MAINTENANCE MANUAL

AIRWORTHINESS LIMITATIONS SECTION P/N 25-1001-11-2

1. Airworthiness Limitations Section
A. Introduction

The Airworthiness Limitations section is Civil Aviation Authority of Israel (CAAI) approved
and specifies maintenance required under Israeli Air Navigation Regulations (ANR)
Chapter 7 Section 126 (equivalent to sections 43.16 & 91.403 of the Code of Federal
Regulations) unless an alternative program has been CAAI approved. The signed CAAI
approval form is kept on file with Gulfstream Aerospace Publications.

These Airworthiness Limitations are mandatory actions derived from the certification
activities, namely, the Damage Tolerance Analysis and the Fatigue Tests. This section
presents the maintenance actions established in order to fully comply with the
requirements of Title 14 CFR Part 25.571 and Part 25.1529 and, therefore, are required to
be accomplished in strict compliance with the life limits, maximum intervals limits,
inspection methods and PSE location established herein. The Airworthiness Limitations
are a result of the Engineering Certification analysis and have been approved by CAAI.
The Airworthiness Limitations may only be revised with the approval of the Civil Aviation
Authority of Israel (CAAI).

Damage tolerance analysis of the 1125 Astra shows that the aircraft structure can safely sustain
damage in the form of cracks permitting timely detection and repair of cracks.
The Airworthiness Limitations Section provides a set of procedures for inspection points for
structural cracks throughout the life of the aircraft for the following two major aircraft components:
• Fuselage (F)
• Wing (W)
For each of these components, a summary table of the inspection points (F followed by inspection
point number and W followed by inspection point number) is presented below. See Table 4.
This Airworthiness Limitations Section is based on IAI engineering reports 25W031/841588 and
25W032/941007.
The table gives, for each major aircraft structural component, a list of structural points where
inspections are to be carried out. For each point are given:
• The structural part and location to be inspected
• The inspection method to be used
• The number of flight hours before the first inspection (inspection threshold)
• The number of flight hours between all further inspections (subsequent inspection intervals)
• Effectivity
Reporting of inspection results is required to ensure continued airworthiness of the fleet is
maintained. This procedure contains the necessary reporting information which is to be used
whenever a airworthiness limitations inspection is accomplished.
NOTE: Inspection results, both positive and negative, are to be reported to Gulfstream
Maintainability Engineering, 912-965-3153, FAX 912-965-4704. Discrepancies are to be
reported within 24 hours of their findings. Complete Table 1 with inspection results.
Provide a digital photograph of the discrepancy.

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Table 1: ALS Inspection Results

AIRCRAFT SERIAL AIRCRAFT TAIL

ALS NUMBER CMP NUMBER
NUMBER NUMBER

Part Number(s) [if

Aircraft Hours Aircraft Landings Date of Inspection
applicable]

Discrepancies Found
No Yes
If yes, complete the following information:
Location
FS BL WL

Size

Orientation

Alternative inspection methods may be used as follows provided the inspector determines the
inspection method will provide satisfactory results.
NOTE: Inspection methods specified as ultrasonic or eddy current should not be substituted with
x-ray as these methods have been determined as the best methods.
• Inspection methods of x-ray, ultrasonic, eddy current or penetrant may be used in place of
visual inspection methods.
• Inspection methods of x-ray, ultrasonic and eddy current may be used in place of penetrant
inspection methods.

Table 2: Alternate NDI Inspections - Accessible Locations

STATED ALTERNATE METHOD

LOCATION
METHOD VISUAL PENETRANT HFEC (1)

Visual — Yes Yes

Accessible Penetrant No — Yes
HFEC No No —
(1)
High Frequency Eddy Current (HFEC).

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Table 3: Alternate NDI Inspections - Inaccessible Locations

STATED ALTERNATE METHOD

LOCATION
METHOD X-RAY ULTRASOUND LFEC (1)

X-ray — Yes (2) Yes (2)

Inaccessible Ultrasound Yes (2) — Yes (2)

LFEC Yes (2) Yes (2) —

(1)
Low Frequency Eddy Current (LFEC).
(2)
Specific authorization is required.

