A
757
MAINTENANCE MANUAL
757 MAINTENANCE MANUAL
CHAPTER 07 - LIFTING & SHORING
TABLE OF CONTENTS
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Chapter Section Subject_______ Subject ____ Effectivity
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LIFTING & SHORING 07-00-00
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JACKING 07-10-00
_______ ú GENERAL JACKING PROCEDURE 07-11-00 JACKING AIRPLANE 07-11-01 Maintenance Practices 201 ALL JACKING AIRPLANE AXLES 07-11-03 Maintenance Practices 201 ALL JACKING AIRPLANE NOSE 07-11-02 Maintenance Practices 201 ALL JACKING FOR AIRPLANE SUPPORT 07-11-05 WITH ENGINE(S) REMOVED Maintenance Practices 201 ALL
07-CONTENTS
GUN.1 Page 1 Sep 28/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757 MAINTENANCE MANUAL
JACKING AIRPLANE - MAINTENANCE PRACTICES
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1. General
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A. This section gives instructions to lift the airplane on jacks when conditions are satisfactory. Three primary jack points are used to lift and lower the airplane. One jack point is used to make the airplane stable (when it is necessary) after it is lifted to the necessary height. Jack adapters must be installed at the four jack points before the airplane is lifted on jacks.
B. The airplane can be lifted on jacks in winds up to 35 knots. You can do this if the jacks are designed and specified for the 757 airplane. If you use jacks that have the general specifications but are not designed for the 757, be careful. It is possible that the maximum wind speed (35 knots) limit will have to be decreased.
TASK 07-11-01-842-001
2. Prepare to Lift the Airplane On Jacks
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A. Equipment
(1)
Airplane Jacks (Fig. 201)
(2)
Adapter, Forward Body Jacking - B07001-7
(3)
Adapter, Tail Jack - B07002-1
(4)
Adapter, Aircraft Jacking - F80060-6
(5)
Shock Strut Lock Equipment, MLG - B32028-1
(6)
Wheel Chocks (8)
B. Consumable Materials
(1) C00308 Corrosion Preventive Compound -MIL-C-11796, Class III
C. Parts
~.............................................................................. | AMM | | AIPC | ................. ............................ | FIG | ITEM | NOMENCLATURE | SUBJECT | FIG | ITEM | ................................................................................ | 202 | 1 | Bolt | 53-13-53| 03 | 229 | | | 1 | Plug Assembly (optional to bolt 1)| | | 230 | | | 2 | Bolt, Hi-Torque (BACB30LL4K11) | | | 244 | 2......…........…...................................…..........…......…........1
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07-11-01
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757
MAINTENANCE MANUAL
PRIMARY WING
TAIL JACKING JACKING
POINT D
POINTS B-LEFT C-RIGHT JACK EXTENDED HEIGHT BASED ON: . LEVEL AIRPLANE . SHOCK STRUTS FULLY EXTENDED . MINIMUM OF 4 INCHES (102 mm) TIRE
JACKING POINT 757-200 JACK SPECIFICATIONS
2POUNDS MAXIMUM LOAD (KG) 3 4 JACK HEIGHT INCHES (METERS) ROLL-UNDER EXTENDED FITTING ADAPTER
1 PRIMARY A 26,900 (12,202) (3.61) 142 (2.69) 106 B07001-7
B 93,000 (42,184) (4.11) 162 (3.33) 131 F80060-6
C 93,000 (42,184) (4.11)(3.33) 131 162 F80060-6
1 STABILIZING D 65 4,000 (1,814) (3.91)(3.12) 154123 B07002-1
CLEARANCE FOR GEAR RETRACTION
THIS VALUE IS LIMITED BY THE PRIMARY NOSE JACKING POINT ALLOWABLE JACK LOAD. LOCAL STRUCTURAL ALLOWABLE LOAD IS 12,000 POUNDS (5,443 KG).
JACKS USED IN THIS POSITION HAVE A
. 6-INCH (152 mm) ROLL-UNDER CLEARANCE RELIEF VALVE THAT OPENS AT 4,000 POUNDS (1,814 KG)
NOSE GEAR TIRE
NOTE: FOR JACK HEIGHT REQUIREMENTS TO DO MAIN GEAR SHOCK STRUT SEAL MAINTENANCE, REFER TO AMM 32-11-25/201, MAIN GEAR SHOCK STRUT SEAL.
757-200
Airplane Jacking System Specifications
Figure 201
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