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F.  The curves in Fig. 202 present the estimated jet wake characteristics for the 737 airplane at breakaway thrust. The results obtained are based on a gross weight of 70,000 pounds and a friction coefficient of 0.04. It should be realized that this is an average value and does not apply to an airplane that has been parked for a long time.
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 10-11-0 Page 201 

 Typical Parking  500 
10-11-0  Figure 201  May 15/67 
Page 202 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

501  Jet Wake Data for Parking 
Jun 20/86  Figure 201 (Sheet 1)  10-11-0 
Page 202A 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

G11275G11276
Jet Wake Data for Parking  5C9 
10-11-0  Figure 201 (Sheet 2)  Feb 20/92 
Page 202B 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

5C9  Jet Wake Data for Parking 
Feb 20/92  Figure 201 (Sheet 3)  10-11-0 
Page 202C 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

Jet Wake Data for Parking  5C9 
10-11-0  Figure 201 (Sheet 4)  Jun 20/86 
Page 202D 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

5C9  Jet Wake Data for Parking 
Jun 20/86  Figure 201 (Sheet 5)  10-11-0 
Page 202E 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

Jet Wake Data for Parking  5C9 
10-11-0  Figure 201 (Sheet 6)  Jun 20/86 
Page 202F 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

5C9  Jet Wake Data for Parking 
Jun 20/86  Figure 202 (Sheet 7)  10-11-0 
Page 202G 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

Jet Wake Data for Parking  501 
10-11-0  Figure 202 (Sheet 8)  Jun 20/86 
Page 202H 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

G.  Review Fig. 202 for identification of engine hazard areas, entry and exit corridors, and personnel safety lanyard assembly (F80239) attach points. Awareness of hazard areas and proper entry/exit corridors is essential whenever maintenance tasks are performed around or near an operating engine. Use of personnel safety lanyard is recommended, but not mandatory.
WARNING:  DO NOT LATCH OR UNLATCH ENGINE SIDE COWLS WHILE ENGINE IS OPERATING. FORWARD SIDE COWL LATCHES ARE IN ENGINE INLET HAZARD AREA.
IF ENGINE SIDE COWLS HAVE NOT BEEN REMOVED FOR PERFORMING ENGINE TRIM, LEAK CHECKS, OR OTHER MAINTENANCE TASKS REQUIRING ENGINE OPERATION, DO NOT ENTER OR EXIT FROM FORWARD END OF SIDE COWLS. ENTERING OR EXITING FROM FORWARD END OF SIDE COWL WILL PLACE PERSONNEL IN ENGINE INLET HAZARD AREA, AND MAY CAUSE POSSIBLE PERSONNEL INJURY.
DO NOT CONNECT SAFETY LANYARD ASSEMBLY TO ANY TUBING, WIRE HARNESS, ETC. DAMAGE TO ENGINE OR INJURY TO PERSONNEL MAY OCCUR.
2.  Equipment and Materials
A.  Nose and Main Landing Gear Ground Lock Assembly -F72735
B.  Plug, Engine Exhaust -F80093
C.  Plug, Side Engine Inlet -F72717
D.  Plug, APU Exhaust -F80076
E.  Mat or suitable material for placing between tires and parking area if airplane is to be parked on ice or packed snow
F.  Pitot Static Tube Cover – HTC 73-75 PPCW (Fwd Fuselage)
G.  Pitot Static Tube Cover – HT 73-75 PPC (Vert. Stabilizer)
H.  Wheel chocks
I.  Safety Lanyard Assembly -F80239
J.  B00316 Solvent -Aliphatic Naphtha, TT-N-95, Type I
K.  G02443 Orange barricade tape, 3 inches wide, 4 mils thick, non-adhesive, with “REMOVE BEFORE FLIGHT” printed on it in black letters.
L.  G02219 3M Scotch Brand No. 471 vinyl adhesive tape (1.5 inches wide) bright yellow color.
M.  G02444 Red paper tag (3 inches wide, 6 inches long) with attaching wire that has “STATIC PORTS COVERED” printed on it in black letters -P/N 2000s.
　
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