(d)
Switch system B spoilers to ON. With control wheel centered, position speed brake handle mid way between ARMED and FLIGHT detents. Record difference between steps (c) and (d) as null leakage for flight spoilers No. 2 and 7. Check that flow does not exceed 4000 cc/min.
(e)
Switch system B flight controls to ON. Record difference between steps (d) and (e) as null leakage for the aileron power control unit. Check that flow does not exceed 3000 cc/min.
(f)
Open No. 6 isolation valve. Record difference between steps (e) and (f) as null leakage for elevator power control unit and tab lock cylinder. Check that flow does not exceed 3000 cc/min.
(g)
Open No. 5 isolation valve. Record difference between steps (f) and (g) as null leakage for rudder power control unit. Check that flow does not exceed 3000 cc/min.
(h)
Open No. 4 isolation valve. Record difference between steps (g) and (h) as leakage for feel computer null and for feel cylinders. Check that flow does not exceed 1500 cc/min.
(i)
Switch off system B spoilers and system B flight controls. Record reading for system B basic reference.
(j)
Close No. 4, 5 and 6 isolation valves and open ground interconnect valve. Record difference between steps (i) and (j) as reference flow which includes system A relief valve and ground spoilers. Check that flow does not exceed 500 cc/min.
(k)
Position flap handle to 25 units, position alternate flap switch off and let flaps stabilize. Record difference between steps (j) and (k) as leakage for T.E. flap control valve at null position. Check that flow does not exceed 8000 cc/min.
(l)
Switch system A spoilers on with control wheel centered and speed brake handle midway between armed and flight detent. Record difference between steps (k) and (l) as null leakage for flight spoilers No. 3 and 6. Check that flow does not exceed 4000 cc/min.
(m)
Position system A flight controls switch on. Record difference between steps (l) and
(m) as null leakage for aileron PCU. Check that flow does not exceed 3000 cc/min.
(n)
Open No. 3 isolation valve. Record difference between steps (m) and (n) as leakage for elevator PCU null and tab lock cylinder. Flow shall not exceed 3000 cc/min.
(o)
Open No. 2 isolation valve. Record difference between steps (n) and (o) as null leakage for the rudder PCU. Flow shall not exceed 3000 cc/min.
(p)
Open No. 1 isolation valve. Record difference between steps (o) and (p) as leakage for the feel computer null and feel cylinder. Flow shall not exceed 1500 cc/min.
(q)
Place landing gear handle in down position. Record difference between steps (p) and
(q) as leakage for nose gear and steering valve. Flow shall not exceed 1500 cc/min.
(r)
Determine from flow reading if procedure 3 or 4 are required. If not, restore airplane to normal per par. C.(8).
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Page 611
(6) Check Internal Leakage (Procedure 3)
NOTE: The following procedure provides an entire leakage check. Portions of this check may be accomplished as required.
(a)
Prepare for check per par. C.(3).
NOTE: If ammeter is being used, set for highest range.
(b)
With system B pump ON, record reading for system B basic reference.
NOTE: When ammeter is being used, record amp reading for each step to the nearest 0.1 amp. When flowmeter is being used record reading for each step to the nearest 100 cc/min.
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29-00 Page 612 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/77
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
1. System B basic reference [Step 1.C.(5)(c)] a. Null leakage spoilers 2
and 7 [Step 1.C.(5)(d)] b. Null leakage aileron PCU
a-1 4000
[Step 1.C.(5)(e)] c. Null leakage elevator PCU
b-a 3000
and tab lock cylinder [Step 1.C.(5)(f)] d. Null leakage rudder PCU
c-b 3000
[Step 1.C.(5)(g)] e. Null leakage feel cylinder
d-c 3000
and computer [Step 1.C.(5)(h)]
e-d 1500
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