Special Conditions: Erickson Air-Crane Incorporated S-64E and S-64F Rotorcraft, 50688-50694 [2010-19921]

Agencies

• Federal Aviation Administration
• DEPARTMENT OF TRANSPORTATION

[Federal Register Volume 75, Number 158 (Tuesday, August 17, 2010)]
[Rules and Regulations]
[Pages 50688-50694]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-19921]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Parts 21 and 29

[Docket No. SW014; Special Conditions No. 29-014-SC]


Special Conditions: Erickson Air-Crane Incorporated S-64E and S-
64F Rotorcraft

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final special conditions.

-----------------------------------------------------------------------

SUMMARY: These special conditions are issued for the Erickson Air-Crane 
Incorporated (Erickson Air-Crane) model S-64E and S-64F rotorcraft. 
These rotorcraft have novel or unusual design features associated with 
being transport category rotorcraft designed only for use in heavy 
external-load operations. At the time of original type certification, a 
special condition was issued for each model helicopter because the 
applicable airworthiness regulations did not contain adequate or 
appropriate safety standards for turbine-engine rotorcraft or for 
rotorcraft with a maximum gross weight over 20,000 pounds that were 
designed solely to perform external load-operations. At the request of 
Erickson Air-Crane, the current type certificate (TC) holder for these 
helicopter models, the following will resolve reported difficulty in 
applying the existing special conditions and eliminate any confusion 
that has occurred in Erickson's dealings with a foreign authority. 
Specifically, we are consolidating the separate special conditions for 
each model helicopter into one special condition to clarify and more 
specifically reference certain special condition requirements to the 
regulatory requirements, to add an inadvertently omitted fire 
protection requirement, to recognize that occupants may be permitted in 
the two observer seats and the rear-facing operator seat during other 
than external-load operations, and to clarify the requirements relating 
to operations within 5 minutes of a suitable landing area. The 
applicable airworthiness regulations do not contain adequate or 
appropriate safety standards for this design feature. These special 
conditions contain the additional safety standards that the 
Administrator considers necessary to establish a level of safety 
equivalent to that established by the existing airworthiness standards.

DATES: Effective Date: September 16, 2010.

FOR FURTHER INFORMATION CONTACT: Stephen Barbini, FAA, Rotorcraft 
Directorate, Regulations and Policy Group (ASW-111), Fort Worth, Texas 
76193-0110, telephone (817) 222-5196, facsimile (817) 222-5961.

SUPPLEMENTARY INFORMATION:

Background

    On November 27, 1967, Sikorsky Aircraft Corporation (Sikorsky) 
filed an application for type certification for its Model S-64E 
helicopter. This rotorcraft is the civil version of the United States 
Army Model CH-54A flying crane. The S-64E has a maximum weight of 
approximately 30,000 pounds when flying only with internal fuel 
loadings and personnel, and without external loads. It has a maximum 
weight of 42,000 pounds, of which a maximum of 20,000 pounds may be 
external loads. Type certificate H6EA that included special condition 
No. 29-6-EA-2 was issued on August 21, 1969. This special condition 
includes conditions for type certification for carrying Class B 
external loads.
    On April 2, 1969, Sikorsky filed for an amendment to its type 
certificate to add the Model S-64F. This aircraft is the civil version 
of the United States Army Model CH-54B flying crane. The S-64F has a 
maximum weight of approximately 30,000 pounds when flying only with 
internal fuel loadings and personnel, and without external loads. It 
has a maximum weight of 47,000 pounds, of which a maximum of 25,000 
pounds may be external loads. Type certificate H6EA was amended on 
November 25, 1970, to add the F model, including special condition No. 
29-16-EA-5 and Amendment No. 1 to that special condition. This Model S-
64F special condition includes requirements for type certification for 
carrying Class A and B external loads.
    The 14 CFR part 29 regulations applicable at the time of 
certification required the models S-64E and S-64F to comply with 
Category A regulations.

[[Page 50689]]

