Attachment 4- Questions Answers and Images.pdf

Questions, Answers, and Images

1. The load weights for the KC-135 nose lift are: Gross Weight = 8700 lbs Net Weight = 6850 lbs

2. The load weights for the F-15 lift are: Gross Weight = 33,000 lbs Net Weight = 31,600 lbs

3. The center of gravity of our KC-135 has been moved forward with the use of concrete weights in the cargo compartment to prevent tipping the aircraft back during the nose lift operation.

4. Our maximum aircraft lift heights for the KC-135 nose lift are 72 inches, and the maximum height for the F-15 lift is 36 inches.

5. The final placement of the suspended load is unchanged; we lift the aircraft straight up and lower it onto the same spot.

b49124

Figure 8-1.

C rane

H oisting

TO

1C

-135-2-07

8-2 b49125

Figure 8-2. Lifting Nose with Mobile Cranes

TO 1C-135-2-07

8-3

T.O. 35-1-251-1

CHAPTER 2

SECTION 7

FUSELAGE LIFTING SLING ASSEMBLY, PART NUMBER F70244-17

2-7-1. GENERAL INFORMATION.

2-7-2. The fuselage lifting sling assembly (figure 2-7-1) provides the means of raising an E-3A air-craft which has crashed landed or experienced landing gear failure at a base. The sling assembly consists of two channels bolted to a center lifting plate with a 12-inch wide nylon webbing fastened at each end to a delta beam. The delta beams are attached to shackles bolted to the beam. The sling assembly is used in conjunction with a mobile lift-ing crane. Leading particulars are contained in table 2-7-1.

2-7-4. SPECIAL TOOLS AND TEST

EQUIPMENT.

2-7-5. No special tools or test equipment are required.

2-7-6. OPERATION INSTRUCTIONS.

2-7-7. Instructions for use of the fuselage lifting sling assembly are contained in T.O. 1E-3A-2-7.

2-7-3. MAINTENANCE INSTRUCTIONS.

2-7-9. The following paragraphs contain instruc-tions for maintenance of the fuselage lifting sling

2-7-3. CONSUMABLE MATERIALS. Table 2-7-2 assembly.

contains a list of the consumable materials required for maintenance of the sling assembly.

Table 2-7-1. Leading Particulars

I T E M

S p a c e r ( 7 , f i g u r e 2 - 7 - 1 )

DESCRIPTION

1 . 2 5 b y 8 . 0 0 b y 1 6 . 0 0 i n c h e s 6061-T651 Aluminum Plate

C h a n n e l ( 8 ) 1 2 . 0 0 i n c h e s b y 1 7 2 . 0 0 i n c h e s l o n g - 7 . 4 l b s / f t 6061-T6 Aluminum

D e l t a P l a t e ( 3 ) 1 . 2 5 b y 1 7 . 2 5 b y 2 0 . 5 i n c h e s 6061-T6 Aluminum Plate

P l a t e ( 9 ) 1 . 2 5 b y 2 4 . 0 0 b y 8 6 . 0 0 i n c h e s 6061-T6 Aluminum Plate

S a f e t y S h a c k l e ( 5 a n d 6 )

W e b b i n g ( 4 )

6 . 5 t o n s a f e w o r k i n g l o a d

1 , 6 0 0 l b / i n . n y l o n w e b b i n g 1 2 i n c h e s w i d e 19,200 pounds minimum strength

Maximum Safe Load

P r o o f L o a d :

P r o o f L o a d :

Weight

1 5 , 0 0 0 p o u n d s

3 0 , 0 0 0 p o u n d s f o r s p r e a d e r b a r a s s e m b l y

1 5 , 0 0 0 p o u n d s f o r b a n d a s s e m b l y

T o b e d e t e r m i n e d

Change 7 2-7-1

TO 1F-15C-2-07JG-00-1

Change 25 4-9/(4-10 blank)

Figure 04. Sheet 4

07-00-04

CDDAR info.pdf