AD 2018-16-11
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Various | Model 234 and Model CH-47D | Airworthiness Directives; Various Model 234 and Model CH-47D Helicopters |
Unsafe Condition
cracking in the pitch housing lugs, located on the lead side of the lower vertical pin lug, due to fatigue and underestimated load conditions in the original life limit calculations.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
repetitive eddy current and ultrasonic inspections of the pitch housing, removing the pitch housing from service when it accumulates a total of 8,200 hours time-in-service (TIS), and revising the pitch housing retirement life.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 50 flight hours
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Affected Aircraft
Model 234 and Model CH-47D helicopters with a pitch housing part number (P/N) 145R2075-11, 145R2075-12, 145R2075-13, 145R2075-14, 145R2075-15, 145R2075-16, 234R2075-1, or 234R2075-2 installed.
AI-generated summary from the source AD text. Verify against the official source before acting.
Source: Official FAA Source ↗
Retrieved: Apr 4, 2026
Rights: U.S. Government Public Domain
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