).

b. Perform NACELLE FIRE EXTINGUISHING SYSTEM FUNCTIONAL TEST (RK-1 AND AFTER) (Ref. Chapter 26-20-00).

H210012 11. VAPOR CYCLE COOLING SYSTEM - COMPRESSOR CONDENSER MODULE (RK-78, RK-87 and After)

a. Inspect compressor drive belt cover for condition.

b. Remove and inspect compressor drive belt for condition, deterioration and evidence of improper tracking.

c. Inspect compressor pulley, shaft and shaft seal for condition.



05-20-04Page 620Jan 01/12 A2



H210012 11. VAPOR CYCLE COOLING SYSTEM - COMPRESSOR CONDENSER MODULE (RK-78, RK-87 and After) (Continued)

d. Perform COMPRESSOR BEARING INSPECTION (Ref. Enviro System CMM, Chapter 21-00-12, Section 12.4 in the Component Maintenance Manual, 128-590001-81 or subsequent).

e. Inspect drive motor brushes for condition and calculate remaining brush life (Ref. Enviro System CMM, Chapter 21-00-12, Section 3.4 in the Component Maintenance Manual, 128-590001-81 or subsequent). Replace brushes if necessary.

f. Inspect drive motor brush holders and commutator for condition, arching, heat distortion and contamination.

g. Perform MOTOR INSULATION RESISTANCE CHECK (Ref. Enviro System CMM, Chapter 21-00-12, Section 12.2 in the Component Maintenance Manual, 128-590001-81 or subsequent).

h. Perform MOTOR BEARING INSPECTION (Ref. Enviro System CMM, Chapter 21-00-12, Section 12.3 in the Component Maintenance Manual, 128-590001-81 or subsequent).

i. Inspect condenser fan, condenser coil and coil fins for condition, accumulation of dirt and damaged fan blades or coil fins.

j. Inspect condenser fan shroud and the condenser outlet shroud for cracking and/or separation between the shroud and the condenser coil.

k. Inspect receiver/dryer assembly, mounting and plumbing for condition.

l. Install and tension compressor drive belt (Ref. Chapter 21-51-00).

m. Verify refrigerant charge level and operating pressures.

H270025 12. CONTROL CABLES

a. Perform RUDDER SERVO CABLE TENSION ADJUSTMENT (Ref. Chapter 22-13-00).



A2 Jan 01/1205-20-04



H270025 12. CONTROL CABLES (Continued)

b. Perform rudder SERVO CABLE CLEARANCE CHECK (Ref. Chapter 22-13-00).

c. Perform ELEVATOR SERVO CABLE TENSION ADJUSTMENT (Ref. Chapter 22-13-00).

d. Perform elevator SERVO CABLE CLEARANCE CHECK (Ref. Chapter 22-13-00).




05-20-04Page 622Jan 01/12 A2


VERTICAL STABILIZER




H550014 1. VERTICAL STABILIZER - Detail inspect vertical stabilizer skin for cracks, loose or missing fasteners and any indication of structural damage.

H530023 2. FAIRING OF VERTICAL STABILIZER-TO-FUSELAGE - Inspect for cracks, loose or missing fasteners and any indication of structural damage.

H530024 3. VERTICAL STABILIZER FRONT SPAR ATTACHMENT AND FRAME - Using a 10x magnifying glass, detail inspect for cracks (especially at attaching points, doubler and stringer cutout through frame), loose or missing fasteners and any indication of structural damage. Pay particular attention to cracks emitting from fastener holes (Ref. Figure 624).

H530025 4. VERTICAL STABILIZER REAR SPAR ATTACHMENT AND FRAME - Using a 10x magnifying glass, detail inspect for cracks (especially at attaching points and doubler), loose or missing fasteners and any indication of structural damage. Pay particular attention to cracks emitting from fastener holes (Ref. Figure 624).

H270009 5. RUDDER OPERATION - Perform the complete RUDDER CONTROL SYSTEM FUNCTIONAL TESTS procedure (Ref. Chapter 27-20-00).

H270010 6. RUDDER TRIM OPERATION - Perform the complete RUDDER TRIM SYSTEM ADJUSTMENT/TEST procedure (Ref. Chapter 27-20-00).


