Table Of ContentAnnex to ED Decision 2008/009/R
European Aviation Safety Agency
Certification Specifications
for
Small Rotorcraft
CS27
Amendment 2
17 November 2008
Amendment 2
CS27
Annex to ED Decision 2008/009/R
CONTENTS (general layout)
CS–27
SMALL ROTORCRAFT
BOOK 1 – AIRWORTHINESS CODE
SUBPART A – GENERAL
SUBPART B – FLIGHT
SUBPART C – STRENGTH REQUIREMENTS
SUBPART D – DESIGN AND CONSTRUCTION
SUBPART E – POWERPLANT
SUBPART F – EQUIPMENT
SUBPART G – OPERATING LIMITATIONS AND INFORMATION
APPENDICES: A, B and C
BOOK 2 – ACCEPTABLE MEANS OF COMPLIANCE (AMC):
AMCs
Amendment 2
C1
Annex to ED Decision 2008/009/R
CS27
PREAMBLE
CS27 Amendment 1 Effective: 30/11/2007
The following is a list of paragraphs affected by this amendment.
Book 1
Subpart B
• CS 27.25 Amended (NPA11/2006)
• CS 27.49 Created by renaming CS 27.73(NPA11/2006)
• CS 27.51 Amended (NPA11/2006)
• CS 27.73 Deleted and moved to CS 27.49(NPA11/2006)
• CS 27.75 Amended (NPA11/2006)
• CS 27.79 Amended (NPA11/2006)
• CS 27.143 Amended (NPA11/2006)
• CS 27.173 Amended (NPA11/2006)
• CS 27.175 Amended (NPA11/2006)
• CS 27.177 Amended (NPA11/2006)
Subpart E
• CS 27.903 Amended (NPA11/2006)
Subpart G
• CS 27.1587 Amended (NPA11/2006)
Appendices
• CS27 Appendix B Amended (NPA 11/2006)
CS27 Amendment 2 Effective: 17/11/2008
The following is a list of paragraphs affected by this amendment.
Book 1
Subpart F
• CS 27.1305 Amended (NPA200717)
Appendices
• CS27 Appendix A Amended (NPA 200717)
• CS27 Appendix C Amended (NPA 200717)
Book 2
• AMC 27 General Amended (NPA200717)
• AMC 27.351 Created (NPA 200717)
• AMC 27.602 Deleted (NPA 200717)
• AMC 27.865 Created (NPA 200717)
• AMC 27.1305(t) and (u) Deleted (NPA 200717)
• AMC MG4 Created (NPA 200717)
Amendment 2
P1
Annex to ED Decision 2008/009/R
CS27 BOOK 1
EASA Certification Specifications
for
SMALL ROTORCRAFT
CS27
Book 1
Airworthiness code
Amendment 2
101
Annex to ED Decision 2008/009/R
CS–27 BOOK 1
SUBPART A – GENERAL
CS 27.1 Applicability
(a) This Airworthiness Code is applicable
to small rotorcraft with maximum weights of
3 175 kg (7 000 lbs) or less and nine or less
passenger seats.
(b) reserved
(c) Multiengine rotorcraft may be type
certificated as Category A provided the
requirements referenced in Appendix C are
met.
JAR 27.2 Special Retroactive Requirements
(a) reserved
(b) For rotorcraft with a certification basis
established prior to 1 May 2001
(1) The maximum passenger seat
capacity may be increased to eight or nine
provided compliance is shown with all the
INTENTIONALLY LEFT BLANK
airworthiness requirements of this initial issue
ofCS27.
(2) The maximum weight may be
increased to greater than 2 722 kg (6 000 lbs)
provided
(i) The number of passenger
seats is not increased above the
maximum number previously
certificated; or
(ii) Compliance is shown with
all of the airworthiness requirements of
this initial issue of CS27.
