(c)
Let the air conditioning packs operate until the conditioned air in the airplane has no smell of the oil contamination.
(d)
Set the L and R PACK switches to OFF.
(e)
Stop the APU (Ref 49-11-0).
(f)
Set the APU BLEED switch to OFF.
(16)
Start the engines and let the engines operate at ground idle speed (Ref 71-00-00).
(17)
Operate the air conditioning packs:
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NOTE: This procedure uses the engine bleed air to remove the oil contamination from the air conditioning system.
(a)
Set the position of these switches on the P5-10 panel as follows:
1) L and R PACK switches to AUTO
2) BLEED 1 and 2 switches to ON
(b)
Let the air conditioning packs operate until the conditioned air in the airplane has no smell of the oil contamination.
(c)
Set the L and R PACK switches to OFF.
(18)
Stop the engines (Ref 71-09-100).
(19)
Set these switches to OFF at the P5-10 panel:
(a)
L and R PACK switches
(b)
GASPER FAN
(20)
Examine these components for oil contamination:
(a)
Heat exchangers
(b)
Coalescer bags in the water separators
(c)
Gasper air fan filters (on some airplanes only)
(21)
Do the procedure again, if required, until the conditioned air in the airplane has no smell of the oil contamination.
(22)
Close the access doors to the air conditioning bays.
(23)
Remove the electrical power if it is not necessary (Ref 24-22-00\MP).
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AIRPLANE ABILITY TO MAINTAIN CABIN PRESSURE
IN FLIGHT ON SINGLE PACK OPERATION - TROUBLE SHOOTING
1. General
A. Trouble shooting the airplane ability to maintain cabin pressure in flight on a single pack operation involves the air cycle system, the pneumatic supply system, the pressurization control system, and various airplane openings that could possibly be a source of leakage. An understanding of how the different components are interrelated as well as the function of each is needed to locate and correct problems in either system.
2. Preparation for Trouble Shooting
A. Supply electrical power (Ref 24-22-00 MP).
B. Make sure that all air conditioning circuit breakers are on.
C. Make sure that all pressurization control system circuit breakers are on.
3. Trouble Shooting Chart (Fig. 101)
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May 01/01 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 21-00-05 Page 101
SYSTEM MINIMUM REQUIREMENT REQUIREMENT SATISFIED
YES NO
SINGLE PACK - GROUND IDLE ABLE TO MAINTAIN CABIN DIFFERENTIAL PRESSURE OF 3.9 - 4.1 PSID AND CABIN RATE OF CHANGE IS NO MORE THAN -100 FEET/MINUTE CONFIDENCE IS FAIR THAT AIRPLANE WILL MAINTAIN PRESSURE WITH SINGLE PACK WHILE AT CRUISE. CONFIDENCE IS LOW THAT AIRPLANE WILL MAINTAIN PRESSURE ON SINGLE PACK AT CRUISE. EMPHASIS NEEDS TO BE PLACED ON THE FOLLOWING OUTFLOW WAS AIRPLANE LEAK DOWN DURING PART III (REF 21-00-05 MP) LESS THAN 100 SECONDS? IF SO, FIRST CHECK FOR CABIN LEAKS THEN RUN PART III TEST AGAIN. INFLOW IF THE CABIN LEAK DOWN RATE WAS ACCEPTABLE, THEN THE PACK PERFORMANCE NEEDS TO BE INVESTIGATED. DO VARIOUS PACK SYSTEM HEALTH CHECKS (REF 21-11-0 A/T).
SINGLE PACK - 65% N2 CABIN RATE OF CHANGE IS -500 FEET/MINUTE OR GREATER CONFIDENCE IS HIGH THAT AIRPLANE WILL MAINTAIN PRESSURE WITH SINGLE PACK WHILE AT CRUISE.
Airplane Ability to Maintain Cabin Pressure in Flight 500
21-00-05 on Single Pack Operation -Trouble Shooting May 01/01
Page 102 Figure 101 (Sheet 1)
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
SYSTEM MINIMUM REQUIREMENT REQUIREMENT SATISFIED
YES NO
AIRPLANE/STRUCTURE AIR LEAKAGE LEAK DOWN RATE FROM 4.0 TO 2.5 PSID IS GREATER THAN OR EQUAL TO 100 SECONDS CABIN LEAKAGE IS ACCEPTABLE OPERATORS MAY WISH TO CONSIDER CONDUCTING (REF 5-51-91 MD) LEAKAGE TEST ON C-CHECK BASIS AND MONITOR PERFORMANCE. INSPECT AND REPAIR ANY AIR LEAKAGE AS NOTED ON THE DATA SHEET. SPECIFICALLY: DOORS AND HATCHES -MISSING OR TORN SEALS, POOR CONTACT BETWEEN DOOR SEALS AND AIRPLANE DUE TO DIRT, ETC., INSPECT SEALING COMPOUND AREAS AND REPAIR DOOR SEALS (REF 21-43-11 R/I). FORWARD OUTFLOW VALVE -DO A TEST OF THE VALVE (REF 52-09-100 AP). EE COOLING VALVE -P/N 10-60701-1 THROUGH -6 SHOULD CLOSE AT 2.0 TO 2.8 PSID AND THE -7 VALVE SHOULD CLOSE AT .7 TO 1.1 PSID. BILGE DRAINS - SHOULD CLOSE AT APPROXIMATELY 2.0 PSID. - CABIN PRESSURE SAFETY RELIEF VALVE - OUTFLOW VALVE SEAL - NEGATIVE PRESSURE RELIEF VALVE SEAL - WATER SERVICE PANEL -FLIGHT DECK WINDOWS - PRESSURE BULKHEAD PENETRATIONS SHOULD ALL HAVE MINIMAL LEAKAGE - SIGNIFICANT LEAKS SHOULD BE RESOLVED AS REQUIRED.
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