However, strict adherence to those regulations was deemed inappropriate 
for these model aircraft and their intended operations. The special 
conditions created for the Model S-64E and Model S-64F combined the 
appropriate standards from both Category A and B, plus added safety and 
other requirements necessary to establish compliance with the 
airworthiness requirements of subpart D of 14 CFR part 133 for Class A 
and B rotorcraft load combinations. Additionally, the special 
conditions allowed operations under 14 CFR part 91. The combination of 
regulations and special conditions was established at a level of safety 
equivalent to 14 CFR part 29 requirements at the time of certification.
    Both aircraft were specifically type certificated as ``industrial 
flying cranes,'' which are used only to carry cargo and all cargo is 
carried as an external load. The cockpit contains only five seats, 
allowing for two pilots, an aft-facing hoist operator and two 
observers. The rotorcraft does not have a passenger compartment and is 
not designed to transport passengers. 14 CFR part 91 operations are 
allowed. The aircraft are powered by two Pratt and Whitney turbo shaft 
engines (Series JFTD12A); the S-64E uses the model 4A which generates 
4,500 horsepower and the S-64F uses the model 5A which generates 4,800 
horsepower. The engines drive a six-blade single main rotor 
approximately 72 feet in diameter and a four-blade tail rotor 
approximately 16 feet in diameter.
    Since the time of original certification, 14 CFR part 29 has been 
modified to recognize that most transport category rotorcraft are being 
used in utility work, rather than in air carrier operations. The 
regulatory changes now enable a rotorcraft of more than 20,000 pounds 
and nine or less passenger seats to be certificated as Category B 
provided certain Category A subparts are met.
    Since the S-64's certification, the regulations have been amended 
to better accommodate rotorcraft designed to operate under the external 
load provisions of 14 CFR part 133; however, no transport category 
rotorcraft (over 20,000 pounds) has been designed with the unique and 
novel features of the ``skycrane.'' In 1992, the type certificate for 
the Model S-64E and Model S-64F was transferred from Sikorsky to 
Erickson Air-Crane Incorporated. In 2004, the Model S-64F received a 
type certificate from the European Aviation Safety Agency (EASA). In 
2005, the Model S-64E was certificated to carry Class A external loads 
under 14 CFR part 133.

Type Certification Basis

    The original type certification basis is as follows:
    For the Model S-64E: 14 CFR part 29, 1 February 1965, including 
Amendments 29-1 and 29-2 except 14 CFR 29.855(d), and Special Condition 
No. 29-6-EA-2.
    For the Model S-64F: 14 CFR part 29, dated 1 February 1965 
including Amendments 29-1 and 29-2 except 14 CFR 29.855(d), and Special 
Condition No. 29-16-EA-5 including Amendment No. 1.
    We have found that the applicable airworthiness regulations for 14 
CFR part 29 do not contain adequate or appropriate safety standards for 
the Erickson S-64E and S-64F rotorcraft because of novel or unusual 
design features. Therefore, special conditions were prescribed under 
the provisions of Sec.  21.16. Special conditions, as appropriate, are 
defined in Sec.  11.19 and issued per Sec.  11.38, and become part of 
the type certification basis under Sec.  21.17(a)(2).
    Special conditions are initially applicable to the model for which 
they are issued. Should the type certificate for that model be amended 
later to include any other model that incorporates the same novel or 
unusual design feature, or should any other model already included on 
the same type certificate be modified to incorporate the same novel or 
unusual design feature, the special conditions would also apply to the 
other model per Sec.  21.101(a)(1).

Novel or Unusual Design Features

    The Erickson Air-Crane S-64 rotorcraft incorporates the following 
novel or unusual design features:
    The aircraft was designed specifically as an industrial flying 
crane--
    (a) With an airframe--
    (1) Designed solely for external load capabilities with no 
passenger cabin and accommodations in the cockpit only for--
    (i) One pilot,
    (ii) One copilot,
    (iii) One aft-stick operator, and
    (iv) Two observers.
    (2) Designed with two small baggage compartments in the nose.
    (3) Designed with multiple ``hard points,'' each with load ratings 
specifically for the carriage of external loads.
    (b) With a rear-facing aft-stick operator seat, which allows for--
    (1) Precision placement of external loads, and
    (2) Limited flight operations capabilities.
    (c) With neither engine equipped with a cowling.
    (d) That weighs over 20,000 pounds, but is designed solely to carry 
cargo in external load operations.

Discussion

    The type certification basis for the Model S-64E helicopter 
contained Special Condition No. 29-6-EA-2, dated January 13, 1969. The 
type certification basis for the model S-64F helicopter contained 
Special Condition No. 29-16-EA-5, issued December 3, 1969 and Amendment 
1 to that Special Condition issued November 13, 1970. The special 
condition for the model S-64E included requirements for type 
certification without external loads (including flight conditions, 
propulsion conditions, systems condition, and operating limitations 
conditions) and requirements for type certification with external loads 
(including general conditions, flight conditions, propulsion 
conditions, systems condition, and operating conditions). The special 
condition, including Amendment 1 for the model S-64F, included 
essentially the same requirements as those for the model S-64E, but 
included additional requirements for Class A load combinations.
    We have reviewed Special Conditions No. 29-6-EA-2 and No. 29-16-EA-
5, including Amendment No. 1. We have determined that the original 
special conditions applied to the model S-64 ensure a level of safety 
equivalent to 14 CFR part 29 requirements at the time of certification 
for both the E and F model rotorcraft.
    At the request of Erickson Air Crane, we are:
    (a) Consolidating the special conditions for both model helicopters 
into one document.
    (b) Indicating whether a special condition requirement is ``in lieu 
of'' or ``in addition to'' a standard certification requirement and 
making specific reference to the certification requirement. The 
original Special Conditions did not delineate the novel or unusual 
design features of the Air-Crane, which resulted in an unclear 
application of the ``in addition to'' and ``in lieu of'' requirements 
as they pertained to the rules existing at the time of certification.
    (c) Referencing 14 CFR part 133 instead of the various rotorcraft 
load combination classes for the special condition requirements 
concerning placards.
    (d) Modifying the occupancy special condition to allow passengers 
to be

