POST OFFI CE BOX 90808 LAFAYETTE, LOUISIANA 70509 USA TELEPHONE: 337 235 2452 FACSIMILE: 337 272

- 4510 November 16, 2015 Also Filed Electronically U.S . Department of Transportation Docket Operations West Building Ground Floor, Room W12

- 140 1200 New Jersey

Avenue, SE Washington, DC 20590. To Whom It May

Concern; In accordan ce with CFR 14 11.15 and 11.81, PHI, In c . , requests an exemption from Part 91.9(a) which , in part, states: Except as provided in paragraph (d) of this section, no person may operate a civil aircraft without complying with the operating limitations specified in the approved Rotorcraft Flight Manual, markings, and placards, or as otherwise prescribed b y the certifying authorit y of the country of registry

. **Extent of Relief Sought and Reason for the Relief**  This petition requests an exemption from the following S

- 92A Rotorcraft Flight Manual limitation when operating between land

- based and offshore facilities or when operating between two offshore facilities. TYPES OF OPERATION Category ’A’ with a maximum of 19 passenger seats or Category ’B’ with 9 or less passenger seats; Day , Night, VFR and IFR. Specificall y, PHI, Inc
. requests approval to operate S

- 92A helicopters with limited exposure to engine failure during takeoff and landing while carrying up to 19 passengers. **This Exemption is in the Public I nterest**  The S

- 92A, and other 10+ seat rotorcraft certified to the latest standards (FAR 29 amendment 47) and equipped with state

- of

- the

- art safet y s ys tems and technology , routinel y transport workers to and from offshore platforms to support the oil and gas industry

. Specificall y, equipment such as HUMS, HTAWS, ADS

- B, TCAS/TAS, FMS, Fault Tolerant Design and other advanced avionics and electronics allow these rotorcraft t o offer the highest level of safet y available today . These aircraft replaced older designs which do not offer these advancements, and not required to meet the current performance requirements imposed on the S

- 92 and other similar aircraft. The intent of this exemption is to provide those workers with the safest transportation available, while maintaining an efficient transportation sy ste m for the oil and gas industry

. For these reasons, this exemption is in the general public interest.PHI , Inc.

Petition for Exemption to 14CFR 91.9 (a) November 16, 2015 **Equivalent Level of Safety** The S

- 92A has operated under Operations Specification H100 in the United States, and under JAR

OPS 3 in other countries, since 2003. Both rules allow for limited exposure to engine failure. The requested exemption will continue to provide the same level of safety that is currentl y in place for offshore operations. During the period noted above, no accide nts (S

- 92A or other aircraft in the same class) have been caused by power loss due to engine failure during takeoff or landing. If this exemption is granted, the S

- 92A w ill continue to operate Category A with the exception of a brief exposure to engine fa ilure during takeoff and landing. The amount of time the aircraft is exposed to engine failure will depend on man y conditions, but the maximum exposure would normall y be less than 9 seconds per takeoff/landing. If this exemption is not granted, the S

- 9 2A (and other like aircraft) would be forced to severel y decrease the number of passengers and/or fuel per sortie. Decreased passenger loads will require more sorties to meet demand and effectivel y increase exposure to hazards unrelated to engine failure. A discussion on the merits of limited exposure to engine failure during offshore operations, explaining how the overall level of safety may be enhanced by the requested exemption, is provided as Attachment A to this petition. **Operations O utside of the U**  **nited States:** Non
- U
. S ., S

- 92A operators outside of the United States do not require this exemption. JAR

- OPS 3, and other equivalent operational rules, already permit operations with limited exposure to engine failure. PHI , Inc., wishes to have this exemption apply to their operations outside the USA for the same reasons stated herein. **Mitigation F actors**  **:** In the unlikel y case of a ditching as a result of an engine failure during takeoff or landing, the following mitigation is provided:

 The S

- 92A is equipped with aircraft flotation gear and is certified f or ditching in up to sea state 6
.  When operating over water, each S

- 92A occupant is provided, and wears, personal flotation equipment.  The S

- 92A is equipped with life rafts that can be deployed from inside or outside the aircraft. To qualify

for JAR

- OPS 3 Performance Class 2 operations (limited exposure to engine failure), Sikorsky Aircraft periodically

submits engine reliability reports to show that the in

- flight shutdown rate is less than 1 per 100 ,000 flight hours. The most rec ent report, dated supports continued PC 2 operations.PHI , Inc.