For limitation inspections after 20,000 flight hours, please contact Gulfstream Aerospace Company,
LP in Savannah, Georgia.
The Airworthiness Limitations Section stipulates, by means of Continued Airworthiness Inspection
Tables, explicit inspection procedures and intervals for the detection of structural cracks throughout
the life of the aircraft. This is facilitated by the information presented in this Airworthiness Limitations
Section.
Airworthiness Limitation Section inspections are specified on the basis of flight hours and not of
flights. To allow the scheduling of structural inspections to coincide with a general maintenance
check, an inspection tolerance of +/-5% of the inspection interval is allowed. The accomplishment of
the ″INITIAL″ inspection is to be performed within +/-5% of the specified interval. Subsequent
inspections are to be performed at the specified ″REPEAT″ inspection interval, within the allowed
+/-5% tolerance, from the time of the actual performance of the previous inspection.
For aircraft that have accomplished the initial inspection outside the +/-5% window prior to Revision
9 of the ALS, dated June 15, 2009, perform next inspection at the “REPEAT” interval, +/-5% from
the actual time of accomplishment of the previous inspection, or at the “INITIAL” interval +/-5%,
whichever is later.
An item that has become overdue for an aircraft as the result of a revision to the ALS (which
included a new item or a reduced threshold and / or frequency reduction) may be accomplished,
unless specifically stated otherwise, at the next inspection interval, not to exceed 250 hours.
All inspections are general visual inspections unless otherwise specified. A corrosion inspection of
the surrounding area is to be included as part of the general visual inspection.
The locations of cracks shown in the figures of Table 4 referenced procedures are theoretical
examples only of damage to structure and were derived by damage tolerance analysis. Similar
damage may exist within the areas surrounding these locations and should also be included in the
inspection procedure.
Whenever cracks, wearing and damages are found during the inspection of items listed in the
Airworthiness Limitations Section, such findings are to be reported to Gulfstream Aerospace
Company, LP in Savannah, Georgia. Repairs of damages are not permitted unless permission is
first obtained from the manufacturer.
B. Log of Revisions

REVISION DESCRIPTION DATE

1 The entire section I and Section II revised. Section III corrected and Section 01/15/1995
IV added.

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REVISION DESCRIPTION DATE

2 Rewritten 01/01/1999
3 The entire inspection requirements section revised to include changes due 01/13/2004
to service experience and correction of editorial errors.
4 Effectivity statement was changed in title page and overfly statement was 11/01/2004
added to introduction for new or revised inspection intervals.
5 Figure 14 effectivity was changed for A/C 004-077. Added new Figure 14A 12/30/2005
for A/C 078 and subsequent. Also added new Figures 14B and 14C for
inspection point W3.
6 ALS format changed in Section 05-10-10 to become similar to standard 11/16/2006
Gulfstream Manual format.
7 Added column for Maintenance Manual reference. 08/20/2007
8 Format changed to meet CAAI requirements. Added corrections and editorial 06/15/2008
changes also.
9 Corrected ALS part number. Added inspection at location F22. Added 06/15/2009
paragraph for the inspection interval tolerance.
10 Corrected inspection tolerance statement. 06/15/2010
11 Added ALS Inspection Reporting table. 06/15/2011
12 1. Changed Federal Aviation Regulations to Code of Federal Regulations. 05/15/2013
2. Added compliance statement.
13 Reformatted ALS table by deleting the Rev column. 05/15/2016
14 Added CMP Number column to ALS table. 06/30/2020

C. Airworthiness Limitations - Structural Inspections

The Airworthiness Limitations Section is Civil Aviation Authority of Israel (CAAI) approved and
specifies maintenance required under Israeli Air Navigation Regulations 126 and under 43.16;
91.403 of the Code of Federal Regulations.
Table 4 contains a list of structural inspections along with the specific description, initial threshold,
repeat interval and Computerized Maintenance Program (CMP) Reference.