A2 Jan 01/1205-20-04






H550009 1. FRONT AND REAR SPAR AND FITTINGS - Remove (4) inspection hole covers. Using a borescope inspect for cracks and loose or failed fasteners at the forward and aft spar locations (Ref. Figures 625 and Figure 626).

H550013 2. HORIZONTAL STABILIZER STRINGERS AND SKINS - Horizontal Stabilizer Station (HSS) 0.00 to HSS 11.81 (300) - Detail inspect for cracks, loose or missing fasteners in the stringers and skins.

H550008 3. AFT PIVOT FITTING ASSEMBLY - Detail inspect for condition.

H550010 4. ELEVATOR OPERATION - Perform complete ELEVATOR ADJUSTMENT/TEST procedure (Ref. Chapter 27-30-00).

H270003 5. PITCH TRIM OPERATION - Perform the complete PITCH TRIM SYSTEM FUNCTIONAL TEST (Ref. Chapter 27-40-00).


05-20-04Page 624Jan 01/12 A2







H210021 1. ENVIRONMENTAL SYSTEM - Perform ENVIRONMENTAL SYSTEM CHECK (RK-1 AND AFTER) (Ref. Chapter 21-00-00).

H240018 2. DC GENERATION AND CONTROL SYSTEM - Perform DC GENERATION AND CONTROL SYSTEM FUNCTIONAL TEST (Ref. Chapter 24-30-00).

H280026 3. FUEL SYSTEM - Perform FUEL PUMP OPERATIONAL TEST WITH ENGINE OPERATION (Ref. Chapter 28-20-00).

A2 Jan 01/1205-20-04


Pilots Compartment Floor Assembly Inspection(RK-1 and After)

Figure 601

RK05B 086011AB.AI

A

DETAIL A


05-20-04Page 626Jan 01/12 A2


Emergency Extension System - Door/Cable Ends and Quadrant Inspection(RK-1 and After)

Figure 602

A2 Jan 01/1205-20-04


Seat Rail Attachment Inspection(RK-1 and After)

Figure 603

RK05B 086097AA.AI

DETAIL A

A

NOTE: ARROWS SHOW POINTS OF INSPECTION FOR TYPICAL SEAT RAIL ATTACHMENTS.

05-20-04Page 628Jan 01/12 A2


Emergency Exit Door Inspection(RK-1 and After)

Figure 604

A2 Jan 01/1205-20-04


Emergency Exit Inspection(RK-1 and After)

Figure 605

RJ05B 084274AB.AI

B

B

B

B

A

DETAIL BDETAIL C

DETAIL A

C

C

TYPICAL CLIP SHOWN

(RK-24 AND AFTER)

(RK-1 AND AFTER)

NOTE:ARROWS SHOW POINTS OF INSPECTION

05-20-04Page 630Jan 01/12 A2


Main Entrance Door Inspection(RK-1 and After)

Figure 606

A2 Jan 01/1205-20-04


Fuselage Inner Skin and Cover Inspection(RK-1 and After)

Figure 607

05-20-04Page 632Jan 01/12 A2


Aft Pressure Bulkhead Inspection (RK-1 and After)

Figure 608

A2 Jan 01/1205-20-04


Aft Pressure Bulkhead Check Valves FS 322.4 (8190) Inspection(RK-1 and After)

Figure 609

05-20-04Page 634Jan 01/12 A2


Fuselage Fuel Tank Locator(RK-1 and After)

Figure 610

A2 Jan 01/1205-20-04


Forward Pressure Bulkhead Inspection(RK-1 and After)

Figure 611

RK05B 070768AA.AI

BA

DETAIL B

DETAIL A

CENTER WINDSHIELD POST ATTACHMENT


05-20-04Page 636Jan 01/12 A2


Nose Landing Gear Wheel Well Inspection(RK-1 and After)

Figure 612

A2 Jan 01/1205-20-04


Frame Reinforcement Clips FS 279.4 (7096) Inspection(RK-1 and After)

Figure 613

05-20-04Page 638Jan 01/12 A2


Emergency Gear Down Bracket Assembly Attach Clip Inspection(RK-1 and After)

Figure 614

A2 Jan 01/1205-20-04


Keel Assembly Inspection(RK-1 and After)

