500 Internal Leakage Test Data Sheet - Procedure 2
May 01/00 (Sheet 1) 29-00
Page 612A
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
A/P No. ____________ Pump Mfr. __________ Ser. No. ____________ Date _______________ Pump Used: No. 1 or No. 2 Recorded Amps Amp Change Flow (cc/min) (Fig. 604) Max Flow Limit (cc/min)
Cumulative Increment
f. Establish new system B reference [Step 1.C.(5)(i)] g. System A reference flow including relief valve and
ground spoilers [Step 1.C.(5)(j)] h. Null leakage trailing edge
g-f 500
flap control [Step 1.C.(5)(k)] i. Null leakage flight spoilers
h-g 8000
3 and 6 [Step 1.C.(5)(l)] j. Null leakage aileron PCU
i-h 4000
[Step 1.C.(5)(m)] k. Null leakage elevator PCU
j-i 3000
and tab lock cylinder [Step 1.C.(5)(n)] l. Null leakage rudder PCU
k-j 3000
[Step 1.C.(5)(o)] m. Null leakage feel cylinder
l-k 3000
and computer [Step 1.C.(5)(p)] n. Null leakage nose gear
m-l 1500
and steering valve [Step 1.C.(5)(q)]
n-m 1500
Internal Leakage Test Data Sheet -Procedure 2 500
29-00 (Sheet 2) May 01/00
Page 612B
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(c)
Switch system B spoilers to ON. Record difference between steps (b) and (c) as leakage with flight spoilers No. 2 and 7 retracted. Check that flow does not exceed 500 cc/min.
(d)
Position control wheel approximately 40 degrees clockwise. Record difference between steps (c) and (d) as null leakage for flight spoiler No. 7. Check that flow does not exceed 2000 cc/min.
(e)
Position control wheel approximately 40 degrees counterclockwise. Record difference between steps (c) and (e) as null leakage for flight spoiler No. 2. Check that flow does not exceed 2000 cc/min.
(f)
With control wheel centered, position speed brake handle half way between ARMED and FLIGHT detent. Record difference between steps (b) and (f) as null leakage for flight spoilers No. 2 and 7. Check that flow does not exceed 4000 cc/min.
(g)
Position speed brake handle to DOWN, switch system B spoilers to OFF and record reading as new basic reference flow.
(h)
Switch system B flight controls to ON. Record difference between steps (g) and (h) as null leakage for aileron power control unit. Check that flow does not exceed 3000 cc/min.
(i)
Position control wheel fully clockwise against wheel stops. Record difference between steps (g) and (i) as aileron cylinder and bleed leakage. Check that flow does not exceed 1500 cc/min. If flow exceeds 1500 cc/min, center control wheel and repeat check.
(j)
With control wheel centered, record reading as new basic reference flow.
(k)
Deleted.
(l)
Deleted.
(m)
Open No. 6 isolation valve. Record difference between steps (j) and (m) as null leakage for elevator power control unit and tab lock cylinder. Check that flow does not exceed 3000 cc/min.
(n)
Position control column fully aft against column stops. Record difference between steps (j) and (n) as elevator cylinder and bleed leakage. Check that flow does not exceed 1500 cc/min. If flow exceeds 1500 cc/min, return column to neutral and repeat test.
(o)
With control column in neutral record reading as new basic reference flow.
(p)
Deleted
(q)
Deleted
(r)
Open No. 5 isolation valve. Record difference between steps (o) and (r) as null leakage for rudder power control unit. Check that flow does not exceed 3000 cc/min.
(s)
Push rudder pedal for full right rudder against pedal stops. Record difference between steps (o) and (s) as rudder cylinder and bleed leakage. Check that flow does not exceed 1200 cc/min. If flow exceeds 1200 cc/min. center the pedals and repeat test.
(t)
With rudder pedals in neutral and autopilot system select switch on B, position yaw damper OFF and record reading as new basic reference flow.
(u)
With rudder pedals in neutral, switch yaw damper to ON. Record difference between steps (t) and (u) as rudder electrohydraulic servo valve leakage. Check that flow does not exceed 2000 cc/min.
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