[[Page 50690]]

transported, as otherwise permitted by the regulations. Operations are 
currently limited to occupants that are flight crewmembers, flight 
crewmember trainees, or other persons performing essential functions 
connected with external load operations or necessary for an activity 
directly associated with external load operations.
    (e) Removing the special condition operating limitation that 
required the helicopters be operated so that a suitable landing area 
could be reached in no more than 5 minutes, and now requiring that only 
when flying over a congested area must the helicopter be operated so 
that a suitable landing area can be reached in no more than 5 minutes.
    (f) Adding a requirement to comply with Sec.  29.855(d), at 
Amendment level 29-3, effective February 25, 1968, which was excluded 
from the original special condition as indicated on the type 
certificate data sheet, requiring the baggage compartment in the 
airframe nose be sealed to contain cargo or baggage compartment fires.
    Neither consolidating the requirements, specifying the ``in lieu 
of'' or ``in addition to'' references, nor referencing 14 CFR part 133 
are intended to make any substantive changes from the requirements 
contained in Special Condition No. 29-6-EA-2 nor Special Condition 29-
16-EA-5, as amended. However, we are modifying the ``occupant'' 
standard.
    The original special conditions only permitted flight crewmembers, 
flight crewmember trainees, or persons performing an essential or 
necessary function in connection with the external load operation to be 
carried on board the helicopter. This occupancy standard was taken 
directly from 14 CFR 133.35, dealing with the carriage of persons 
during rotorcraft external-load operations. At the time of original 
certification, there was no intent to allow the carriage of persons 
other than crewmember trainees and those required in connection with 
the external-load operation. Flights conducted under 14 CFR part 91 
regulations were only expected to occur when the helicopter was being 
re-positioned with two pilot crewmembers. In addition, limitations were 
placed on the S-64E and S-64F helicopter designs because they were not 
the typical transport category helicopter because they did not meet all 
appropriate 14 CFR part 29 transport category helicopter requirements. 
In particular, the designs do not include a power-plant fire 
extinguishing system and the related cowlings that assist in engine 
fire suppression.
    Since original certification, operators have stated that they would 
like the option to use the additional three seats, which includes the 
one rear-facing seat occupied by a crewmember during external-load 
operations, to carry support crews between operational bases and the 
worksites. The intended effect of removing the essential crewmember and 
crewmember trainee limitation recognizes that these model helicopters 
are not operated exclusively under 14 CFR part 133. Under this special 
condition, we recognize that the two observer seats and the rear-facing 
aft-stick operator's seat may be occupied by persons other than persons 
performing an essential or necessary function in connection with the 
external load operation during 14 CFR part 91 operations. The intent of 
this provision is to allow the two observer seats and the rear-facing 
operator's seat, when the rear-facing aft-stick operator's controls are 
disengaged and the collective guard is installed to prevent 
unintentional movement, to be occupied during other than external-load 
operations. As described in the FAA approved flight manual, the aft-
stick operator's controls are only to be engaged when a qualified 
crewmember is at the main and aft-stick operator's controls.
    From an engine-fire safety standpoint, single-engine helicopters 
certificated to Category B requirements of 14 CFR part 29 are permitted 
to carry up to nine passengers. However, if an engine fails due to a 
fire, although the fire may be extinguished, the helicopter will still 
be forced to execute an auto-rotation. Depending on where the 
helicopter is operating, a safe autorotative landing may not be 
possible. In addition, helicopters certificated to 14 CFR part 27 
requirements are not required to have a power-plant fire protection 
system, but are certificated to carry up to nine passengers. If a twin-
engine model S-64E or S-64F helicopter has an engine failure due to an 
engine fire, these helicopters can still fly on a single engine and the 
certification standards require that they must be safely controlled so 
that the essential structure, controls, and parts can perform their 
essential functions for at least five minutes in order to reach a 
possible suitable landing area.
    Although we are removing the ``occupant'' limitation, when 
conducting other than external-load operations, which most commonly we 
anticipate may be 14 CFR part 91 operations, operators will still be 
required to comply with the other FAA operating requirements applicable 
to their particular operation.\1\
---------------------------------------------------------------------------

