TB 1--1520--240--20--135
e.
Maintenance Trainers (Category A and B). Comply no later than 12 August 2001.
f. Component/Parts in Stock at All Levels (Depot and Others) including War Reserves - Upon receipt
of this Technical Bulletin, Depot and Materiel Activity Commanders will ensure the materiel condition tags of
all items in all condition codes listed in paragraph 7 are annotated to read "CH-47-01-ASAM-07 (TB
1--1520--240--20--135), inspection for untested flight safety part (FSP) bolts, P/N 114R3650-13 and
114R3650-15, not complied with."
(1) Wholesale Stock --N/A.
(2) Retail Stock -- Upon receipt of this Technical Bulletin, Commanders and Facility Managers
maintaining retail stock at Installation level and below shall contact the supported aviation unit to perform the
procedures required in accordance with paragraphs 8 and 9 on suspect materiel. Dispose of discrepant mate-
riel in accordance with paragraph 10d.
g. Components/Parts in Work (Depot Level and Others) -- Depot and other Maintenance Activity Com-
manders will ensure items listed in paragraph 7 are not issued until they are in compliance with this Technical
Bulletin.
2. Task/Inspection Suspense Date. Complete the inspection in accordance with paragraph 8 at the next
phase inspection but no later than 01 March 2002, and report in accordance with paragraph 14b.
than 7 March 2001.
4.
Summary of the Problem.
a. The original qualification (fatigue testing) of flight safety parts was done by Boeing Helicopters under
Army direction. The fatigue testing of these parts substantiated their service life and the parts design was
considered qualified. In October 1995 a change in the Army flight safety part (FSP) policy required that parts
manufactured by authorized vendor/suppliers and orginally qualified by the prime contractor must be fatigue
tested. The 114R3650-13 and 114R3650-15 bolts are flight safety parts. The 114R3650-13 bolt (three per
rotor head) is superseded and replaced by the improved 114R3650-16 bolt, and is used to attach the upper
end of each pitch link to the pitch arm on both the forward and aft rotor heads. The 114R3650-15 bolt (three
per rotor head) is superseded and replaced by the improved 114R3650-17 bolt, and is used to attach the lower
end of each pitch link to the swashplate on both the forward and aft rotor heads. Some of the 114R3650-13
and -15 bolts were fielded without being qualified as an alternate source by fatigue testing.
b.
For manpower/downtime and funding impacts see paragraph 12.
c.
The purpose of this Technical Bulletin is to -
(1) Inspect all 114R3650-13 and 114R3650-15 bolts installed on H-47 aircraft, installed on spare
rotor heads, and in stock.
(2) Replace all 114R3650-13 and 114R3650-15 bolts that do not have the approved CAGE Code
or manufacturers name on the bolts with improved 114R3650-16 and 114R3650-17 bolts respectively.
5.
End Items to be inspected . All H--47 series aircraft.
Assembly Components to be Inspected. N/A.
Parts to be Inspected . --
NOMENCLATURE
PART NUMBER
NATIONAL STOCK NUMBER
BOLT ASSEMBLY
114R3650-13
N/A
(replaced by 114R3650-16)
BOLT ASSEMBLY
114R3650-15
N/A
(replaced by 114R3650-17)
2
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