Petition for Exemption to 14CFR 91.9 (a) November 16, 2015 PHI , In c . , will conduct operations in such a manner as to minimize the time spent exposed to engine failure. This will be accomplished by following the manufacturer’s recommended takeoff and landing procedures whenever feasible. Operations will not be conducted unless the current aircraft weight, altitude and temperature ensure a 150 feet per minute climb at 1,000 feet above the takeoff surface with one engine inoperat ive and the remaining engine at maximum continuous OEI power. PHI , Inc., further mitigates exposure by ;

 Conducting flight operations to and from helidecks and shore based heliports that meet or exceed size and weight requirements appropriate to the aircr aft configuration.  Training our crews in a Level D, FFS (Full Flight Simulator) initially and annually , insuring the highest levels of proficiency and competency

.  Conducting route checks to confirm that our crews remain procedurall y compliant and use CRM principles during all flight operations.  Using PHI's Flight Data Monitoring Program (known as LAMP) to insure flight profiles are in accordance with PC

- 2 procedures. **Summary** PHI , as the launch customer for the S

- 92, has accumulated o ver 150 ,000 hours of operational experience in this make/model all in accordance with H
- 100 and Performance Class 2 profiles

. This experience demonstrate s that when takeoff and landing techniques are used to minimize exposure to forced landing due to engine failure, that this aircraft can be operated at an equivalent level of safety to Category A (PC

- 1). Due to the remote nature of our operations, helideck size and off

- airport basing, the viability o f full Category Ao r Performance Class One (PC1) is impractical. I f this requirement were to be imposed, the S

- 92 (and its equivalent competitor aircraft) would become economically unfeasible which likely would result in their removal from service. T he outcome would be a reversion to smaller, older, less sophisticated a ircraft that do not provide the same level of safet y. T his would result in an overall degradation of safet y and not serve the most important stakeholder...the passenger. If there are an y questions concerning this petition, or to report the disposition of this request, please contact me as indicated below. Sincerel y, 

# Paul A. Perkins, Jr. Paul A. Perkins, Jr. Chief Pilot , PHI , Inc. P.O. Box 90808 Lafayette, LA 70509 337.272.4242 email: mhurst@phihelico.com AttachmentPHI , Inc.

Petition for Exemption to 14CFR 91.9 (a) November 16, 2015



### INTENTIONALLY BLANKPHI , Inc.

Petition for Exemption to 14CFR 91.9 (a) November 16, 2015

Attachment A Page | 1 of 7 

### At tachment	A
**The Case for Limited Exposure to Engine Failure** Sikorsky Aircraft uses a hazard identification/mitigation process that identifies the hazards involved in each area of operation and then uses different mitigation processes to drive the risk down to the lowest possible level. In the rare case where the m itigation process for one hazard adversel y raises the risk of a different hazard, the mitigation must be applied to the most likely accident scenario. The following discussion examines the offshore takeoff and landing maneuvers, identifies the historica l hazards associated with these maneuvers, and assigns appropriate mitigation processes to each hazard. **Offshore elevated helideck takeoff procedure.**

Figure 1 Published S

- 92A Elevated Helideck Takeoff ProcedurePHI , Inc.

Petition for Exemption to 14CFR 91.9 (a) November 16, 2015

Attachment A Page | 2 of 7 Figure 2. Ty pical Elevated Platform
The no - exposure takeoff from an offshore elevated helideck (Figure 1) is initiated by adding power to establish a vertical climb. The takeoff decision point (TDP) is defined as a height above the takeoff surface with a corresponding vertical ve locity at that height. For the S

- 92A, the TDP for an elevated helideck is 30 feet with a 1,000 fpm climb rate. If an engine should fail prior to the TDP, the takeoff is rejected and the aircraft lands back on the helideck. If an engine should fail at or after the TDP, the takeoff is continued and the aircraft flies away . When this procedure is flown at the appropriate weight for the given ambient conditions (pressure altitude, temperature and helideck height) the aircraft has no exposure to engine fail ure. - i.e. an engine can fail at an y point in the procedure and the aircraft can either safel y land back on the helideck or continue the takeoff and fly away on the remaining engine. There are two primary hazards associated with this maneuver. Takeoff h azard 1 : Contact with the platform structure with All Engines Operating (AEO). The takeoff procedure is very dy namic. The pilot is required to attain a fairly high climb rate in a short period of time while maintaining position directly over the heli deck. Visual cues for position maintenance are limited under the best of conditions and quickly degrade in poor weather or at night. As the aircraft climbs, there is a tendency to drift aft in an attempt to keep the edge of the helideck in sight. If th e pilot drifts backwards, the aircraft main or tail rotor may contact the offshore platform structure. Note the proximity of obstacles in Figure 2. Mitigation: Lo wer the TDP height and vertical velocity

.PHI , Inc.