Figure 615

A

B

RK05B 082445AA.AI

DETAIL B

DETAIL A

05-20-04Page 640Jan 01/12 A2


Lower Frame and Splice FS 307.2 (7803) Inspection(RK-1 and After)

Figure 616

A2 Jan 01/1205-20-04


Spoiler Fairleads Inspection(RK-1 and After)

Figure 617

05-20-04Page 642Jan 01/12 A2


Wing Ribs and Stringers Inspection(RK-1 and After)

Figure 618

RK05B 022602AC.AI

B

A

DETAIL B

DETAIL A

RK-1 THRU RK-46 ONLY

RIB REMOVED FOR CLARITY

1/4" (6.35)

BP 35 (890)

WS 50.6 (1285)

WCS 65.4 (1660)

THE '(s) IN DETAIL A SHOW THE APPROXIMATE LOCATIONS OF THE STRINGER DRAIN HOLES THAT ARE NEAR THE SPECIFIED WING STATIONS.

NOTE:

TYPICAL STRINGER DRAIN HOLE 8-PLACES (RK-1 THRU RK-46) 6-PLACES (RK-47 AND AFTER)

A2 Jan 01/1205-20-04


Fuel Level Control Shut-Off Float Valve (P/N 1323-518100M2) Inspection(RK-1 and After)

Figure 619

RK05B 070769AA.AI

A

DETAIL A

05-20-04Page 644Jan 01/12 A2


Main Landing Gear Fittings Inspection(RK-1 and After)

Figure 620

RJ05B 023366AB.AI

B A

DETAIL B

DETAIL A


NOTE: CHECK FOR INTERFERENCE BETWEEN ACTUATOR BRACKET AND WING SPAR.

A2 Jan 01/1205-20-04


Temperature Sensors Locator Inspection(RK-1 thru RK-109, except RK-98)

Figure 621

RK05B 080314AA.AI

A

DETAIL A

DETAIL B

B

HIGH-LIMIT TEMPERATURE

SENSORS

DUCT TEMPERATURE SENSOR

DUCT TEMPERATURE

SENSOR

05-20-04Page 646Jan 01/12 A2


Pressure Regulator Locator Inspection(RK-1 thru RK-109, except RK-98)

Figure 622

A2 Jan 01/1205-20-04


Forward Engine Carry-Through Inspection(RK-1 and After)

Figure 623

05-20-04Page 648Jan 01/12 A2


Vertical Stabilizer Spars Inspection(RK-1 and After)

Figure 624

A2 Jan 01/1205-20-04


Horizontal Stabilizer Front and Rear Spar and Fitting (Lugs) Inspection(RK-1 and After)

Figure 625

RK05B 082446AA.AI

EDDY CURRENT CROSSHATCH AREA

DETAIL A

"C" INSPECTION VIEW WITH BORESCOPE

VISUALLY INSPECT BOLT

"D" INSPECTION EDDY CURRENT

"D" INSPECTION EDDY CURRENT

A

05-20-04Page 650Jan 01/12 A2


Horizontal Stabilizer Front and Rear Spar and Fitting Inspection(RK-1 and After)

Figure 626

Jan 30/0905-20-05


60060060005-20-03

SCHEDULED IFA-D INSPECTIONS

SCHEDULED IFA-D INSPECTIONS

TASKCODE(REF) DATE MECH INSP

A. SCHEDULED D INSPECTIONS

H530026 1. LOWER FITTING OF WINDSHIELD CENTER POST - Perform detailed inspection for cracks, loose or missing fasteners and any indication of structural damage (Ref. Figure 601).

H560006 2. CABIN WINDOW FRAME - Perform detailed inspection for cracks, loose or missing fasteners and evidence of damage.

H530027 3. FRAME AND INTERCOSTALS BEHIND INNER SKIN - Perform detailed inspection for cracks, loose or missing fasteners and any indication of structural damage (Ref. Model 400/400A Structural Repair Manual, Chapter 53-10-47B).

H530028 4. CABIN FRAMES AND STRINGERS - Perform detailed inspection for leaks, loose or missing fasteners and any indication of structural damage.

H530030 5. ELEVATOR CONTROL-COLUMN-SUPPORT BOX (LH & RH) - Detail inspect for cracks in the stringers (P/N 45A61176) located under the support bracket. Inspect all four corners.