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 Table 4: Airworthiness Limitations
Description Inpection Interval
ALS ATA CMP
NDI Type Repeat
Number Aircraft Maintenance Manual Initial Ref Ref
Procedure
F1 F1 Trunnion Support / Drag Brace - NDT Dye penetrant 10000 flight 5000 flight hours 53-10-00 530045
Location Inspection hours
a-d
F2 F2 Main Landing Gear Actuator Housing - Dye penetrant 10000 flight 5000 flight hours 53-10-00 530046
NDT Inspection hours 530047

F3 F3 Forward Pressure Bulkhead - Visual Visual 10000 flight 5000 flight hours 53-10-00 530048
Location Inspection hours
a-d

MAINTENANCE MANUAL
F4 F4 Forward Fuselage Skin - Visual Visual 10000 flight 3000 flight hours 53-10-00 530051
Location Inspection hours
a-b
F5 F5 Cabin Window Outside - Visual Visual 4000 flight hours 2500 flight hours 53-10-00 530052
Inspection
F6 F6 Emergency Exit Outside - Visual Visual 6000 flight hours 5000 flight hours 53-10-00 530053
Inspection
F7 F7 Fuselage Upper Skin Between STA Visual 10000 flight 3000 flight hours 53-10-00 530054
Location 249.00 - STA 316.84 - Visual Inspection hours
a - c, f
F7 F7 Fuselage Upper Skin and Access Visual 10000 flight 5000 flight hours 53-10-00 530055
Location Panels Between STA 249.00 - STA hours
d - e, g - h 316.84 - Visual Inspection
F8 F8 Top Splice Frame at STA 403.00 and Visual 10000 flight 5000 flight hours 53-10-00 530058
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Location Engine Forward Fitting - Visual Inspection hours 530059

a-c
F9 F9 Engine Aft Beam Fitting - Visual Visual 10000 flight 5000 flight hours 53-10-00 530062
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Inspection hours 530071

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05-10-10 Description Inpection Interval
ALS ATA CMP
NDI Type Repeat
Number Aircraft Maintenance Manual Initial Ref Ref
Procedure
F10 F10 Top Aft Corner of Main Landing Gear Visual 10000 flight 5000 flight hours 53-10-00 530063
Bay - Visual Inspection hours 530064

F11 F11 Forward Top and Bottom Corners of Visual 10000 flight 5000 flight hours 53-10-00 530065
Location Baggage and Equipment Compartment hours
a-b Doors - Visual Inspection
F12 F12 Skin Splice at Longeron No. 3 - Visual 10000 flight 5000 flight hours 53-10-00 530066
Visual Inspection hours

MAINTENANCE MANUAL
F13 F13 Lower Beam Fitting Attachment at Visual 10000 flight 5000 flight hours 53-10-00 530067
Frame 260 - Visual Inspection hours

F15 F15 Vertical Stabilizer Aft Fitting Dye penetrant 10000 flight 5000 flight hours 53-10-00 530068
Location Attachment - NDT Inspection hours
a-b
F15 F15 Horizontal Stabilizer Rear Spar Visual 600 flight hours 400 flight hours 53-10-00 530069
Location Hinge (Aluminum) - Visual Inspection
c NOTE: Aircraft 004 thru Aircraft 053
Pre-SB SB 1125-55-017.
F15 F15 Horizontal Stabilizer Rear Spar Visual 4400 flight hours 2200 flight hours 53-10-00 530070
Location Hinge (Titanium) - Visual Inspection
c NOTE: Aircraft 004 thru Aircraft 053
Post SB SB 1125-55-017,
Aircraft 054 thru Aircraft 072
and Aircraft 074 thru Aircraft
078.
F15 F15 Horizontal Stabilizer Outer Lugs - Ultrasonic 5000 flight hours 2000 flight hours 53-10-00 530072
Location Ultrasonic Inspection
d
 Description Inpection Interval
ALS ATA CMP
NDI Type Repeat
Number Aircraft Maintenance Manual Initial Ref Ref
Procedure
F16 F16 Vertical Stabilizer Fittings - Visual Visual 10000 flight 5000 flight hours 53-10-00 530073
Location Inspection hours
a
F16 F16 Horizontal Stabilizer Fasteners - Visual 10000 flight 1250 flight hours 53-10-00 530074
Location Visual Inspection hours
b
F17 F17 Airstair Lower Door Stops - NDT Dye penetrant 10000 flight 2500 flight hours 53-10-00 530075
Location Inspection hours
a-b