Amendment 2
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Annex to ED Decision 2008/009/R
CS–27 BOOK 1
SUBPART B – FLIGHT
GENERAL (iii) The weight of full oil
capacity; and
(iv) For each seat, an occupant
CS 27.21 Proof of compliance weight of 77 kg (170 lbs) or any lower
weight for which certification is
Each requirement of this Subpart must be met
requested.
at each appropriate combination of weight and
centre of gravity within the range of loading (b) Minimum weight. The minimum weight,
conditions for which certification is requested. the lowest weight at which compliance with each
This must be shown: applicable requirement of this CS–27 is shown,
must be established so that it is:
(a) By tests upon a rotorcraft of the type for
which certification is requested or by calculations (1) Not more than the sum of:
based on, and equal in accuracy to, the results of
(i) The empty weight determined
testing; and
under CS 27.29; and
(b) By systematic investigation of each
(ii) The weight of the minimum
required combination of weight and centre of
crew necessary to operate the rotorcraft,
gravity if compliance cannot be reasonably
assuming for each crew member a weight
inferred from combinations investigated.
no more than 77 kg (170 lbs), or any
lower weight selected by the applicant or
included in the loading instructions; and
CS 27.25 Weight limits
(2) Not less than:
(a) Maximum weight. The maximum
(i) The lowest weight selected by
weight, the highest weight at which compliance
the applicant;
with each applicable requirement of this CS–27
is shown, must be established so that it is: (ii) The design minimum weight,
the lowest weight at which compliance
(1) Not more than:
with each applicable structural loading
(i) The highest weight selected condition of this CS–27 is shown; or
by the applicant;
(iii) The lowest weight at which
(ii) The design maximum weight, compliance with each applicable flight
the highest weight at which compliance requirement of this CS–27 is shown.
with each applicable structural loading
(c) Total weight with jettisonable external
condition of this CS–27 is shown;
load. A total weight for the rotorcraft with a
(iii) The highest weight at which jettisonable external load attached that is greater
compliance with each applicable flight than the maximum weight established under sub
requirement of this CS–27 is shown; or paragraph (a) may be established for any
rotorcraftload combination if:
(iv) The highest weight, as a
function of altitude and temperature, in (1) The rotorcraftload combination
which the provisions of CS 27.79 and/or does not include human external cargo,
CS 27.143(c)(1) are demonstrated if the (2) Structural component approval for
operating conditions (altitude and external load operations under either CS
temperature) prescribed by those 27.865, or under equivalent operational
requirements can not be met; and standards is obtained,
(2) Not less than the sum of: (3) The portion of the total weight that
is greater than the maximum weight
(i) The empty weight determined
established under subparagraph (a) is made
under CS 27.29;
up only of the weight of all or part of the
(ii) The weight of usable fuel jettisonable external load,
appropriate to the intended operation
(4) Structural components of the
with full payload;
rotorcraft are shown to comply with the
applicable structural requirements of this CS
Amendment 2
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Annex to ED Decision 2008/009/R
CS–27 BOOK 1
27 under the increased loads and stresses
caused by the weight increase over that
CS 27.33 Main rotor speed and pitch
established under subparagraph (a) , and
limits
(5) Operation of the rotorcraft at a
(a) Main rotor speed limits. A range of
total weight greater than the maximum
main rotor speeds must be established that:
certificated weight established under sub
paragraph (a) is limited by appropriate (1) With poweron, provides adequate
operating limitations under CS 27.865 (a) and margin to accommodate the variations in rotor
(d). speed occurring in any appropriate manoeuvre,
and is consistent with the kind of governor or
[Amdt. No.: 27/1]
synchroniser used; and
(2) With poweroff, allows each
CS 27.27 Centre of gravity limits appropriate autorotative manoeuvre to be
performed throughout the ranges of airspeed
The extreme forward and aft centres of gravity
and weight for which certification is
and, where critical, the extreme lateral centres of
requested.
