Document:

CUSTOMER SUPPORT VARIABLES

                                     between

                               THE BOEING COMPANY

                                       and

                            American Trans Air, Inc.

                   Supplemental Exhibit CS1 to Purchase Agreement Number 2285

<PAGE>

                           CUSTOMER SUPPORT VARIABLES

                                   relating to

                          BOEING MODEL 757-33N AIRCRAFT

Customer currently operates an aircraft of the same model as the Aircraft.  Upon
Customer's  request,  Boeing will  develop and  schedule a  customized  Customer
Support  Program to be  furnished  in support of the  Aircraft.  The  customized
program will be based upon and equivalent to the entitlements summarized below.

1.       MAINTENANCE TRAINING.
         --------------------

         1.1      Maintenance   Training  Minor  Model  Differences  Course,  if
                  required,   covering   operational,   structural   or  systems
                  differences between Customer's newly-purchased Aircraft and an
                  aircraft of the same model currently  operated by Customer;  1
                  class of 15 students;

         1.2      Training  materials,  if applicable,  will be provided to each
                  student. In addition, one set of training materials as used in
                  Boeing's  training  program,  including  visual aids, text and
                  graphics will be provided for use in  Customer's  own training
                  program.

2.       FLIGHT TRAINING.
         ---------------

         Boeing will provide,  if required,  one classroom course to acquaint up
         to 15 students with  operational,  systems and performance  differences
         between Customer's newly-purchased Aircraft and an aircraft of the same
         model currently operated by Customer.

         Any training  materials used in Flight Training,  if required,  will be
         provided for use in Customer's own training program.

3.       PLANNING ASSISTANCE.
         -------------------

         3.1      MAINTENANCE AND GROUND OPERATIONS.
                  ---------------------------------

                  Upon  request,   Boeing  will  provide   planning   assistance
                  regarding Minor Model Differences requirements for facilities,
                  tools and equipment.

         3.2      SPARES.
                  ------

                  Boeing will revise, as applicable,  the customized Recommended
                  Spares Parts List (RSPL) and Illustrated Parts Catalog (IPC).

4.       TECHNICAL DATA AND DOCUMENTS.
         ----------------------------

         Boeing  will  revise,  as  applicable,  technical  data  and  documents
         provided with previously delivered aircraft.SERVICE LIFE POLICY COMPONENTS

                                     between

                               THE BOEING COMPANY

                                       and

                            American Trans Air, Inc.

                   Supplemental Exhibit SLP1 to Purchase Agreement Number 2285

<PAGE>

                         SERVICE LIFE POLICY COMPONENTS

                                   relating to

                            BOEING MODEL 757 AIRCRAFT

This is the listing of Covered  Components for the Aircraft which relate to Part
3, BOEING  SERVICE LIFE POLICY of Exhibit C, PRODUCT  ASSURANCE  DOCUMENT to the
AGTA and is a part of Purchase Agreement No. 2285.

1.           WING.
             ----

     (a) Upper and lower skins and stiffeners  between the forward and rear wing
spars.

     (b) Wing spar webs, chords, and stiffeners.

     (c) Inspar wing ribs.

     (d) Inspar splice plates and fittings.

     (e) Main landing gear support structure.

     (f) Wing center section lower beams,  spanwise  beams and floor beams,  but
not the seat tracks attached to the beams.

     (g) Wing-to-body structural attachments.

     (h)  Engine  strut  support  fittings  attached  directly  to wing  primary
structure.

     (i) Support structure in the wing for spoilers and spoiler  actuators;  for
aileron  hinges and  reaction  links;  and for leading edge devices and trailing
edge flaps.

     (j) Trailing edge flap tracks and carriages.

     (k) Aileron  leading edge device and  trailing  edge flap  internal,  fixed
attachment and actuator support structure.

2.           BODY.
             ----

     (a) External surface skins and doublers, longitudinal stiffeners, longerons
and  circumferential  rings and frames between the forward pressure bulkhead and
the vertical stabilizer rear spar bulkhead, and structural support and enclosure
for the APU but excluding all system  components  and related  installation  and
connecting  devices,  insulation,  lining,  and  decorative  panels and  related
installation and connecting devices.

     (b)  Window  and  windshield   structure  but  excluding  the  windows  and
windshields.

     (c) Fixed  attachment  structure of the  passenger  doors,  cargo doors and
emergency exits,  excluding door mechanisms and movable hinge components.  Sills
and frames  around the body openings for the  passenger  doors,  cargo doors and
emergency exits, excluding scuff plates and pressure seals.

     (d) Nose wheel well  structure,  including  the wheel well walls,  pressure
deck, forward and aft bulkheads, and the gear support structure.

     (e) Main gear wheel well structure  including pressure deck,  bulkheads and
landing gear beam support structure.

     (f) Floor beams and support  posts in the control cab and  passenger  cabin
area, but excluding seat tracks.

     (g) Forward and aft pressure bulkheads.

     (h) Keel  structure  between the wing front spar bulkhead and the main gear
wheel well aft bulkhead, including splices.

     (i) Wing front and rear spar support bulkheads, and vertical and horizontal
stabilizer front and rear spar support bulkheads including terminal fittings but
excluding all system components and related installation and connecting devices,
insulation,  lining,  decorative panels, and related installation and connecting
devices.

     (j) Support  structure in the body for the stabilizer  pivot and stabilizer
screw.

3.           VERTICAL STABILIZER.
             -------------------

     (a) External skins between front and rear spars.

     (b) Front,  rear and  auxiliary  spar chords,  webs,  and  stiffeners,  and
attachment fittings between vertical stabilizer and body.

     (c) Inspar ribs.

     (d)  Support  structure  in the  vertical  stabilizer  for  rudder  hinges,
reaction links and actuator.