    \1\ Some operational regulations that may apply during 14 CFR 
part 91 operations include, 14 CFR 61.113(a) which, with some 
exceptions, prohibits a private pilot from acting as pilot in 
command of an aircraft carrying passengers for compensation or hire, 
and from acting as pilot in command for compensation or hire. An 
exception to 14 CFR 61.113(a), 14 CFR 61.113(b) allows a private 
pilot to act as pilot in command of an aircraft for compensation or 
hire in connection with any business or employment if the flight is 
only incidental to that business or employment and the aircraft does 
not carry passengers or property for compensation or hire. Another 
regulation, 14 CFR 119.33 prohibits a person from providing or 
offering to provide air transportation when that person has control 
over the operational functions performed in providing that 
transportation unless that person has an air carrier certificate and 
operations specifications. Under our regulations, ``compensation'' 
has been interpreted very broadly and ``need not be direct nor in 
the form of money. Goodwill is a form of prohibited compensation.'' 
Administrator v. Murray, EA-5061, October 29, 2003 citing 
Administrator v. Blackburn, 4 NTSB 409 (1982).
    Intangible benefits, such as the expectation of future economic 
benefit or business, are sufficient to ``render a flight one for 
``compensation or hire''.'' See, e.g., Administrator v. Platt, NTSB 
Order No. EA-4012 (1993) at 6; Administrator v. Blackburn, 4 NTSB 
409 (1982), aff'd., Blackburn v. NTSB, NTSB, 709 F.2d 1514 (9th Cir. 
1983); Administrator v. Pingel, NTSB Order No. EA-3265, at n.4 
(1991); Administrator v. Mims, NTSB Order No. EA-3284 (1991).
---------------------------------------------------------------------------

    Another current special condition operating limitation requires 
that the helicopters be operated at an altitude and over routes which 
provide suitable landing areas that can be reached in no more than 5 
minutes. We are qualifying this limitation and only require this 
limitation when the helicopters are operated over a congested area. The 
5-minute portion of the limitation complements the fire protection 
requirements in Sec.  29.861, which for Category B rotorcraft requires 
that certain structure, controls, and other essential parts be able to 
perform their essential functions for at least 5 minutes under 
foreseeable powerplant fire conditions. Relaxing the limitation by 
allowing flights over other than congested areas that may not be within 
the 5-minute distance still exceeds the safety standard in the current 
Sec.  133.33(d) provision, which allows the holder of a Rotorcraft 
External-Load Operator Certificate to conduct rotorcraft external-load 
operations under certain circumstances over congested areas 
notwithstanding the requirements of 14 CFR part 91. Therefore, this is 
consistent with that standard.
    We are also changing the current type certification basis of both 
model helicopters that excludes the requirement to comply with Sec.  
29.855(d). At the time of the application for type certification of the 
model S-64E

[[Page 50691]]

helicopter on November 27, 1967, and before the changes to 14 CFR part 
29 by Amendment level 29-3, effective February 25, 1968, Sec.  
29.855(d) required that cargo and baggage compartments be designed or 
have a device to ensure detection of fires by a crewmember at his 
station to prevent entry of harmful substances into the crew or 
passenger compartment. In Notice 65-42 in Proposal 22 published on 
December 28, 1965 (30 FR 16129, 16139), we proposed to change Sec.  
29.855(d) because experience had shown that the design requirements for 
cargo and baggage compartments were not specific enough for 
compartments that are not sealed against fire and for cargo-only 
compartments. Because of the novel design of this helicopter, it did 
not have a typical transport category rotorcraft cargo or baggage 
compartment, only two small baggage compartments in the nose of the 
rotorcraft that are inaccessible during flight. Since the model S-64E 
helicopter was not the type of transport category rotorcraft envisioned 
when the transport category requirements of 14 CFR part 29 were adopted 
to address rotorcraft use in air carrier service and the necessary 
higher degree of safety to protect common carriage passengers and the 
fact that the model S-64E did have a sealed cargo compartment meeting 
the new proposed standard in Notice 65-42, the type certification basis 
for the model S-64E helicopter excluded the requirements of Sec.  
29.855(d). The model S-64E would later be shown to be in compliance 
with Sec.  29.855(d) at Amendment 29-3 because that amendment would not 
require a fire detection device for cargo and baggage compartments 
provided they are sealed to contain fires. The type certification basis 
for the model S-64F is the same as that for the model S-64E. Therefore, 
we are adding back to the type certification basis for both model 
helicopters the requirement to comply with Sec.  29.855(d), at 
Amendment level 29-3, effective February 25, 1968.

Discussion of Comments

    Notice of proposed special conditions No. 29-014-SC for the 
Erickson Air-Crane Incorporated S-64E and S-64F rotorcraft was 
published in the Federal Register on December 29, 2009 (74 FR 68731). 
No comments were received, and the special conditions are adopted as 
proposed.

Applicability

    This special condition is applicable to the Erickson Air-Crane 
Model S-64E and Model S-64F rotorcraft. Should Erickson Air-Crane apply 
later for a change to the type certificate to include another model 
incorporating the same novel or unusual design features, this special 
condition would apply to that model according to the provisions of 
Sec.  21.101(a)(1).

Conclusion

    This action affects only certain novel or unusual design features 
on the model S-64E and S-64F helicopters. It is not a rule of general 
applicability and it affects only the applicant who applied to the FAA 
for approval of these features on the helicopter.

List of Subjects in 14 CFR Parts 21 and 29

    Aircraft, Aviation safety, Reporting and recordkeeping 
requirements.

    The authority citation for these special conditions is as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701-44702, 44704.