MAINTENANCE MANUAL
F17 F17 Passenger / Crew Door Backup Visual 10000 flight 2500 flight hours 52-10-00 530076
Location Fitting - Visual Inspection hours
c
F17 F17 Passenger / Crew Door Structure - Visual 10000 flight 5000 flight hours 52-10-00 530077
Location Visual Inspection hours
d-e
F17 F17 Cabin Door Frame Assembly STA Visual 10000 flight 5000 flight hours 53-10-00 530078
Location 63.78 and STA 92.78 - Visual Inspection hours
f, i, k
F17 F17 Aft Cabin Door Frame - NDT Dye penetrant 10000 flight 5000 flight hours 53-10-00 530079
Location Inspection hours
g
F17 F17 J-beam Flange at STA 63.78 and X-ray 7000 flight hours 2000 flight hours 53-10-00 530080
Location STA 92.78 - NDT Inspection
h NOTE: Aircraft 004 thru Aircraft 041.
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F17 F17 J-beam Flange at STA 63.78 and X-ray 10000 flight 5000 flight hours 53-10-00 530080
Location STA 92.78 - NDT Inspection hours
h NOTE: Aircraft 042 thru Aircraft 072
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and Aircraft 074 thru Aircraft

078.
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05-10-10 Description Inpection Interval
ALS ATA CMP
NDI Type Repeat
Number Aircraft Maintenance Manual Initial Ref Ref
Procedure
F17 F17 Center Section Frame - NDT Dye penetrant 10000 flight 2000 flight hours 53-10-00 530082
Location Inspection hours
j NOTE: Aircraft 004 thru Aircraft 041.
F17 F17 Center Section Frame - NDT Dye penetrant 10000 flight 5000 flight hours 53-10-00 530082
Location Inspection hours
j NOTE: Aircraft 042 thru Aircraft 072
and Aircraft 074 thru Aircraft
078.
F18 F18 Emergency Exit Door Corner Visual 10000 flight 5000 flight hours 53-10-00 530084

MAINTENANCE MANUAL
Location Fasteners - Visual Inspection hours
a
F18 F18 Emergency Exit Door Stops - Visual Visual 10000 flight 3500 flight hours 53-10-00 530085
Location Inspection hours
b
F19 F19 Aft Pressure Bulkhead - Visual Visual 10000 flight 5000 flight hours 53-10-00 530086
Location Inspection hours
a-d
F20 F20 Inner Flange at STA 199.579 - NDT Dye penetrant 10000 flight 5000 flight hours 53-10-00 530088
Location Inspection hours
a
F20 F20 Main Frame Between STA 199.579 Visual 10000 flight 5000 flight hours 53-10-00 530089
Location and STA 260.082 - Visual Inspection hours
b, d - e
F20 F20 Intermediate Frame Strap Dye penetrant 7500 flight hours 2500 flight hours 53-10-00 530090
Location Attachment Fasteners - NDT Inspection
c
F20 F20 Inner Flange Splice Area Fasteners - Dye penetrant 10000 flight 5000 flight hours 53-10-00 530092
Location NDT Inspection hours
f
 Description Inpection Interval
ALS ATA CMP
NDI Type Repeat
Number Aircraft Maintenance Manual Initial Ref Ref
Procedure
F21 F21 Horizontal Stabilizer Actuator Jacks - Visual 1000 flight hours 250 flight hours 27-40-00 274046
Location Visual Inspection
a-b
F22 F22 Vertical Stabilizer Aft Spar Flanges at Eddy current 10000 flight Note 55-30-00 553011
Rudder Fitting Attachments - NDT hours
Inspection
NOTE: Next inspection (not interval) is
13500 hours, 17000 hours,
20000 hours.
For aircraft past 10000 hours,

MAINTENANCE MANUAL
accomplish initial inspection
within 12 months from date of
revision 18.
W1 W1 Wing to CTS Attachment - Visual Visual 10000 flight 5000 flight hours 57-10-00 570035
Location Inspection hours 570036
a-f
W2 Wing Ribs (Inspection Points W2) - Visual 10000 flight 5000 flight hours 57-00-00 570045
Location Visual Inspection hours 570046
a-d
W2 W2 Location E, Wing Ribs - NDT Dye penetrant 2000 flight hours 2000 flight hours 57-00-00 570053
Location Inspection 570054
e NOTE: Aircraft 004 thru Aircraft 072
and Aircraft 074 thru Aircraft
077 Pre-SB 1125-57-136 with
corrosion found during
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performance of SB 1125-57-
136.
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05-10-10 Description Inpection Interval
ALS ATA CMP
NDI Type Repeat
Number Aircraft Maintenance Manual Initial Ref Ref
Procedure
W2 W2 Location E, Wing Ribs - NDT Dye penetrant 5000 flight hours 5000 flight hours 57-00-00 570053
Location Inspection 570054
e NOTE: Aircraft 004 thru Aircraft 072
and Aircraft 074 thru Aircraft
077 Post SB 1125-57-136 or
no corrosion found during
performance of SB 1125-57-
136 and Aircraft 078.
W3 W3 Wing Ribs - NDT Inspection Dye penetrant 2000 flight hours 2000 flight hours 57-00-00 570057
Location NOTE: Aircraft 004 thru Aircraft 072 570058

