code

MD

Crash of a Cessna 402B off Easton: 1 killed

Date & Time: Jul 16, 2024 at 0932 LT
Type of aircraft:
Registration:
N7875E
Flight Type:
Survivors:
No
Schedule:
Fort Meade - Easton
MSN:
402B-0432
YOM:
1973
Crew on board:
1
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
1
Circumstances:
On approach to Easton-Newman Field Airport Runway 04, MD, the pilot lost control of the airplane that crashed into the Tred Avon River. The wreckage was found about 7 km short of runway. The airplane sank and the pilot was killed. The pilot apparently reported engine problem on final.

Crash of an Embraer EMB-500 Phenom 100 in Gaithersburg: 6 killed

Date & Time: Dec 8, 2014 at 1041 LT
Type of aircraft:
Operator:
Registration:
N100EQ
Flight Type:
Survivors:
No
Site:
Schedule:
Chapel Hill - Gaithersburg
MSN:
500-00082
YOM:
2009
Crew on board:
1
Crew fatalities:
Pax on board:
2
Pax fatalities:
Other fatalities:
Total fatalities:
6
Captain / Total flying hours:
4737
Captain / Total hours on type:
136.00
Aircraft flight hours:
634
Aircraft flight cycles:
552
Circumstances:
The airplane crashed while on approach to runway 14 at Montgomery County Airpark (GAI), Gaithersburg, Maryland. The airplane impacted three houses and the ground about 3/4 mile from the approach end of the runway. A postcrash fire involving the airplane and one of the three houses, which contained three occupants, ensued. The pilot, the two passengers, and the three people in the house died as a result of the accident. The airplane was destroyed by impact forces and postcrash fire. The flight was operating on an instrument flight rules flight plan under the provisions of 14 Code of Federal Regulations (CFR) Part 91. Visual meteorological conditions prevailed at the time of the accident. Data from the airplane’s cockpit voice and data recorder (CVDR) indicated that the takeoff about 0945 from Horace Williams Airport, Chapel Hill, North Carolina, and the cruise portion of the flight were uneventful. CVDR data showed that about 15 minutes after takeoff, the passenger in the right cockpit seat made a statement that the airplane was “in the clouds.” A few seconds later, the airplane’s engine anti-ice system and the wing and horizontal stabilizer deice system were manually activated for about 2 minutes before they were manually turned off. About 6 minutes later, a recording from the automated weather observing system (AWOS) at GAI began transmitting over the pilot’s audio channel, containing sufficient information to indicate that conditions were conducive to icing during the approach to GAI. The CVDR recorded no activity or faults during the rest of the flight for either ice protection system, indicating that the pilot did not turn the systems back on. Before the airplane descended through 10,000 ft, in keeping with procedures in the EMB-500 Pilot Operating Handbook, the pilot was expected to perform the Descent checklist items in the Quick Reference Handbook (QRH), which the pilot should have had available in the airplane during the flight. Based on the AWOS-reported weather conditions, the pilot should have performed the Descent checklist items that appeared in the Normal Icing Conditions checklist, which included turning on the engine anti-ice and wing and horizontal stabilizer deice systems. That action, in turn, would require the pilot to use landing distance performance data that take into account the deice system’s activation. CVDR data show that, before beginning the descent, the pilot set the landing reference (Vref) speed at 92 knots, indicating that he used performance data for operation with the wing and horizontal stabilizer deice system turned off and an airplane landing weight less than the airplane’s actual weight. Using the appropriate Normal Icing Conditions checklist and accurate airplane weight, the pilot should have flown the approach at 126 knots (a Vref of 121 knots +5 knots) to account for the icing conditions.
Probable cause:
The National Transportation Safety Board determines that the probable cause of this accident was the pilot’s conduct of an approach in structural icing conditions without turning on the airplane’s wing and horizontal stabilizer deice system, leading to ice accumulation on those surfaces, and without using the appropriate landing performance speeds for the weather conditions and airplane weight, as indicated in the airplane’s standard operating procedures, which together resulted in an aerodynamic stall at an altitude at which a recovery was not possible.
Final Report:

