(2)
Adjust fuel flow PMF.
(a)
Using PDC CDU, determine current PMF pin connection as follows: 1) Position mode selector to STBY. 2) Press minus (-) key. 3) Using page key, advance to TEST page 3. Note PMF index level on row 6
columns 11 and 12.
(b)
Open PDC circuit breaker on P18 circuit breaker panel.
(c)
Connect PDC wiring as indicated in Fig. 502.
(d)
Close PDC circuit breaker.
(e)
Repeat step (2) (a) 1) thru (2) (a) 3) to confirm new fuel model PMF connection.
(f)
Monitor fuel flow %. WF on future flights to determine possible additional adjustments.
(g)
If no further adjustments are required, perform Restore to Normal.
5A7
Jun 20/84 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 34-18-0 Page 511
Adjustments Fuel Flow PMF 5A7
34-18-0 Figure 502 Jun 20/84
Page 512
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
E. Drag PMF Adjustment
(1)
General
(a)
Performance data computer K-factor may vary from flight to flight due to items such as trim drag associated with airplane loading, inaccurate zero fuel weight, or varying atmospheric pressure isobars during flight. Pin adjustment may be performed, at the operator's discretion, when an average K-factor over many flights indicates a deviation of one percent or more.
(b)
Percent deviations are from current drag model value.
(c)
K-factor values indicate percent deviation directly; for example: 1.02 indicates a +2 percent deviation, 0.98 indicates a -2 percent deviation.
(d)
The following drag producing devices are not indicated in the baseline drag level: Single HF wire +0.25 Dual HF wire +0.50 Low pressure tires +1.25 Gravel runway kit +1.75
(2)
Adjust drag PMF
(a)
Calculate drag percent deviation value for adjustment.
(b)
Using PDC CDU, determine current drag PMF pin connection as follows: 1) Position mode selector on PDC CDU to STBY. 2) Press minus (-) key. 3) Using page key, advance to final page of TEST pages (4 of 4 or 6 of 6).
Note PMF index level on row 2 columns 1 and 2.
(c)
Open PDC circuit breaker on P18 circuit breaker panel.
(d)
Connect PDC wiring as indicated in Fig. 503.
(e)
Close PDC circuit breaker.
(f)
Repeat step (2) (b) 1) thru (2) (b) 3) to confirm new drag model PMF connection.
(g)
Monitor system K-factor on future flights to determine possible additional adjustment.
(h)
If no further adjustments are required, perform Restore to Normal.
5A7
Jun 20/84 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 34-18-0 Page 513
Adjustments Drag PMF 5A7
34-18-0 Figure 503 Jun 20/84
Page 514
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
6. Restore to Normal
A. Pull command bug set knobs on EPR indicators to the out position.
CAUTION: WITH THE PDCS INOPERATIVE OR TURNED OFF, SET EPR AND MACH/AIRSPEED COMMAND BUGS TO MANUAL MODE OR EXCESSIVE WEAR TO COMMAND INDEX CLUTCH WILL OCCUR.
B. Open PDCS and PDC MODE ANN circuit breakers on P18 panel.
C. Circuit breakers associated with systems as specified in par. 1. C. should be opened if no longer required.
D. Move mode selector to STBY.
E. Set all air conditioning and anti-ice system bleed air switches to off.
F. Remove electrical power from airplane if no longer required.
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Jun 20/84 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 34-18-0 Page 515
PERFORMANCE DATA COMPUTER - REMOVAL/INSTALLATION
1. General
A. The Performance Data Computer is located on the E1-1 electronic rack, top shelf, station 297.5, in the forward electronics bay. The PDC is held to the tray assembly with lever latches on the bottom front of PDC.
2. Referenced Procedures
A. 34-18-0, Performance Data Computer - Adjustment/Test
B. 20-10-111, Electrical/Electronic Black Box - Maintenance Practices
3. Performance Data Computer Removal
A. Ensure that PDCS circuit breaker on the P18 panel is open and tagged with do-not-operate identifiers.
B. Gain access to forward electronics bay.
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