H320035 6. MAIN LANDING GEAR DOOR ACTUATOR FITTING - Perform a detailed inspection of the fitting for cracks using a 10x magnifying glass (Ref. Figure 602).

H540007 7. FORWARD AND AFT ENGINE CARRY-THROUGH - Remove the firewall blanket, and perform detailed inspection for cracks, loose or missing fasteners and evidence of structural damage through existing access holes. If engine is not removed, borescope inspection is required (Ref. Figure 603).

H540008 8. FRAME AND PYLON RIB - Perform detailed inspection for cracks, loose or missing fasteners and indications of structural damage (Ref. Figure 604).

H570012 9. MAIN FLAP CENTER RAIL ASSEMBLY AND CENTER FLAP ROLLERS - Perform detailed inspection for loose or missing fasteners, bolts of center flap roller for condition and any indication of structural damage (Ref. Figure 605).

05-20-05Page 602Jan 30/09


A. SCHEDULED D INSPECTIONS (Continued)

H570013 10. WING FRONT AND REAR SPAR FITTINGS - Perform detailed inspection of attachment fittings using Eddy current procedures. Refer to WING FORWARD AND AFT SPAR FITTING INSPECTION procedures, Chapter 57-40-00. (The wing does not have to be removed.)

H570014 11. FORWARD AND AFT CARRY-THROUGH (LUGS) (P/N 45A33511 and 45A33512) - Perform detailed inspection of lugs using Eddy current procedures. Refer to FORWARD AND AFT CARRY-THROUGH (LUGS) INSPECTION procedures, Chapter 57-40-00. (The wing does not have to be removed.)

H270044 12. RUDDER TORQUE TUBE ATTACHMENT AND TRIM TAB ACTUATOR ATTACHMENT

a. Perform a detailed inspection of the rudder torque tube attachment and rudder trim tab actuator attachments for cracks using a 10X magnifying glass. Focus on welds.

b. Detail inspect attaching bolts and surrounding structure for condition (Ref. Figure 606).

H550011 13. VERTICAL STABILIZER RIBS AND STRINGERS - Perform detailed inspection for cracks, loose or missing fasteners and any indications of structural damage.

H270045 14. ELEVATOR TORQUE TUBE

a. Perform detailed inspection of the elevator torque tube attachment for cracks with a 10X magnifying glass. Focus on welds.

b. Detail inspect attaching bolts and surrounding structure for condition (Ref. Figure 607).

H550012 15. HORIZONTAL STABILIZER FRONT AND REAR SPAR FITTINGS

a. Perform a detailed inspection of the rear spar fitting lugs using Eddy current. Refer to the HORIZONTAL STABILIZER REAR SPAR FITTINGS (LUGS) INSPECTION procedure in Chapter 55-50-00.

b. Inspect Horizontal Stabilizer pivot bolts and bushings for wear, corrosion, chemical intrusion and damage.

c. Visually inspect the surrounding area for loose or missing fasteners and any indication of structural damage.

SCHEDULED IFA-D INSPECTIONS (Continued)


Jan 30/0905-20-05



H280022 16. MIDFUSELAGE FUEL TANK (P/N 45A30901) - Perform detailed inspection for corrosion, fatigue cracks, loose or missing fasteners and general condition. Inspect fore and aft liners for cracks (Ref. Figure 608). NOTE: Initially, it is not necessary to completely remove the fuel bladder for this inspection, but access to the inside of the tank structure must be made (Note - corrosion will typically be at the bottom of the tank between the fuel bladder and the tank structure where moisture may have accumulated). The outer tank structure should be inspected thoroughly (borescope where required) to check for possible corrosion, fatigue cracks, loose or missing fasteners. In the event that corrosion is found during the initial phase of this inspection, a more thorough inspection, with the fuel bladder removed, is required.

H280023 17. AFT FUEL CELL COMPARTMENT (P/N 45A34891) - Perform detailed inspection for corrosion, fatigue cracks, loose or missing fasteners and general condition (Ref. Figure 608). NOTE: Initially, it is not necessary to completely remove the fuel bladder for this inspection, but access to the inside of the tank structure must be made (Note - corrosion will typically be at the bottom of the tank between the fuel bladder and the tank structure where moisture may have accumulated). The outer tank structure should be inspected thoroughly (borescope where required) to check for possible corrosion, fatigue cracks, loose or missing fasteners. In the event that corrosion is found during the initial phase of this inspection, a more thorough inspection, with the fuel bladder removed, is required.