Crash of a Socata TBM-700 in Gaithersburg

Date & Time: Mar 1, 2010 at 1715 LT
Type of aircraft:
Operator:
Registration:
N700ZR
Flight Type:
Survivors:
Yes
Schedule:
Chapel Hill - Gaithersburg
MSN:
87
YOM:
1993
Crew on board:
1
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
0
Captain / Total flying hours:
4215
Captain / Total hours on type:
1240.00
Circumstances:
The pilot of the single-engine turboprop was on an instrument flight rules (IFR) flight and cancelled his IFR flight plan after being cleared for a visual approach to the destination airport. He flew a left traffic pattern for runway 32, a 4,202-foot-long, 75-foot-wide, asphalt runway. The pilot reported that the airplane crossed the runway threshold at 81 knots and touched down normally, with the stall warning horn sounding. The airplane subsequently drifted left and the pilot attempted to correct with right rudder input; however, the airplane continued to drift to the left side of the runway. The pilot then initiated a go-around and cognizant of risk of torque roll at low speeds did not apply full power. The airplane climbed to about 10 feet above the ground. At that time, the airplane was in a 20-degree left bank and the pilot applied full right aileron input to correct. The airplane then descended in a left turn, the pilot retarded the throttle, and braced for impact. A Federal Aviation Administration inspector reported that the airplane traveled about 100 feet off the left side of the runway, nosed down in mud, and came to rest in trees. Examination of the wreckage by the inspector did not reveal any preimpact mechanical malfunctions, nor did the pilot report any. The reported wind, about the time of the accident, was from 310 degrees at 10 knots, gusting to 15 knots.
Probable cause:
The pilot’s failure to maintain aircraft control while performing a go-around.
Final Report:

Crash of a Douglas DC-10-30ER in Baltimore

Date & Time: May 6, 2009 at 1302 LT
Type of aircraft:
Operator:
Registration:
N139WA
Survivors:
Yes
Schedule:
Leipzig – Baltimore
MSN:
46583/292
YOM:
1979
Flight number:
WOA8535
Crew on board:
12
Crew fatalities:
Pax on board:
168
Pax fatalities:
Other fatalities:
Total fatalities:
0
Captain / Total flying hours:
6500
Captain / Total hours on type:
193.00
Copilot / Total flying hours:
6300
Copilot / Total hours on type:
373
Aircraft flight hours:
107814
Circumstances:
The flight was conducting a straight-in approach during visual meteorological conditions. The approach was backed up by an ILS and was stable at 500 feet above touchdown. The initial touchdown was firm and main landing gear rebounded, possibly bouncing slightly off the runway. Control column input and possibly momentum from the touchdown resulted in a rapid pitch down and hard nose gear impact with the runway. Wing spoilers likely did not deploy due to the main gear bounce and/or throttle position. Following the nose gear impact, the airplane pitched up as expected and the column was held in a slightly forward position. Airspeed rapidly decayed, and engine power began to increase as the airplane pitch reversed to a downward motion for a second time. One of the crew, likely the FO, called “flare flare” and the column recorded a rapid nose up input, followed by a rapid nose down input, and the nose gear again struck the runway very hard, likely causing the majority of the damage at that point. Following the second nose gear impact, column inputs stabilized at a slightly nose up command, power was set on all three engines, and the go-around was successfully executed. A slight lag in the power increase on engine number 3 may have contributed to the nose down motion leading to the second nose gear impact, although the large forward (airplane nose down) column movement appears to be a much more significant contributor. It is unclear why the engine was slower to increase. Throttle lever angle was not recorded, but the engine operated as expected for all other phases of the flight, including after the impact, therefore it is possible the pilot did not advance the number 3 throttle concurrently with the others. The captain’s flight and duty schedule complied with Federal Aviation regulations, but he experienced a demanding 10-day trip schedule prior to the incident involving multiple time zone crossings and several long duty periods, and reported difficulties sleeping prior to the accident leg. The captain was likely further affected by a digestive system upset during the accident flight. It is likely that the captain’s performance was degraded by fatigue and some degree of physical discomfort brought on by a short-term illness. The captain had recently completed upgrade training to DC-10, having previously been flying as an MD-11 first officer. The training program was fragmented over approximately ten months, and while in accordance with FAA regulations, may have adversely affected his consolidation of skills and experience.
Probable cause:
The captain’s inappropriate control inputs following a firm landing, resulting in two hard nose-gear impacts before executing a go-around. Contributing to the inappropriate control inputs was the captain’s fatigue and physical discomfort; and a possible lack of practical consolidation of skills and experience due to a protracted and fragmented training period.
Final Report:

