ALTERNATE PRESSURE PORT - REMOVAL/INSTALLATION
1. Equipment and Materials
A. High Temperature Fillet Sealant - BMS 5-18A, Type II - PR-810 (or equivalent)
2. Remove Static Pressure Port (Fig. 401)
A. Remove forward cargo compartment lining to gain access to static pressure ports (Ref Chapter 25, Equipment and Furnishings).
B. Disconnect static hose from elbow. Cap static hose to prevent entry of foreign material.
C. Loosen jamnut and remove elbow and O-ring from static pressure port.
D. Remove lockwire and clean away sealant from around static pressure port.
E. Remove static pressure port retaining nut and washer.
F. Remove static pressure port from exterior of airplane.
3. Install Static Pressure Port
A. Clean away any remaining sealant and prepare area for application of new sealant.
B. Insert static pressure port in mounting hole. Adjust until face of port is as flush with airplane skin as possible and hold in place.
C. Install static pressure port retaining nut and washer. Tighten retaining nut to torque value of 250 to 400 inch-pounds. Lockwire nut using double-twist method.
D. Check port is flush with the skin within +0.003/-0.000 inch after installation. If necessary, shave external surfaces of static pressure port until it is flush with airplane skin within tolerance. After shaving is complete, ensure surface finish on face of static port is 63 RMS maximum. Ensure no burrs or materials are in static pressure port and all inlet holes are free from obstructions or deformation.
E. After installation, the skin surface, for a distance of 3 inches forward and aft of the port centerline, should be flush within 0.010 inch maximum measured as the clearance between the skin and the edge of a 6-inch straightedge placed horizontally against the skin. All rivets within a 3-inch radius of the port center should be flush with the skin within 0.003 inch maximum.
500
Oct 20/91 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 34-11-21 Page 401
H28368
Alternate Static Port Installation 501
34-11-21Page 402 Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Nov 15/67
F. Alodize static pressure port with Alodine 1000 (Ref Protective Finishes in Chapter 51, Structures - General).
G. Apply sealant to static pressure port as shown in Fig. 401, Detail A (Ref 51-30-0, Seals and Sealing).
H. Install elbow and O-ring in static pressure port. Tighten jamnut.
I. Remove cap from end of static hose and check for any foreign material inside hose, clean if necessary.
J. Connect static hose and fitting to elbow. Tighten to torque value of 100 to 125 inch-pounds.
K. Install cargo compartment lining (Ref Chapter 25, Equipment/Furnishings).
L. Perform an alternate static system test per 34-11-0, Pitot Static System - A/T.
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Oct 20/86 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 34-11-21 Page 403
AIR DATA PRESSURE INSTRUMENTS - DESCRIPTION AND OPERATION
EFFECTIVITY
GJ ALL EXCEPT B-2509 thru B-2510 and B-2524
1. General
A. Air data pressure instruments are those which derive their inputs from the pitot static air pressure system and the air data computer system (Ref 34-11-0, Pitot Static System). The air data pressure instruments are two airspeed/mach indicators, two instantaneous vertical speed/rate of climb indicators, two altimeters, and one air data computer.
B. Indicated airspeed and mach number are conventionally displayed as a function of differential pitot and static air pressures on mach/airspeed combined instrument indicators. Mach inputs to this indicator will come from the air data computer and static and pitot air pressures.
C. Instantaneous vertical speed/rate of climb, through a range of 0 to 6000 feet per minute, is indicated according to accelerometer and static air pressure information.
D. Altitude throughout the range of 1000 feet below mean sea level to 50,000 feet above mean sea level may conventionally be indicated on both captain's and first officer's indicators from static air pressure information, and by fine altitude signals from the air data computer to the captain's altimeter.
E. The air data computer system electrically integrates and computes from pitot static pressures, the corrected altitude, mach number, and airspeed signals. This data is sent to the ATC transponder, autopilot, flight director, mach trim, and other systems shown in Fig. 6. Power to operate the computer is obtained from circuit breaker panel P18. Provisions are included for the installation of a second air data computer system.
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