Petition for Exemption to 14CFR 91.9 (a) November 16, 2015

Attachment A Page | 3 of 7 Decreasing the TDP height to 15 feet allows the pilot to keep the helideck edge in sight and decreases the time spent in close proximity to the rig structure. Decreasing the TDP vertical speed to 500 fpm makes the maneuver less abrupt and easier to fl y. Takeoff hazard 2 : Engine failure during take off. Large transport (19 passengers) helicopters do not have sufficient power to hover on one engine when at normal takeoff weights. If an engine should fail at, or immediatel y after TDP, the takeoff procedure described above takes advantage of vertical velocity energy and the energy

gained b y dropping down below the helideck to attain a safe One Engine Inoperative (OEI) speed (V TOSS ). If sufficient energy is not available at the critical point, the aircraft is exposed to hitting the deck edge or ditchin g in the water below the platform. Mitigation: In crease the TDP height and vertical velocity

. A higher TDP height and vertical velocity provides more energy for a subsequent fl y away maneuver if an engine should fail at or immediatel y after the TDP. In addition, i t should be noted that, as the helicopter weight decreases (lower fuel/payload), the exposure to engine failure decreases due to increased OEI power margins. It is clear that the mitigation factors for each of the two hazards are diametrically opposed, the AEO hazard being mitigated b y a lower TDP with a slower initial climb rate, and the OE I hazard being mitigated b y a higher TDP with a higher initial climb rate. The hazards associated with lowering the takeoff weight are discussed later in this paper.PHI , Inc.

Petition for Exemption to 14CFR 91.9 (a) November 16, 2015

Attachment A Page | 4 of 7 **Offshore elevated helideck landing procedure.**

Figure 3 Published S

- 92A Elevat ed Helideck Landing Procedure The landing procedure requires an offset approach with an aim point that is one to two rotor diameters to the side of the target helideck. The S

- 92A no

- exposure approach is flown at an indicated airspeed no slower than 40 kn ots with a descent rate no greater than 600 fpm. At 50 feet above the helideck, a flaring side step maneuver slows the aircraft to a hover while placing the aircraft over the landing spot. The Landing Decision Point (LDP) is 50 feet above the landing sur face with at least 40 knots airspeed and no more than 600 fpm descent rate. If an engine fails prior to the LDP, the pilot flies a go

- around maneuver, dropping below and to the side of the platform. If an engine fails at or beyond the TDP, the pilot perf orms an OEI landing on the helideck. The two primary hazards during a landing are very similar to those associated with an elevated helideck takeoff ; AEO contact with the platform and OEI deck edge strike or ditching. Landing hazard 1: Collision with the platform structure with all engines operating (AEO).PHI , Inc.

Petition for Exemption to 14CFR 91.9 (a) November 16, 2015

Attachment A Page | 5 of 7 I f zero exposure to engine failure is mandated, the pilot must fly the OEI profile every approach, just in case an engine fails at the most inopportune time. A single engine landing to a small platform (60

- 100 foot diameter circle) requires a very dy namic maneuver involving an aggressive pitch rate and high pitch attitude. Under the best of conditions, this ty

pe of maneuver, in close proximity to the obstructions associated with an offshore plat form, is challenging. When the degraded visual cues of a night mission, along with the turbulence associated with the rig structure, are considered, the chances for error are greatl y increased. This dynamic AEO landing procedure is the cause of many of fshore accidents. Mitigation: Reduced approach speed Reducing the approach speed results in a much lower pitch attitude during the flare and consequentl y a less aggressive maneuver. A 10 knot ground speed provides a safer, more controlled approach. Landing hazard 2: Engine failure during landing. As noted in the takeoff discussion, the aircraft under discussion do not have an OEI hover capability at the desired operating weight. The helicopter requires sufficient airspeed to minimize the power req