Crash of a Rockwell Aero Commander 560F in Cumberland: 4 killed

Date & Time: Oct 14, 2007 at 1030 LT
Operator:
Registration:
N6370U
Flight Phase:
Flight Type:
Survivors:
No
Schedule:
Cumberland - Atlantic City
MSN:
560-1416-68
YOM:
1964
Crew on board:
1
Crew fatalities:
Pax on board:
3
Pax fatalities:
Other fatalities:
Total fatalities:
4
Captain / Total flying hours:
21000
Aircraft flight hours:
3705
Circumstances:
The airplane was loaded to within a few hundred pounds of its maximum gross takeoff weight, and departed from an airport located in a valley, surrounded by rising terrain. Although visual conditions prevailed at the accident airport, fog was present in the adjacent valleys. During the initial climb after takeoff, the right engine lost partial power due to a failure of the number one cylinder exhaust valve. The pilot secured the right engine; however, he was unable to maintain a climb with only the left engine producing power. The airplane was manufactured in 1964. Review of weight and performance data published at the time of manufacture, revealed that the airplane should have been able to climb about 400 feet-per-minute with a single engine producing power. No current weight and balance data was recovered, and due to impact and fire damage, the preimpact power output of the left engine could not be determined. Both engines were last overhauled slightly more than 12 years prior to the accident, and flown about 310 hours during that time. For the make and model engine, the manufacturer recommended overhaul at 1,200 hours of operation, or during the twelfth year.
Probable cause:
A partial power loss in the right engine due to the failure of the number one exhaust valve, and the airplane's inability to maintain a climb on one engine for unknown reasons. Contributing to the accident were fog and rising terrain.
Final Report:

Crash of a Beechcraft 200 Super King Air in Leonardtown

Date & Time: Oct 12, 2006 at 1216 LT
Operator:
Registration:
N528WG
Flight Type:
Survivors:
Yes
Schedule:
Leonardtown - Leonardtown
MSN:
BB-151
YOM:
1979
Crew on board:
2
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
0
Captain / Total flying hours:
7140
Captain / Total hours on type:
900.00
Copilot / Total flying hours:
1100
Copilot / Total hours on type:
59
Aircraft flight hours:
11077
Circumstances:
With all cockpit indications showing the landing gear was down and locked, the airplane touched down on the runway. Immediately after touchdown, the pilots heard the landing gear warning horn sound intermittently for several seconds, and then the right main landing gear collapsed. The airplane veered to the right, exited the runway, and came to rest. A post crash fire ensued, and the crew exited without injury. A postaccident examination of the airplane revealed that the collapsed right main landing gear had penetrated the right main fuel tank and the majority of the right side of the fuselage had been consumed by fire. Examination of the left and right main landing gear assemblies revealed, that both downlock plates had been installed backwards, providing only a fraction of the design contact area between the plate and throat of the downlock hook. Examination of the manufacturer's component maintenance manual, which was used for the assembly and installation of the left and right main landing gear, revealed no guidance regarding downlock plate orientation during installation.
Probable cause:
The airplane manufacturer's inadequate landing gear downlock plate maintenance orientation information, and the disengaged main landing gear.
Final Report:

Crash of a Mitsubishi MU-2B-60 Marquise in Baltimore: 1 killed

Date & Time: May 14, 2004 at 0724 LT
Type of aircraft:
Operator:
Registration:
N755AF
Flight Type:
Survivors:
No
Site:
Schedule:
Philadelphia - Baltimore
MSN:
755
YOM:
1980
Flight number:
EPS101
Crew on board:
1
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
1
Captain / Total flying hours:
6800
Aircraft flight hours:
6951
Circumstances:
The pilot was finishing his third round-trip, Part 135 cargo flight. The first round trip began the previous evening, about 2150, and the approach back to the origination airport resulted in a landing on runway 15R at 2305. The second approach back to the origination airport resulted in a landing on runway 28 at 0230. Prior to the third approach back to the airport, the pilot was cleared for, and acknowledged a visual approach to runway 33R twice, at 0720, and at 0721. However, instead of proceeding to the runway, the airplane flew north of it, on a westerly track consistent with a modified downwind to runway 15L. During the westerly track, the airplane descended to 700 feet. Just prior to an abeam position for runway 15L, the airplane made a "sharp" left turn back toward the southeast, and descended into the ground. Witnesses reported the airplane's movements as "swaying motions as if it were going to bank left, then right, and back left again," and "the nose...pointing up more than anything...but doing a corkscrew motion." Other witnesses reported the "wings straight up and down," and "wings vertical." Tower controllers also noted the airplane to be "low and tight," and "in an unusually nose high attitude close to the ground. It then "banked left and appeared to stall and then crashed." A post-flight examination of the wreckage revealed no evidence of mechanical malfunction. The pilot, who reported 6,800 hours of flight time, had also flown multiple round trips the previous two evenings. He had checked into a hotel at 0745, the morning prior to the accident flight, checked out at 1956, the same day, and reported for work about 1 hour before the first flight began.
Probable cause:
The pilot's failure to maintain airspeed during a sharp turn, which resulted in an inadvertent stall and subsequent impact with terrain. Factors included the pilot's failure to fly to the intended point of landing, and his abrupt course reversal back towards it.
Final Report:

