TB 1-1520-238-20-84
3.
Reporting Compliance Suspense Date. No later than 30 December 1996 per para 14a of this TB.
4.
Summary of the Problem.
a.
The Utah ANG reported (via a Category 1 Deficiency report) chafing and subsequent arcing and
burning of the ALQ-144 radar jammer power lines on the aft mixer support bellcrank upon power up of the radar jammer.
Without proper clamping and routing, chafing may occur when the collective is full up and the cyclic is forward, similar to
a condition when the aircraft is in a 30o dive.
b.
For manpower/downtime and funding impacts refer to paragraph 12.
c.
The purpose of the TB is to initiate a one-time inspection of the suspected area and direction to repair
and reroute, as required.
5.
End Items to be Inspected. All AH-64 aircraft will be inspected.
6.
Assembly Components to be Inspected. N/A.
7.
Parts to be Inspected.
NOMENCLATURE
PART NUMBER
NATIONAL STOCK
NUMBER
Wire Harness (W119)
7-311 B24119-087
N/A
Bellcrank
7-311511125
8.
Inspection Procedures.
a.
Remove access panels L200 and T225.
b.
Locate ALQ-144 power cables along FS 219. With P949 connector connected to the transmitter and then
again in the stow position, place the collective full up and the cyclic full forward. Note any contact between cables and
bellcrank. No chafing is allowed. Any evidence of chafing requires repair in accordance with TM 1-1500-204-23. Note
any evidence of damage to the bellcrank, and replace if required in accordance with TM 1-1520-238-23.
9.
Correction Procedures.
a.
Cables are usually securely fastened along the forward side of fuselage station 219 using two clamps, one
attached directly onto the FS 219 frame and the other on the "L" bracket located approximately at 5.750 RBL and 185
WL. If installed and proper clearance is verified in all configurations, or if clearance of at least 1 -inch exists without the
clamp installed on the "L" bracket, the inspection is complete.
NOTE
When these cables are rerouted, they will be stiff and should be carefully formed to ensure stress
is limited to the connector as these cables are soldered onto the connector.
b.
Aircraft not meeting these requirements will require installation of the clamp onto the "L" bracket using the
appropriate hardware. The L-bracket is typically the one that is not installed. Verify proper clearance in all
configurations.
10.
Supply/Parts and Disposition.
a.
Parts Required. Items cited in paragraph 7 may be required to replace defective items.
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