uired to avoid contact with the water if the engine should fail prior to the LDP. The kinetic energy associated with this airspeed is also required to carry the aircraft over the landing surface if the engine should fail at or just after the LDP. Mitigation: In crease d approach speed A 40 knot approach speed is required to ensure sufficient energy for a fl y - away

maneuver (engine fails prior to LDP) or successful landing (engine fails at or after LDP). Again, it should be noted that, as the helicopter w eight decreases (lower fuel/payload), the exposure to engine failure decreases due to increased OEI power margins. Again, the mitigation factors for the two primary landing hazards are opposite. A slow approach speed is required for an easily flown, controlled approach which will decrease the chances of AEO contact with the platform structure. However, a faster approach speed provides the energy required to perform a successful OEI fly away or landing. **Decreased gross weight**

. In both the takeoff and landing maneuvers, a lower aircraft gross weight will improve single engine performance and decrease the hazard of an OEI accident. However, decreasing the aircraft gross weight can only be accomplished b y decreasing the passenger or fuel load. Hazard of decreased passenger load: The total number of passengers exposed to an accident does not change. A decreased passenger load on each sortie will require additional sorties to be flown to service the offshore oil fields. With the current fleet of air craft operating in the Gulf of Mexico, if flight with no exposure to engine failure was mandated, the number of sortiesPHI , Inc.

Petition for Exemption to 14CFR 91.9 (a) November 16, 2015

Attachment A Page | 6 of 7 required would at least double. Each additional sortie increases the likelihood of AEO accidents caused b y Controlled Flight Into Terra in (CFIT), mid

- air collision, or mechanical failures. Hazard of decreased fuel load: Fuel starvation and increased take

- off and landing activity

. There are two concerns with a decreased fuel load. 1. The knowledgeable pilot will carry more than the minimum required fuel as insurance against the changing offshore environment. If required to minimize gross weight, there will be increased pressure to launch with the absolute minimum fuel required. Due to changing weather conditions, this will certainly lead to landings with fuel levels below the required minimums and the associated possibility of ditching due to fuel starvation. 2. For longer range missions, what would normally be a “non

- stop” flight will require an intermediate fuel stop going to and ret urning from the intended offshore destination. These additional (unnecessary) offshore takeoffs and landings also increase the likelihood of the AEO accidents noted above. **The Dilemma** : The mitigations for the All Engines Operating (AEO) hazards are dire ctly opposed to the mitigations for the One Engine Inoperative (OEI) hazards. In order to minimize the AEO hazards, it would be necessary to: 1. Fly slow controlled approaches (15 knot ground speed) 2. Utilize lower takeoff decision points (15 feet at 500 f pm climb rate) 3. Maximize passengers on each sortie to minimize the number of sorties 4. Carry additional fuel reserves to minimize additional offshore landings and takeoffs to refuel In order to minimize the OEI hazards, it would be necessary to: 1. Fly faster approach speeds (40 KIAS) 2. Utilize higher takeoff decision points (30 feet at 1,000 fpm climb rate) 3. Minimize weight b y off loading passengers and fuel. 4. Add offshore refueling stages to the mission The offshore oil industry

reviewed these hazard s to determine the safest route forward. They identified the hazard which, historically , has been the major contributor to accidents and then addressed that hazard. T he issue may be summarized as determining whether there are more accidents caused b y pil ot error with all engines operating or by the loss of power due to a single engine failure

. A review of the last ten years of worldwide helicopter offshore operations yields eight instances of pilot error; AEO accidents in which the aircraft struck some p ortion of the platform. TherePHI , Inc.

Petition for Exemption to 14CFR 91.9 (a) November 16, 2015

Attachment A Page | 7 of 7 were also at least four instances in which pilot error resulted in an inadvertent AEO ditching/crash into the water. During that same ten

- ye ar period, there were no accidents caused by the loss of power due to engine failure on multi engine aircraft. The best route forward is clear. The chances of an accident caused b y pilot error with AEO is much greater than the likelihood of an OEI accident. Procedures that minimize the opportunity for pilot error and permit limited exp osure to engine failure provid e the highest level of safet y. Procedures, such as Performance Class II (PC

- 2) have been proven worldwide to offer an equivalent level of safety as compared to Category A or PC

- 1 profiles. **Recommendation.** The FAA should approve this request for exemption from Part 91.9(a) to permit limited exposure to engine failure when operating in the offshore environment or in other areas where exposure can be minimized using accepted takeoff and landing profiles

.