Crash of a Piper PA-31-310 Navajo off Stevensville

Date & Time: May 24, 1996 at 1055 LT
Type of aircraft:
Registration:
N103RW
Flight Phase:
Flight Type:
Survivors:
Yes
Schedule:
Stevensville - Laconia
MSN:
31-223
YOM:
1968
Crew on board:
1
Crew fatalities:
Pax on board:
6
Pax fatalities:
Other fatalities:
Total fatalities:
0
Captain / Total flying hours:
2000
Captain / Total hours on type:
600.00
Aircraft flight hours:
3812
Circumstances:
The pilot reported that he ran the engines to full power before releasing the brakes. Immediately after lift-off, when he retracted the landing gear, he noticed a dramatic loss of airspeed. The airplane began to rock back and forth, and the pilot's efforts to increase the airspeed including lowering the nose and adding full power was unsuccessful. According to the Piper Information Manual for a short field takeoff, a lift-off speed of 85 mph and 15 degree of flaps is required. The reported winds were 010 degrees at 7 knots. The pilot departed runway 29 which is 2910 feet long. A witness who was refueling an airplane on the ramp stated that the airplane was still on the runway at the 500 foot mark from the end of runway 29.
Probable cause:
The pilot's improper short field takeoff/procedure and selection of the wrong runway for takeoff.
Final Report:

Crash of a Piper PA-46-310P Malibu in Cambridge: 1 killed

Date & Time: Mar 15, 1995 at 0512 LT
Operator:
Registration:
N166CP
Flight Phase:
Flight Type:
Survivors:
No
Schedule:
Cambridge - Baltimore
MSN:
46-8408024
YOM:
1984
Crew on board:
1
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
1
Captain / Total flying hours:
9600
Aircraft flight hours:
6089
Circumstances:
The airplane collided with trees shortly after takeoff and came to rest in a church yard. There were no witnesses to the crash; however, several local residents heard the airplane overfly their homes at a low altitude. One resident stated that he heard the airplane collide with the trees. Another resident stated that he heard the engine operating as the airplane flew low overhead. Both residents reported that reduced visibility hampered their ability to find the wreckage. One resident estimated that the visibility was about 50 to 60 feet. The prescribed takeoff minimums for that airport is 300 feet and 1 mile visibility. Examination of the airplane did not disclose evidence of mechanical malfunction. The pilot, sole on board, was killed.
Probable cause:
The commercial/instrument rated pilot's failure to obtain/maintain adequate altitude/clearance during the initial climb after takeoff. Related factors are the pilot's poor planning/decision making, and the fog.
Final Report:

Crash of a Volpar Turboliner 18 in Baltimore: 1 killed

Date & Time: Dec 10, 1992 at 1535 LT
Type of aircraft:
Operator:
Registration:
N7770B
Flight Type:
Survivors:
No
Schedule:
Dayton - Baltimore
MSN:
AF-320
YOM:
1951
Crew on board:
1
Crew fatalities:
Pax on board:
0
Pax fatalities:
Other fatalities:
Total fatalities:
1
Captain / Total flying hours:
2658
Captain / Total hours on type:
657.00
Aircraft flight hours:
26436
Circumstances:
The pilot supervised the loading of the airplane. According to info from a person that helped load the plane, the bill of loading, and actual weights and measurements of the cargo after the accident, the plane was loaded to a gross weight of 11,979 lbs with the cg 2.7 inches behind the aft limit. At the destination, the flight was vectored for an ILS runway 10 approach. About 3 miles from the runway, the pilot was told to make a missed approach due to inadequate separation from traffic. The pilot acknowledged, but soon thereafter, radar contact with the plane was lost. Witnesses saw the plane descend from a low cloud layer before it crashed. One witness said its wings were moving from side to side and the plane was falling faster than it was moving forward. There was evidence the plane had impacted in a flat attitude with little forward movement. Four cargo straps were found loose with no sign of tensile overload; 3 others and a restraining board were found loose as if they had not been used. No preimpact mechanical problem was found. The wind was from 090° at 21 gusting 32 kts. The pilot, sole on board, was killed.
Probable cause:
Failure of the pilot to properly secure the cargo, which allowed a shift in the center of gravity during a missed approach maneuver and resulted in subsequent loss of aircraft control and flying speed. A factor related to the accident was failure of the pilot to assure the airplane was loaded within its proper weight and balance limitations.
Final Report: