#### Tag: aw139

We all know it is the pilot’s responsibility to insure the helicopter is flown in accordance to limitations, which in part requires knowing the helicopters takeoff weight. However, due to the versatile nature of helicopters it isn’t always as simple as back in flight school. We may find ourselves picking up a sling load such as a log. How does one weigh a log? A dozen passengers off a ship. Ever try to use a scale on a heaving ship? Or out in the bush of Alaska picking up crew and equipment.,What scale?  One aspect that goes along with flying the ultimate off-road vehicle is that we may find ourselves in places without scales.

An AW139 lifts a daisy chain sling load on the North Slope of Alaska. This helicopter has a load cell and so the pilots were able to monitor and verify the weight of the cargo.

Most helicopters are not flying sling loads nor have a load cell installed, so we need another method of weight verification. Fortunately some performance charts can be used for this purpose. Performance charts are predictive, enabling a pilot to accurately determine variables prior to takeoff and many can be used in a variety of ways depending on which variables are known. The Sikorsky S-92 flight manual makes this an easy process, with the Indicated Torque Required to Hover in Ground Effect chart. One can predict what the indicated torque per engine will be for a specific weight, density altitude and wind condition. In this example, a negative 3,000-foot density altitude with a 10-knot headwind would equal 66 percent per engine torque for a gross weight of 23,000 pounds. For the same density altitude and wind condition, 83 percent per engine torque would indicate the maximum gross weight of 27,700 pounds is being exceeded. Using the chart it’s easy to see that that 1,000 pounds is equivalent to about 3.5 percent per engine torque, for a given density altitude and wind condition.

Using the Indicated Torque Required to Hover in Ground Effect, one can obtain the predicted torque for the S92 at a specific aircraft weight, density altitude and wind condition.

If the aircraft lacks this type of chart, a little m,ore work is necessary. The takeoff and maximum continuous power Hover in Ground Effect charts also provide maximum weights for a range of density altitudes. This gives a start for making your own quick reference chart, and after a couple dozen flights you can add more data points with other power settings. Say you flew 500 lbs under gross weight with a 1000-foot density altitude; simply note the torque in a stable in ground effect hover and enter the torque, density altitude, and weight on your quick reference chart. Over time, you will have created a chart to use as an aid when you are unsure of the aircraft takeoff weight. An external load pilot, without a load cell may opt to use a HOGE (hover out of ground effect) chart instead of a HIGE chart. Experienced pilots with a lot of time-in-type already have a pretty good idea of the power required for specific weights and density altitudes, which is essentially what this quick reference chart provides.

The pilot should also note the cyclic position necessary to maintain a stable position over the ground, providing an indication of the aircraft’s center of gravity. An excessive lateral or longitudinal deviation from a normal position can indicate a CG out of normal range. Wind can also effect the cyclic position, but experience in type will help you learn what a normal cyclic flight control position should be in a variety of conditions. For example, a farther forward and left cyclic position than normal would indicate an aft and right CG, which a left quartering headwind could also cause.

These methods are certainly not a substitute for a proper weight and balance calculation using accurate weights. They are a means of verifying your calculations, particularly when in situations where the weights provided may be in question. It is also a means of understanding the performance of your helicopter better.

Flying helicopters IFR with a sling load presents unique challenges, requiring specific skills of the pilot.  One must obviously be able to control the helicopter without any outside visual references. Less obvious, one must also be able to correctly interpret the instruments, which reflect both the behavior of the load and the orientation of the helicopter. A Class B external load (sling load) is one that is free of the earth’s surface and is attached to the helicopter by a synthetic or wire line. The pilot is “flying” both the helicopter and the load, which at times can seem to have a mind of its own.

Today slinging IFR is not a common practice, though there was a time on the North Slope of Alaska where it was employed regularly. I thought it might be interesting to look at this operation in some detail.

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Normally one can see the external load, and make the necessary corrections. Lateral swinging is more common than a fore-aft motion or a circular motion, so we will focus on that. A quick lateral cyclic input towards the load, just as it reaches its apex, moves the aircraft over the load neutralizing its motion. You are essentially moving the aircraft over the load after it has swung out to the side. This dampens the movement of the load and stabilizes it. However, when flying IFR the instruments must be used to indicate the loads’ position and movement. The best way to learn how the instruments reflect the movements of the load is during VFR flight, when the load and gauges can be seen together.

Flying IFR with a sling it is important not to make corrections reflecting the gauges as one normally would, but instead understand exactly what the load is doing beneath you. The attitude indicator reflects rhythmic changes in bank angle from the load tugging the helicopter laterally side to side, as does the ball in the inclinometer. The inclinometer is used to indicate when and how much lateral cyclic input is necessary for a correction, though there is a natural lag. The load will reach its apex prior to the inclinometer, and the pilot must compensate for this natural lag. When the ball starts to swing out of center to the right and is about half way from its apex, the load is almost at its apex to the left, the pilot then uses left lateral cyclic as a correction. The rhythmic oscillations in the attitude indicator and inclinometer reflect the movements of the load, and the average of these movements are the actual orientation of the aircraft.  The pilot learns to mentally average these oscillations in order to control the pitch, roll, and yaw of the aircraft itself.

“An ounce of prevention is worth a pound of cure”, so one learns to make flight control inputs very smoothly so as to not aggravate the load. Turns are initiated slowly, and half standard rate turns are sometimes prudent.

Determining cruise airspeed

Another consideration is determining the target airspeed at which to fly.  This must be greater than Vmini (minimum IFR speed) and less than the loads effective Vne. While the aircraft will have an external load airspeed limitation, this may not be possible if the load is unstable at a lower speed. Many loads cannot be flown at the external load Vne, and the effective Vne must be determined. As the pilot slowly accelerates during takeoff, the load is carefully watched prior to IMC to determine what airspeed above Vmini the load can be flown at. Once that airspeed is determined, it is maintained for the entire flight.

Should the load show signs of instability below Vmini or only slightly above so as to not provide a safe and adequate airspeed window, the takeoff is aborted while still VMC.

One should be sure of a load’s stability and capability at a safe airspeed prior to IMC, and one should only fly known loads in IFR or at night. A known load is one that is similar to one previously flown during the day. The load characteristics are predictable and stable.

Autopilots and external loads don’t usually mix, and many Rotorcraft Flight Manuals prohibit autopilot coupling during external load operations. The autopilot can be too abrupt in pitch attitude and roll, particularly when initiating and terminating turns. A pilot can make changes with a more gentle touch; such as slowly entering a half-standard rate turn when necessary. The autopilot can be used for stability augmentation; it just shouldn’t be coupled to the flight director directly controlling the aircraft.

Horizontal and vertical situational awareness

Class B sling loads can be jettisoned, either intentionally or unintentionally. The hook release is typically electric and controlled by the pilot. Under normal operation the load is released once it has been placed gently on the ground; however, in the case of an emergency the pilot may opt to release it in flight. Due to the possibility of the load being released in flight, persons or property are never overflown. This requires horizontal situational awareness; easy enough VFR, but IFR is another matter. Fortunately, the North Slope of Alaska provides assurance due to its desolate nature.

Vertical situational awareness must also be considered, not just for the helicopter but also for the load hanging underneath. With the typical 25 to 50’ line, the altitude of the load isn’t a factor in cruise flight; however, during the instrument approach it must be considered.

The Instrument Approach

As much fun controlling the helicopter and load may be in IFR conditions, eventually we do need to land. For that we need to fly an instrument approach. Let’s stick with the North Slope of Alaska, using the Deadhorse (PASC) ILS 05 as an example, using a little simple math.

A load 5 feet high hanging on a 50 foot line would require a 55 foot adjustment factor to the decision altitude. For the Deadhorse ILS, this means increasing the decision altitude of 267 feet to 322 feet, and ALS conditional altitude of 167 feet to 222 feet. It would also be prudent to include this 55 foot altitude adjustment into your preflight IFR planning.

Final Thoughts

While flying slings IFR is no longer common, the training for IFR slings still occurs. Having the skill and confidence to be able to fly a sling IFR is vital should unforecasted adverse weather be encountered, not unheard of on the Alaskan North Slope where the weather can change quickly. Airports and options are few and far between north of the Brooks Range of Alaska. These skills also translate well and are employed for night sling operations, which are still done on a regular basis.

The last two blogs provided great explanations of the height-velocity diagram as it pertains to single engine helicopters. So, let’s now take it a little further into the multiengine helicopter realm.

Just as with singles, you will typically find a H-V diagram for multiengine helicopters in the flight manual. However, unlike the singles, the H-V diagram for the multi is to insure a safe landing OEI (one engine inoperative), and not from an autorotation. Furthermore, whether or not the H-V diagram even applies is dependent on how well the aircraft can perform OEI. This performance is defined in a series of categories. If the multi is full-time Category B (as are all singles), or a part-time Cat B, then a H-V diagram limitation will apply; whereas, if Category A it will not. Basically, Cat A is where OEI performance is so good that the H-V is not applicable. Comparing three very different multiengine helicopters to highlights these differences.

The BO105CBS is full-time Cat B, with marginal OEI performance. Even in ideal conditions (light weight and low density altitude), it can barely hold altitude on one engine. Varying airspeed from Vy just a couple knots results in a descent. Approach and departure profiles AEO (all engines operating) need to be such that a quick transition can be made in accordance with the H-V diagram, in the event of an engine failure.

The Bell 412 is an example of a multi that can be operated Cat A or Cat B, depending on the weight, altitude, and temperature. At lower weights, altitudes, and temperatures it will have good enough OEI performance to qualify as a Cat A aircraft. However, in most day-to-day operations it is typically a Cat B aircraft, which means the H-V diagram would apply.

Bell 412 H-V diagram

The AgustaWestland 139 is a true Cat A aircraft, although as with many other Cat A aircraft it is possible to find conditions that will push it into Cat B. The AW139 was largely designed to operate Cat A, in an offshore petroleum support environment with a high useful load (passengers, cargo, and fuel). It is capable of landing and taking off from helipads, while carrying up to 15 passengers, with Cat A performance.

AW139 H-V diagram

So, what is Cat A?  Cat A is where the aircraft has adequate performance capability for continued safe flight in the event of an engine failure, no matter when that failure occurs. While single engine and Cat B multiengine helicopters have no such assurances, the Cat A aircraft is able to ensure that a safe and normal landing can be made OEI at an airport or heliport.

In the event of an engine failure, different types or categories of helicopters dictate different courses of action in order to do the same thing: preserve rotor RPM. No matter the helicopter and its’ number of engines, Nr is the wing and it must be maintained. The single must obviously enter an autorotation. The Cat B multi must fly at or above Vy (best rate of climb OEI) in order to maintain or increase altitude, and then fly to an area where a safe landing can be made. During takeoff and landing while close to the ground and below Vy, an engine failure in a Cat B will likely result in a forced landing. Though not as dire as an autorotation, it is more of an event than the Cat A helicopter. The difference with the Cat A is that engine failure doesn’t dictate a forced landing. In the event of an engine failure during takeoff, a Cat A has the ability to either return to and safely stop at the takeoff area or to continue takeoff, climb and establish forward flight. In the event of an engine failure during landing, the Cat A can either land at the intended landing area or abort the approach and reestablish forward flight. Unlike Cat B, there is no exposure to the possibility of a forced landing, hence no H-V diagram.

(These views and opinions are my own and do not necessarily reflect the views of Era.)