MAINTENANCE MANUAL
a and Aircraft 074 thru Aircraft
077 Pre-SB 1125-57-136 or
corrosion found during
performance of SB 1125-57-
136.
W3 W3 Wing Ribs - NDT Inspection Dye penetrant 10000 flight 5000 flight hours 57-00-00 570057
Location NOTE: Aircraft 004 thru Aircraft 072 hours 570058
a and Aircraft 074 thru Aircraft
077 Post SB 1125-57-136 with
no corrosion found during
performance of SB 1125-57-
136 and Aircraft 078.
W4 W4, W5 Wing Areas - Visual Inspection Visual 10000 flight 5000 flight hours 57-00-00 570060
hours

W5 W4, W5 Wing Areas - Visual Inspection Visual 10000 flight 5000 flight hours 57-00-00 570060
hours

W6 W6 Main Landing Gear Bearing Housing Visual 10000 flight 5000 flight hours 57-00-00 570061
Location - Visual Inspection hours 570062
a-b
 Description Inpection Interval
ALS ATA CMP
NDI Type Repeat
Number Aircraft Maintenance Manual Initial Ref Ref
Procedure
W6 W6 Web at Rib 2 - Visual Inspection Visual 10000 flight 5000 flight hours 57-00-00 570067
Location hours 570068
c-d
W7 W7 Outboard Flap Rails - Visual Visual 10000 flight 5000 flight hours 57-51-00 570071
Location Inspection hours 570072
a
W7 W7 Outboard Flap - Visual Inspection Visual 10000 flight 2500 flight hours 57-51-00 570073
Location hours 570074
b-c

MAINTENANCE MANUAL
W8 W8 Slat Structure - Visual Inspection Visual 10000 flight 5000 flight hours 57-41-00 570077
Location hours 570078
a-b
W9 W9 Aileron Main Hinge Assembly - Visual Visual 10000 flight 5000 flight hours 57-60-00 570079
Location Inspection hours 570080
a
W9 Aileron Surface - NDT Inspection Tap Test 5000 flight hours 5000 flight hours 57-60-00 570081
Location 570082
c
W9 W9 Aileron External Structure - NDT Ultrasonic 10000 flight 5000 flight hours 57-60-00 570083
Location Inspection hours 570084
d
W10 W10 Aileron Inner Lug - NDT Inspection Dye penetrant 10000 flight 5000 flight hours 57-60-00 570085
hours 570086
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W14 W14 Wing External Skin - NDT Eddy current 5000 flight hours 2500 flight hours 57-00-00 570095
Inspection 570096
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D. Canadian Certified Aircraft Requirements

Table 5 below lists all mandatory inspections required by aircraft certified in Canada.
NOTE: The first two columns (PAGE and PARA.) refer to Engineering Document TR 25W042/
940970.