The Special Conditions

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Special Condition No. 29-6-EA-2, Docket No. 9351, 
issued January 13, 1969 for the Model S-64E and Special Condition No. 
29-16-EA-5, Docket No. 10002, issued December 3, 1969 and Amendment 1 
to Special Condition No. 29-16-EA-5, issued November 13, 1970 for the 
Model S-64F, are removed and the following special condition is added 
as part of the type certification basis for Erickson Air-Crane models 
S-64E and S-64F helicopters. Unless otherwise noted, all regulatory 
references made within this special condition pertain to those 14 CFR 
part 29 regulations in effect at Amendment level 29-2, effective June 
4, 1967 (32 FR 6908, May 5, 1967).
    (a) Takeoff and Landing Distance. Because of the S-64's novel 
design as an industrial flying crane, the following apply:
    (1) For operations without external load, the takeoff and landing 
distance must be determined by flight tests over the ranges of weight, 
altitude, and temperature for which takeoff and landing data are 
scheduled. The flight tests must encompass the critical areas of a 
takeoff and landing flight path from a 50-foot hover. If the takeoff 
and landing distance throughout the operational range to be approved 
are zero, the minimum takeoff and landing area length must be one and 
one-half times the maximum helicopter overall length (main rotor 
forward tip path to tail rotor aft tip path) and the area width must be 
one and one-half times main rotor tip path diameter. Additionally, this 
information must be furnished in the performance information section of 
the Rotorcraft Flight Manual.
    (2) For Class A rotorcraft load combination operations:
    (i) Compliance must be shown with the provisions of Sec.  29.51 
(Takeoff data: General), except that in paragraph (a) of Sec.  29.51, 
the references to Sec. Sec.  29.53(b) (Critical decision point) and 
29.59 (Takeoff path: Category A) are not applicable.
    (ii) In lieu of the requirements of Sec. Sec.  29.53 and 29.59, the 
following apply:
    (A) Compliance must be shown with the provisions of Sec.  29.63 
(Takeoff: Category B),
    (B) The horizontal takeoff distance to a point 50 feet above the 
plane of the takeoff surface must be established with both engines 
operating within their approved limits, and
    (C) The takeoff climbout speed must be established.
    (iii) Compliance must be shown with the provisions of Sec.  29.79 
(Limiting height-speed envelope).
    (3) For Class B rotorcraft load combination operations:
    (i) Compliance must be shown with Sec.  29.51 (Takeoff data: 
General), except that in paragraph (a), the references to Sec. Sec.  
29.53(b) (Critical decision point), 29.59 (Takeoff path: Category A) 
and 29.67(a)(1) and (2) (Climb: One engine inoperative) are not 
applicable.
    (ii) In lieu of the requirements of Sec. Sec.  29.53 and 29.59, 
compliance must be shown with the provisions of Sec.  29.63 (Takeoff: 
Category B).
    (b) Climb. Because of the S-64's novel design as an industrial 
flying crane, the following apply:
    (1) For Class A rotorcraft load combination operations, in lieu of 
the requirements of Sec. Sec.  29.67 (Climb: One engine inoperative) 
and 29.71 (Helicopter angle of glide: Category B), compliance must be 
shown with Sec. Sec.  29.65(a) (Category B climb: All engines 
operating) and 29.67(a)(1) and (2) (Climb: One engine inoperative).
    (2) For Class B rotorcraft load combination operations, in lieu of 
the requirements of Sec. Sec.  29.67 (Climb: One engine inoperative) 
and 29.71 (Helicopter angle of glide: Category B), compliance must be 
shown with Sec.  29.65 (Category B climb: All engines operating).
    (c) Landing. Because of the S-64's novel design as an industrial 
flying crane, for Class A rotorcraft load combination operations, in 
lieu of the requirements of Sec. Sec.  29.77 (Balk landing: Category A) 
and 29.75 (Landing), compliance must be shown for 29.75(b)(5), and the 
following apply:
    (1) The horizontal distance required to land and come to a complete 
stop,

[[Page 50692]]