H280024 18. AFT FUEL CELL COMPARTMENT BULKHEAD (P/N 45A34704) - Perform detailed inspection for corrosion, fatigue cracks, loose or missing fasteners and general condition (Ref. Figure 608). NOTE: Initially, it is not necessary to completely remove the fuel bladder for this inspection, but access to the inside of the tank structure must be made (Note - corrosion will typically be at the bottom of the tank between the fuel bladder and the tank structure where moisture may have accumulated). The outer tank structure should be inspected thoroughly (borescope where required) to check for possible corrosion, fatigue cracks, loose or missing fasteners. In the event that corrosion is found during the initial phase of this inspection, a more thorough inspection, with the fuel bladder removed, is required.



05-20-05Page 604Jan 30/09



H280018 19. FUEL TANK, FUSELAGE FILLER (128-920022) (Outer Tank Inspection Only) - Detail inspect for corrosion, fatigue cracks, loose or failed fasteners and general condition (Ref. Figure 608).

H520017 20. ENTRANCE DOOR - (Window installation, door frames, fittings, bolts, door mechanism and handle cases) - Perform detailed inspection for cracks, loose or missing fasteners and any indication of structural damage (Ref. Figure 609).

H520018 21. ENTRANCE DOOR LAND AND SUPPORTING FRAMES, LATCH PIN RECEPTACLES AND DOOR LAND GUIDES - Perform detailed inspection for cracks, loose or missing fasteners and any indication of structural damage. Inspect latch pin receptacles for cracks and structural damage (Ref. Figure 609).

H530031 22. AFT FUSELAGE BAGGAGE COMPARTMENT - Perform detailed inspection of compartment structure for cracks, corrosion and structural damage.

H210034 23. COMPRESSOR/CONDENSER MODULE (compressor/condenser module removed) (RK-78, RK-87 and After)

a. Perform detailed inspection of attach points to mounting plate for cracks, loose or missing fasteners and any other indication of structural damage.

b. Perform detailed inspection of support structure for cracks, loose or missing fasteners and any other indication of structural damage.

c. Perform detailed inspection of the support structure attachment to the airframe for cracks, loose or missing fasteners and any other indication of structural damage.

d. Perform detailed inspection of the air exhaust, skin doublers and adjacent skin (both inside and outside the airplane) between FS 437.6 (11115) and FS 457.3 (11615) for cracks, loose or missing fasteners and any other indication of structural damage.

H320036 24. NOSE LANDING GEAR SUPPORT FITTING (P/N 45A31311) - Perform a detailed inspection for cracks, loose or missing fasteners and evidence of structural damage (Ref. Figure 610).



Jan 30/0905-20-05


Forward Pressure Bulkhead Inspection(RK-1 and After)

Figure 601

RK05B 070768AA.AI

BA

DETAIL B

DETAIL A

CENTER WINDSHIELD POST ATTACHMENT


05-20-05Page 606Jan 30/09


Main Landing Gear Door Actuator Fitting Inspection(RK-1 and After)

Figure 602

Jan 30/0905-20-05


Forward Engine Carry-Through Inspection(RK-1 and After)

Figure 603

05-20-05Page 608Jan 30/09


Frame and Pylon Rib Inspection(RK-1 and After)

Figure 604

Jan 30/0905-20-05


Main Flap Center Rail Inspection(RK-1 and After)

Figure 605

05-20-05Page 610Jan 30/09


Rudder Torque Tube Attachment and Trim Tab Actuator Inspection(RK-1 and After)

Figure 606

Jan 30/0905-20-05


Elevator Torque Tube Inspection(RK-1 and After)

Figure 607

05-20-05Page 612Jan 30/09


Fuselage Fuel Tank Locator(RK-1 and After)

Figure 608

Jan 30/0905-20-05


Entrance Door Inspection(RK-1 and After)

Figure 609

05-20-05Page 614Jan 30/09


Nose Landing Gear Support Fitting (45A31311) Inspection(RK-1 and After)

Figure 610

Chapter_5

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