Table 5: Systems Mandatory Inspections Intervals

INSPECT
INTERVAL IN
CHAPTER FLIGHT
PAGE PARA. 5 REF. CMP REF. DESCRIPTION HOURS
1-2 A.1 05-20-00 243020 Battery - Servicing 200
243021
1-6 B(7) 05-20-00 322050 Nose Landing Gear Scissors 250
Assembly - Visual Inspection
1-30 2.D 05-20-00 341055 Angle of Attack / Stall Warning - 250
Operational Test
1-30 2.E 05-20-00 278075 Automatic Slat Operation - 250
Functional Test
1-31 A(3) 05-20-00 521004 Cabin Entrance Door Seal - Visual 250
Inspection
1-31 A(4) 05-20-00 521005 Door Warning System - Operational 250
Test
1-33 B(4) 05-20-00 352001 Passenger Oxygen Supply System - 1000
Functional Test
1-36 C(2)b 05-20-00 272010 Rudder Linear Ball Bearings - 1000
Inspection
1-42 A(4)(b) 05-20-00 275029 Flaps Roller Bearings - Lubrication 1000
275030
1-43 A(5)(b) 05-20-00 275039 Flexible Shaft - Lubrication 1000
275040
1-44 A(6)(b) 05-20-00 275055 Flap Linear Actuator - Lubrication 500
275056
1-45 B(4)(b) 05-20-00 278029 Slats Roller Bearings - Lubrication 1000
278030
1-46 B(5)(b) 05-20-00 278057 Flexible Shaft Core - Inspection and 1000
278040 Lubrication
1-48 D(3)(a) 05-20-00 271020 Aileron (Using Auxiliary Hydraulic 250
System) - Functional Check
1-48 D(3)(a) 05-20-00 271025 Aileron (Using Main Hydraulic 250
System) - Functional Check

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INSPECT
INTERVAL IN
CHAPTER FLIGHT
PAGE PARA. 5 REF. CMP REF. DESCRIPTION HOURS
1-48 D(3)(a) 05-20-00 271029 Aileron Servo Actuator - Detailed 250
271030 Inspection
1-49 D(5) 05-20-00 271035 Aileron Travel Limit Stops - Visual 1000
271036 Inspection
1-50 D(5) 05-20-00 271055 Aileron Linear Ball Bearing - Friction 1000
271056 Check
1-50 D(10) 05-20-00 271069 Compensator - Volume Check 250
271070
1-52 K(4) 05-20-00 276011 Airbrake - Operational Test 1000
1-53 N(1) 05-20-00 282309 Collector Tank Boost Jet Pump - First 1000
282310 Detailed Inspection hours, each
2500 hours
1-53 N(1) 05-20-00 282315 Low Center Tank Transfer Pump -
thereafter
282316 Detailed Inspection
1-53 N(1) 05-20-00 282319 Wing Transfer Jet Pump - Detailed
282320 Inspection
1-64 F(10) 05-20-00 321092 Swivel Joint - Seal Replacement 1000
321093
1-65 I(1)(b) 05-20-00 323002 Extension and Retraction 500
Emergency System - Functional Test
1-65 I(1)(b) 05-20-00 323003 Emergency Gear Extension Cable - 500
Functional Test
1-66 I(2) 05-20-00 323911 Landing Gear Emergency Extension 500
and (3) System - Servicing
1-73 F(7) 05-20-00 211101 Bleed Pressure High Warning Light - 1000
Operational Test
1-73 F(7) 05-20-00 216001 Duct TEMP HI Warning Light - 1000
Operational Test
1-73 F(7) 05-20-00 210010 Cabin 10000 Warning Light - Check 1000
1-73 F(7) 05-20-00 215432 Low Limit Temperature Sensor 1000
Circuit - Inspection Check
1-75 F(8) 05-20-00 215431 Low Limit Temperature Sensor - 250
Visual Inspection
1-79 H(2)(a) 05-20-00 282201 Fuel Shut-off Valve - Operational 250
Test

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INSPECT
INTERVAL IN
CHAPTER FLIGHT
PAGE PARA. 5 REF. CMP REF. DESCRIPTION HOURS
1-84 A(6) 05-10-10 274035 Horizontal Stabilizer Trim Actuator 250
Torque Tubes - Inspection /
Lubrication
1-84 A(7) 05-20-00 274040 Horizontal Stabilizer Trim Actuator 1000
and (8) Wiring Integrity - Visual Inspection
1-84 A(7) 05-20-00 274045 Horizontal Stabilizer Trim Actuator 1000
and (8) Lug / Rod Ends - Visual Inspection
1-88 C(5) 05-20-00 273050 Skin Separation - Inspection 250
1-91 F(3) 05-20-00 272020 Rudder Trim Tab Actuator - Visual 250
Inspection
Maximum Brakes Wear = 0.1 inch Every
Pre-flight

E. Temporary Limitation and Inspection Requirements

NOTE: There are not current temporary limitation requirements.

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 Table 6: Temporary Limitation and Inspection Requirements

AWL TO COMPLY LIFE

INTERVAL
NO. REPORT NO. CMP DESCRIPTION EFFECTIVITY WITHIN LIMIT

MAINTENANCE MANUAL
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