N74420

Substantial
None

Grumman AA5S/N: AA5B-0222

Accident Details

Date
Monday, July 23, 2018
NTSB Number
CEN18LA292
Location
Brazoria, TX
Event ID
20180723X31358
Coordinates
28.984722, -95.539169
Aircraft Damage
Substantial
Highest Injury
None
Fatalities
0
Serious Injuries
0
Minor Injuries
0
Uninjured
2
Total Aboard
2

Probable Cause and Findings

The propeller blade separation due to a fatigue fracture.

Aircraft Information

Registration
N74420
Make
GRUMMAN
Serial Number
AA5B-0222
Engine Type
Reciprocating
Year Built
1975
Model / ICAO
AA5AA5
Aircraft Type
Fixed Wing Single Engine
No. of Engines
1

Registered Owner (Historical)

Name
RJM-AV8 LLC
Address
1911 LAZY HOLLOW LN
Status
Deregistered
City
PEARLAND
State / Zip Code
TX 77581-1713
Country
United States

Analysis

On July 23, 2018, about 1215 central daylight time, a Grumman AA-5B, N74420, was substantially damaged while maneuvering near Brazoria, Texas. The flight instructor and student pilot were not injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 instructional flight.

According to the student pilot, the airplane began to shake violently while he practiced basic-attitude maneuvers under simulated instrument meteorological conditions. A reduction of engine power revealed that the one of the propeller blades had separated about midspan. The flight instructor took control of the airplane and completed an uneventful forced landing in a nearby field. A postaccident examination revealed several fractured engine mounts.

The two-blade propeller, a McCauley Propeller Systems model No. 1A170/FFA7563, serial No. P77410, was examined at the National Transportation Safety Board Materials Laboratory in Washington, D.C. About one-half of one blade had separated and was not located during the investigation. The fracture surface was flat from the trailing edge through roughly two-thirds of the chord length, before angling from the center outwards adjacent to the blade surface. Further examination of the flat portion of the fracture surface revealed a pattern of crack arrest lines and striations that were consistent with fatigue cracking. The pattern of crack arrest lines indicated that the fatigue cracking emanated from the trailing edge tip of the blade. Damage to the fracture surface at the trailing edge tip of the blade obscured the exact initiation point of the fatigue cracking. According to the propeller logbook, the most recent propeller inspection was completed in conjunction with an annual inspection on November 1, 2017, at which time the propeller had accumulated 4,488 hours since its last overhaul. The airplane had been flown about 11 hours since the last annual inspection.

Data Source

Data provided by the National Transportation Safety Board (NTSB). For more information on this event, visit the NTSB Records Search website. NTSB# CEN18LA292