from a point 50 feet above the landing surface must be determined with 
a level, smooth, dry, hard surface.
    (2) The approach and landing may not require exceptional piloting 
skill or exceptionally favorable conditions.
    (3) The landing must be made without excessive vertical 
acceleration or tendency to bounce, nose over, or ground loop.
    (4) The landing data must be determined at each weight, altitude, 
and temperature for which certification is sought with one engine 
inoperative and the remaining engine operating within approved 
operating limitations.
    (5) The approach and landing speeds must be selected by the 
applicant and must be appropriate to the type rotorcraft.
    (6) The approach and landing path must be established to avoid the 
critical areas of a limiting height-speed envelope established under 
Sec.  29.79.
    (d) Performance at Minimum Operating Speed. Because of the S-64's 
novel design as an industrial flying crane, in lieu of the requirements 
of Sec.  29.73 (Performance at minimum operating speed) the following 
apply:
    (1) For operations without external load, the hovering performance 
must be determined at 50 feet or more above the takeoff surface over 
the ranges of weight, altitude, and temperature for which takeoff data 
are scheduled. This must be shown with the most critical engine 
inoperative, the remaining engine at not more than the maximum 
certificated single engine rated power, and the landing gear extended.
    (2) For Class A rotorcraft load combination operations, the 
hovering performance must be determined over the ranges of weight, 
altitude, and temperature for which certification is requested, and 
takeoff data must be scheduled--
    (i) Up to takeoff power on each engine;
    (ii) With landing gear extended; and
    (iii) The helicopter at a height consistent with normal takeoff 
procedures.
    (3) For Class B rotorcraft load combination operations, the 
hovering performance must be determined over the ranges of weight, 
altitude, and the temperature for which certification is requested, and 
takeoff data must be scheduled--
    (i) Up to takeoff power on each engine;
    (ii) With landing gear extended; and
    (iii) The rotorcraft out of ground effect.
    (e) Airspeed Indicating System. Because of the S-64's novel design 
as an industrial flying crane, for operations with and without external 
load, compliance must be shown with Sec.  29.1323 (Airspeed indicating 
system) effective February 25, 1968 (Amendment 29-3), modified as 
follows:
    (1) In addition to the flight conditions prescribed in subparagraph 
(b)(1), the system must be calibrated at operational rates of climb.
    (2) In lieu of the speed range prescribed in subparagraph (c)(1), 
the airspeed error may not exceed the requirements throughout the speed 
range in level flight at forward airspeeds of 35 knots or more.
    (f) Power Boost and Power-Operated Control System. Because of the 
S-64's novel design as an industrial flying crane, for operations 
without external load, in lieu of the requirements of Sec.  
29.695(a)(1) (Power boost and power-operated control system) as it 
applies to any single failure of the main rotor tandem servo housing, 
the following apply:
    (1) It must be shown by endurance tests of the tandem servo that 
failure of the servo housing is extremely improbable.
    (2) A tandem servo life limit must be established.
    (3) A periodic inspection program for the tandem servo must be 
established.
    (4) The hydraulic system must be provided with means to ensure that 
system pressure, including transient pressure and pressure from fluid 
volumetric changes in components which are likely to remain closed long 
enough for such changes to occur--
    (i) Are within 90 to 110 percent of pump average discharge pressure 
at each pump outlet or at the outlet of the pump transient pressure 
dampening device, if provided; and
    (ii) May not exceed 135 percent of the design operating pressure, 
excluding pressures at the outlets specified in subparagraph (i) above. 
Design operating pressure is the maximum steady operating pressure.
    (g) Propulsion Conditions. Because of the S-64's novel design as an 
industrial flying crane, its powerplant was designed without a cowling, 
and does not include a fire extinguishing system. Therefore, in lieu of 
the requirements of Sec. Sec.  29.861(a) (Fire protection of structure, 
controls, and other parts), 29.1187(e) (Drainage and ventilation of 
fire zones), 29.1195 (Fire extinguishing systems), 29.1197 (Fire 
extinguishing agents), 29.1199 (Extinguishing agent containers), and 
29.1201 (Fire extinguishing system materials), the following apply:
    (1) Fire protection of structure, control and other parts. 
Compliance must be shown with Sec.  29.861(b) (Fire protection of 
structure, controls, and other parts) so each part of the structure, 
controls, rotor mechanism, and other parts essential to controlled 
landing and flight must be protected so they can perform their 
essential functions for at least 5 minutes under any foreseeable 
powerplant fire condition.
    (2) Powerplant fire protection. In addition to compliance with 
Sec.  29.1183 (Lines and fittings), except for lines and fittings 
approved as part of the engine type certificate under 14 CFR part 33, 
design precautions must be taken in the powerplant compartment to 
safeguard against the ignition of fluids or vapors which could be 
caused by leakage or failure in flammable fluid systems.
    (3) Exhaust system drains. In addition to compliance with Sec.  
29.1121 (Exhaust system: General), compliance must be shown with Sec.  
29.1121(h) (Exhaust system: General) effective February 25, 1968 
(Amendment 29-3) in that if there are significant low spots or pockets 
in the engine exhaust system, the system must have drains that 
discharge clear of the rotorcraft, in normal ground and flight 
attitudes, to prevent the accumulation of fuel after the failure of an 
attempted engine start.
    (4) Rotor drive system testing. If the engine power output to the 
transmission can exceed the highest engine or transmission power rating 
and the output is not directly controlled by the pilot under normal 
operating conditions (such as the control of the primary engine power 
control by the flight control), in addition to the endurance tests 
prescribed in Sec.  29.923 (Rotor drive system and control mechanism 
tests), the following test must be made:
    (i) With all engines operating, apply torque at least equal to the 
maximum torque used in meeting Sec.  29.923 plus 10 percent for at 
least 220 seconds.
    (ii) With each engine, in turn, inoperative, apply to the remaining 
transmission power inputs the maximum torque attainable under probable 
operating conditions, assuming that torque limiting devices are 
functioning properly. Each transmission input must be tested at this 
maximum torque for at least 5 minutes.
    (5) Powerplant installation. In addition to the requirements of 
Sec.  29.901 (Installation), compliance must be shown with Sec.  
29.901(b)(5) (Installation) effective February 25, 1968 (Amendment 29-
3) in that the axial and radial expansion of the engines may not affect 
the safety of the powerplant installation.
    (6) Powerplant operation characteristics. In addition to the 
requirements of Sec.  29.939 (Turbine