gravity must be established for each weight
established under CS 27.25. Such an extreme (b) Normal main rotor high pitch limits
may not lie beyond: (poweron). For rotorcraft, except helicopters
required to have a main rotor low speed warning
(a) The extremes selected by the applicant;
under subparagraph (e). It must be shown, with
(b) The extremes within which the structure poweron and without exceeding approved engine
is proven; or maximum limitations, that main rotor speeds
substantially less than the minimum approved
(c) The extremes within which compliance
main rotor speed will not occur under any
with the applicable flight requirements is shown.
sustained flight condition. This must be met by:
(1) Appropriate setting of the main
CS 27.29 Empty weight and rotor high pitch stop;
corresponding centre of gravity (2) Inherent rotorcraft characteristics
that make unsafe low main rotor speeds
(a) The empty weight and corresponding
unlikely; or
centre of gravity must be determined by weighing
the rotorcraft without the crew and payload but (3) Adequate means to warn the pilot
with: of unsafe main rotor speeds.
(1) Fixed ballast; (c) Normal main rotor low pitch limits
(poweroff). It must be shown, with poweroff,
(2) Unusable fuel; and
that:
(3) Full operating fluids, including:
(1) The normal main rotor low pitch
(i) Oil; limit provides sufficient rotor speed, in any
autorotative condition, under the most critical
(ii) Hydraulic fluid; and
combinations of weight and airspeed; and
(iii) Other fluids required for
(2) It is possible to prevent
normal operation of rotorcraft systems,
overspeeding of the rotor without exceptional
except water intended for injection in the
piloting skill.
engines.
(d) Emergency high pitch. If the main rotor
(b) The condition of the rotorcraft at the
high pitch stop is set to meet subparagraph
time of determining empty weight must be one
(b)(1), and if that stop cannot be exceeded
that is well defined and can be easily repeated,
inadvertently, additional pitch may be made
particularly with respect to the weights of fuel,
available for emergency use.
oil, coolant, and installed equipment.
(e) Main rotor low speed warning for
helicopters. For each single engine helicopter, and
each multiengine helicopter that does not have an
CS 27.31 Removable ballast
approved device that automatically increases power
Removable ballast may be used in showing
on the operating engines when one engine fails,
compliance with the flight requirements of this
there must be a main rotor low speed warning which
Subpart.
meets the following requirements:
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CS–27 BOOK 1
(1) The warning must be furnished to (1) 80%, at and below standard
the pilot in all flight conditions, including temperature; and
poweron and poweroff flight, when the speed
(2) 34%, at and above standard
of a main rotor approaches a value that can
temperature plus 28°C (50°F) between these
jeopardise safe flight.
two temperatures, the relative humidity must
(2) The warning may be furnished vary linearly.
either through the inherent aerodynamic
(f) For turbine enginepowered rotorcraft, a
qualities of the helicopter or by a device.
means must be provided to permit the pilot to
(3) The warning must be clear and determine prior to takeoff that each engine is
distinct under all conditions, and must be capable of developing the power necessary to
clearly distinguishable from all other achieve the applicable rotorcraft performance
warnings. A visual device that requires the prescribed in this Subpart.
attention of the crew within the cockpit is not
acceptable by itself.
CS 27.49 Performance at minimum
(4) If a warning device is used, the
operating speed
device must automatically deactivate and
reset when the lowspeed condition is (a) For helicopters:
corrected. If the device has an audible
(1) The hovering ceiling must be
warning, it must also be equipped with a
determined over the ranges of weight, altitude,
means for the pilot to manually silence the
and temperature for which certification is
audible warning before the lowspeed
requested, with:
condition is corrected.
