Document:

SERVICE LIFE POLICY COMPONENTS

                                     between

                               THE BOEING COMPANY

                                       and

                            American Trans Air, Inc.

           Supplemental Exhibit SLP1 to Purchase Agreement Number 2262

<PAGE>

                         SERVICE LIFE POLICY COMPONENTS

                                   relating to

                            BOEING MODEL 737 AIRCRAFT

This is the listing of SLP  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. 2262.

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 floor beams,  lower beams and spanwise  beams,  but
not the seat tracks attached to floor beams.

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

     (h) Wing-to-body structural attachments.

     (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.

<PAGE>

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, bulkheads, and gear support structure.

     (e) Main gear wheel well structure including pressure deck 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.

<PAGE>

3.           Vertical Stabilizer.
             -------------------

     (a) External skins between front and rear spars.

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

     (c) Inspar ribs.

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

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

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

4.           Horizontal Stabilizer.
             ---------------------

     (a) External skins between front and rear spars.

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

     (c) Inspar ribs.

     (d) Stabilizer center section including hinge 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 and
including the engine-mounted support fittings.

<PAGE>

6.           Main Landing Gear.
             -----------------

     (a) Outer cylinder.

     (b) Inner cylinder, including axles.

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

     (d) Drag strut.

     (e) Bell crank.

     (f) Orifice support tube.

     (g) Trunnion link.

     (h) Downlock links including spindles and universals.

     (i) Torsion links.

     (j) Actuator beam, support link and beam arm.

7.           Nose Landing Gear.
             -----------------

     (a) Outer cylinder.

     (b) Inner cylinder, including axles.

     (c) Orifice support tube.

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

     (e) Steering plates and steering collars.

     (f) Torsion links.

     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 2262 (the Purchase  Agreement)  between The
Boeing  Company  (Boeing) and American  Trans Air, Inc.  (Customer)  relating to
Model 737-83N 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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