[[Page 50693]]

engine operating characteristics), the powerplant operating 
characteristics must be investigated in flight to determine that no 
adverse characteristics, such as stall, surge, or flameout are present 
to a hazardous degree during normal and emergency operation of the 
helicopter within the range of operating limitations of the helicopter 
and of the engine.
    (7) Powerplant control system. In addition to the requirements of 
Sec.  29.1141 (Powerplant controls: General), the powerplant control 
system must be investigated to ensure that no single, likely failure or 
malfunction in the helicopter installed components of the system can 
cause a hazardous condition that cannot be safely controlled in flight.
    (8) Fuel pump installation. In addition to the requirements of 
Sec.  29.991 (Fuel pumps), there must be provisions to maintain the 
fuel pressure at the inlet of the engine fuel system within the limits 
established for engine operation throughout the operating envelope of 
the helicopter.
    (9) Fuel strainer. In addition to the requirements of Sec.  29.997 
(Fuel strainer or filter), compliance must be shown with Sec.  
29.997(e) (Fuel strainer or filter) effective February 25, 1968 
(Amendment 29-3) in that unless there are means in the fuel system to 
prevent the accumulation of ice on the filter, there must be means to 
automatically maintain the fuel flow if ice-clogging of the filter 
occurs.
    (10) Cooling test. In lieu of the requirements of Sec.  29.1041(a) 
(Powerplant cooling: General), which includes requirements for 
reciprocating engines, compliance must be shown with Sec.  29.1041(a) 
(Powerplant cooling: General) effective February 25, 1968 (Amendment 
29-3) in that the powerplant cooling provisions must maintain the 
temperatures of powerplant components and engine fluids within safe 
values under critical surface and flight operating conditions and after 
normal engine shutdown.
    (11) Induction system icing protection. The S-64 has two turbine 
engines; therefore, in lieu of Sec.  29.1093 (Induction system icing 
protection), which includes requirements for reciprocating engines, 
compliance must be shown with Sec.  29.1093(b) (Induction system icing 
protection) effective February 25, 1968 (Amendment 29-3) in that each 
engine must operate throughout its flight power range, without adverse 
effect on engine operation or serious loss of power or thrust under the 
icing conditions specified in appendix C of 14 CFR part 25.
    (12) Induction system duct. The S-64 has two turbine engines; 
therefore, in lieu of Sec.  29.1091(d) and (e) (Air induction), which 
includes requirements for reciprocating engines, compliance must be 
shown with Sec.  29.1091(f) (Air induction) effective February 25, 1968 
(Amendment 29-3) in that:
    (i) There must be means to prevent hazardous quantities of fuel 
leakage or overflow from drains, vents, or other components of 
flammable fluid systems from entering the engine intake system.
    (ii) The air inlet ducts must be located or protected to minimize 
the ingestion of foreign matter during takeoff, landing, and taxiing.
    (h) Powerplant Instruments. At the time of original certification, 
the S-64 had a novel design of being powered by two turbine engines; 
therefore, in lieu of Sec.  29.1305 (Powerplant instruments), which 
includes requirements for reciprocating engines, compliance must be 
shown with Sec.  29.1305 (Powerplant instruments) effective February 
25, 1968 (Amendment 29-3) in that the following are required powerplant 
instruments:
    (1) A fuel quantity indicator for each fuel tank.
    (2) If an engine can be supplied with fuel from more than one tank, 
a warning device to indicate, for each tank, when a 5-minute usable 
fuel supply remains when the rotorcraft is in the most adverse fuel 
feed condition for that tank, regardless of whether that condition can 
be sustained for the 5 minutes.
    (3) An oil pressure warning device for each pressure lubricated 
gearbox to indicate when the oil pressure falls below a safe value.
    (4) An oil quantity indicator for each oil tank and each rotor 
drive gearbox, if lubricant is self-contained.
    (5) An oil temperature indicator for each engine.
    (6) An oil temperature warning device for each main rotor drive 
gearbox to indicate unsafe oil temperatures.
    (7) A gas temperature indicator for each turbine engine.
    (8) A gas producer rotor tachometer for each turbine engine.
    (9) A tachometer for each engine that, if combined with the 
instrument required by subparagraph (10) of this paragraph, indicates 
rotor rpm during autorotation.
    (10) A tachometer to indicate the main rotor rpm.
    (11) A free power turbine tachometer for each engine.
    (12) A means for each engine to indicate power for that engine.
    (13) An individual oil pressure indicator for each engine, and 
either an independent warning device for each engine or a master 
warning device for the engines with means for isolating the individual 
warning circuit from the master warning device.
    (14) An individual fuel pressure indicator or equivalent device for 
each engine, and either an independent warning device for each engine 
or a master warning device for the engines with means for isolating the 
individual warning circuit from the master warning device.
    (15) Fire warning indicators.
    (i) Cargo and baggage compartments. Since the S-64 includes an 
unusual design in that the baggage compartments are located in the nose 
of the airframe and are inaccessible during flight, in lieu of Sec.  
29.855(d), compliance must be shown with Sec.  29.855(d) effective 
February 25, 1968 (Amendment 29-3) so that each cargo and baggage 
compartment is sealed to contain cargo or baggage compartment fires 
completely without endangering the safety of the rotorcraft or its 
occupants.
    (j) Auxiliary Control Station. The S-64 includes a novel design for 
an optional aft-facing pilot position (auxiliary control station) which 
is used during precision placement rotorcraft load combination 
operations. There are no specific requirements in the airworthiness 
standards for this type of pilot position. Therefore, if the auxiliary 
control station is equipped with flight controls--
    (1) The rotorcraft must be safely controllable by the auxiliary 
controls, throughout the range of the auxiliary controls.
    (2) The auxiliary controls may not interfere with the safe 
operation of the rotorcraft by the pilot or copilot when the station is 
not occupied.
    (3) The auxiliary control station and its associated equipment must 
allow the operator to perform his or her duties without unreasonable 
concentration or fatigue.
    (4) The vibration and noise characteristics of the auxiliary 
control station appurtenances must not interfere with the operator's 
assigned duties to an extent that would make the operation unsafe.
    (5) The auxiliary control station must be arranged to give the 
operator sufficiently extensive, clear, and undistorted view for safe 
operation. The station must be free of glare and reflection that could 
interfere with the operator's view.
    (6) There must be provisions to prevent unintentional movement of 
the controls when the rear-facing aft-stick operator's seat is occupied 
by other than essential crewmembers during other than external-load 
operations.