     (e) Rudder internal, fixed attachment and actuator support structure.

     (f) Rudder hinges and supporting ribs, excluding bearings.

4.           HORIZONTAL STABILIZER.
             ---------------------

     (a) External skins between front and rear spars.

     (b) Front, rear and auxiliary spar chords, webs, and stiffeners.

     (c) Inspar ribs.

     (d) Stabilizer center splice fittings, pivot and screw support structure.

     (e) Support structure in the horizontal stabilizer for the elevator hinges,
reaction links and actuators.

     (f) Elevator internal, fixed attachment and actuator support structure.

5.           ENGINE STRUT.
             ------------

     (a) Strut external surface skin and doublers and stiffeners.

     (b) Internal strut chords, frames and bulkheads.

     (c) Strut to wing fittings and diagonal brace.

     (d) Engine mount support fittings attached directly to strut structure.

     (e) For Aircraft  equipped with Pratt & Whitney  engines  only,  the engine
mounted support fittings.

6.           MAIN LANDING GEAR.
             -----------------

     (a) Outer cylinder.

     (b) Inner cylinder.

     (c) Upper and lower side struts, including spindles and universals.

     (d) Drag strut.

     (e) Side strut reaction link.

     (f) Side strut support link.

     (g) Downlock links including spindles and universals.

     (h) Orifice plate.

     (i) Trunnion link.

     (j) Truck beam.

     (k) Axles.

     (l) Torsion links.

     (m) Stabilizer link.

7.           NOSE LANDING GEAR.
             -----------------

     (a) Outer cylinder.

     (b) Inner cylinder.

     (c) Upper and lower drag strut, including lock links.

     (d) Axles.

     (e) Torsion links.

     (f) Steering plates and steering collar.

     (g) Orifice plate.

     NOTE: The Service Life Policy does not cover any bearings, bolts, bushings,
clamps, brackets, actuating mechanisms or latching mechanisms used in or on
the Covered Components.American Trans Air, Inc.
7337 West Washington St.
Indianapolis International Airport
Indianapolis, Indiana  46231

     Subject: Demonstration Flight Waiver

     Reference:  Purchase  Agreement 2285 (the Purchase  Agreement)  between The
Boeing  Company  (Boeing) and American  Trans Air, Inc.  (Customer)  relating to
Model 757-33N aircraft (the Aircraft)

     This Letter  Agreement amends and supplements the Purchase  Agreement.  All
terms used but not defined in this Letter  Agreement shall have the same meaning
as in the Purchase Agreement.

DEFINITION OF TERMS:

CORRECTION  COSTS:  Customer's  direct  labor costs and the cost of any material
required to correct a Flight  Discrepancy  where direct labor costs are equal to
the warranty  labor rate in effect between the parties at the time such labor is
expended.

FLIGHT DISCREPANCY: A failure or malfunction of an Aircraft, or the accessories,
equipment or parts  installed on the Aircraft which results from a defect in the
Aircraft,  Boeing Product, engine or Supplier Product or a nonconformance to the
Detail Specification for the Aircraft.

The AGTA  provides  that each  aircraft will be test flown prior to delivery for
the purpose of demonstrating  the functioning of such Aircraft and its equipment
to Customer;  however,  Customer  may elect to waive this test flight.  For each
test flight waived,  Boeing agrees to provide  Customer an amount of jet fuel at
delivery  that,  including the standard fuel  entitlement,  totals the following
amount of fuel:

 ---------------------- -----------------------------------------------
 AIRCRAFT MODEL         TOTAL FUEL ENTITLEMENT
                        (U.S. GALLONS)
 ---------------------- -----------------------------------------------
 ---------------------- -----------------------------------------------
 737                    Full tanks (approx.  5,300 to 6,800, depending
                        on model)
 ---------------------- -----------------------------------------------
 ---------------------- -----------------------------------------------
 747                    26,000
 ---------------------- -----------------------------------------------
 ---------------------- -----------------------------------------------
 757                    9,600
 ---------------------- -----------------------------------------------
 ---------------------- -----------------------------------------------
 767                    11,000
 ---------------------- -----------------------------------------------
 ---------------------- -----------------------------------------------
 777                    10,300
 ---------------------- -----------------------------------------------

Further,  Boeing agrees to reimburse  Customer for any Correction Costs incurred
as a result of the discovery of a Flight  Discrepancy during the first flight of
the aircraft by Customer  following delivery to the extent such Correction Costs
are not covered under a warranty provided by Boeing, the engine  manufacturer or
any of Boeing's suppliers.

Should a Flight Discrepancy be detected by Customer which requires the return of
the Aircraft to Boeing's facilities at Seattle,  Washington,  so that Boeing may
correct such Flight  Discrepancy,  Boeing and  Customer  agree that title to and
risk of loss of such  Aircraft  will remain with  Customer.  In addition,  it is
agreed that Boeing will have  responsibility for the Aircraft while it is on the
ground at Boeing's facilities in Seattle, Washington, as is chargeable by law to
a bailee for mutual benefit, but Boeing shall not be chargeable for loss of use.

To be reimbursed for Correction Costs,  Customer shall submit a written itemized
statement describing any flight discrepancies and indicating the Correction Cost
incurred by Customer  for each  discrepancy.  This  request must be submitted to
Boeing's Contracts Regional Director at Renton,  Washington,  within ninety (90)
days after the first flight by Customer.

Very truly yours,

THE BOEING COMPANY

By
  ------------------------------------------

Its           ATTORNEY-IN-FACT
   --------------------------------------

ACCEPTED AND AGREED TO this

Date:                                , 2000
      -------------------------------

AMERICAN TRANS AIR, INC.

By
  ------------------------------------------

Its
   ------------------------------------------

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