[[Page 50694]]

    (k) Quick-Release Devices. The S-64 is specifically designed for 
rotorcraft load combination operations with particular weight-specified 
hard points designed into the airframe. Because of this unusual design, 
when quick release devices are required under 14 CFR part 133, it must 
enable the pilot to release the external-load quickly during flight. 
The quick-release system must comply with the following:
    (1) An activating control for the quick-release system must be 
installed on one of the pilot's primary controls and must be designed 
and located so it may be operated by the pilot without hazardously 
limiting his or her ability to control the rotorcraft during an 
emergency situation.
    (2) An alternative independent activating control for the quick-
release system must be provided and must be readily accessible to the 
pilot or a crewmember.
    (3) The design of the quick-release system must ensure that 
failure, which could prevent the release of external loads, is 
extremely improbable.
    (4) The quick-release system must be capable of functioning 
properly after failure of all engines.
    (5) The quick-release system must function properly with external 
loads up to and including the maximum weight for which certification is 
requested.
    (6) The quick-release system must include a means to check for 
proper operation of the system at established intervals.
    (l) Maximum Weight with External Load. When establishing compliance 
with Sec.  29.25, the maximum weight of the rotorcraft-load combination 
for operations with external loads must be established by the applicant 
and may not exceed the weight at which compliance with all applicable 
requirements has been shown.
    (m) External Load Jettisoning. The external load must be 
jettisonable to the maximum weight for which the helicopter has been 
type certificated for operation without external loads or with Class A 
loads.
    (n) Minimum Flight Crew. To meet the requirements of Sec.  29.1523, 
the minimum flight crew consists of a pilot and a copilot. For pickup 
of the external-load and on-site maneuvering and release of the 
external-load, the copilot may act as the aft-facing hoist operator.
    (o) Occupancy. When engaged in operations other than external-load 
operations under 14 CFR part 133, the carriage of passengers in the two 
observer seats and the rear-facing aft-stick operator's seat, when the 
aft-stick operator's controls are disengaged and the collective guard 
is installed, will be controlled by the FAA operating requirements 
applicable to that particular operation.
    (p) Operations. The S-64 meets the Category B fire protection 
requirements for structures and controls in lieu of Category A 
requirements. Therefore, when operating over congested areas, the 
rotorcraft must be operated at an altitude and over routes that provide 
suitable landing areas that can be reached in no more than 5 minutes.
    (q) Markings and Placards. For purposes of rotorcraft load 
combination operations, the following markings and placards must be 
displayed conspicuously and must be applied so they cannot be easily 
erased, disfigured, or obscured.
    (1) A placard, plainly visible to appropriate crewmembers, 
referring to the helicopter flight manual limitations and restrictions 
for rotorcraft load combinations allowed under 14 CFR part 133.
    (2) A placard, marking, or instructions (displayed next to the 
external-load attaching means) stating the maximum external-load 
prescribed as an operating limitation for rotorcraft load combinations 
allowed under 14 CFR part 133.
    (3) A placard in the cockpit prescribing the occupancy limitation 
during rotorcraft load combination operations under 14 CFR part 133.

    Issued in Fort Worth, Texas, on August 4, 2010.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2010-19921 Filed 8-16-10; 8:45 am]
BILLING CODE 4910-13-P