(i) Takeoff power;
(ii) The landing gear extended;
PERFORMANCE
and
(iii) The helicopter in ground
effect at a height consistent with normal
CS 27.45 General
takeoff procedures; and
(a) Unless otherwise prescribed, the
(2) The hovering ceiling determined in
performance requirements of this Subpart must
subparagraph (a)(1) of this paragraph must be
be met for still air and a standard atmosphere.
at least:
(b) The performance must correspond to the
(i) For reciprocating engine
engine power available under the particular
powered helicopters, 1219 m (4 000 ft) at
ambient atmospheric conditions, the particular
maximum weight with a standard
flight condition, and the relative humidity
atmosphere; or
specified in subparagraphs (d) or (e), as
appropriate. (ii) For turbine enginepowered
helicopters, 762 m (2 500 ft) pressure
(c) The available power must correspond to
altitude at maximum weight at a
engine power, not exceeding the approved power,
temperature of standard +22°C (+40°F).
less:
(3) The outofground effect hovering
(1) Installation losses; and
performance must be determined over the
(2) The power absorbed by the ranges of weight, altitude, and temperature for
accessories and services appropriate to the which certification is requested, using takeoff
particular ambient atmospheric conditions and power.
the particular flight condition.
(b) For rotorcraft other than helicopters, the
(d) For reciprocating enginepowered steady rate of climb at the minimum operating
rotorcraft, the performance, as affected by engine speed must be determined, over the ranges of
power, must be based on a relative humidity of weight, altitude, and temperature for which
80% in a standard atmosphere. certification is requested, with:
(e) For turbine enginepowered rotorcraft, (1) Takeoff power; and
the performance, as affected by engine power,
(2) The landing gear extended.
must be based on a relative humidity of:
Amendment 2
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Annex to ED Decision 2008/009/R
CS–27 BOOK 1
[Amdt. No.: 27/1] (ii) At maximum weight; and
(iii) With maximum continuous
power on each engine.
CS 27.51 Takeoff
(2) The steady rate of climb must be
The takeoff, with takeoff power and rpm at the
determined:
most critical center of gravity, and with weight
from the maximum weight at sealevel to the (i) At the climb speed selected by
weight for which takeoff certification is the applicant at or below VNE;
requested for each altitude covered by this
(ii) Within the range from sea
paragraph:
level up to the maximum altitude for
(a) May not require exceptional piloting skill which certification is requested;
or exceptionally favourable conditionsthroughout
(iii) For the weights and
the ranges of altitude from standard sealevel
temperatures that correspond to the
conditions to the maximum altitude for which take
altitude range set forth in subparagraph
off and landing certification is requested, and (b)(2)(ii) and for which certification is
requested; and
(b) Must be made in such a manner that a
landing can be made safely at any point along the (iv) With maximum continuous
flight path if an engine fails. This must be power on each engine.
demonstrated up to the maximum altitude for which
takeoff and landing certification is requested or
2134m (7,000 ft) density altitude, whichever is less. CS 27.67 Climb: oneengineinoperative
[Amdt. No.: 27/1] For multiengine helicopters, the steady rate of
climb (or descent), at V (or at the speed for
Y
minimum rate of descent), must be determined
CS 27.65 Climb: allenginesoperating with:
(a) For rotorcraft other than helicopters: (a) Maximum weight;
(1) The steady rate of climb, at V (b) The critical engine inoperative and the
Y
must be determined: remaining engines at either:
(i) With maximum continuous (1) Maximum continuous power and,
power on each engine; for helicopters for which certification for the
use of 30minute one engine inoperative (OEI)
(ii) With the landing gear
power is requested, at 30minute OEI power;
retracted; and
or
(iii) For the weights, altitudes, and (2) Continuous OEI power for
temperatures for which certification is helicopters for which certification for the use
requested; and of continuous OEI power is requested.
(2) The climb gradient, at the rate of
climb determined in accordance with sub
CS 27.71 Glide performance
paragraph (a)(1), must be either:
For singleengine helicopters and multiengine
(i) At least 1:10 if the horizontal
helicopters that do not meet the category A
distance required to take off and climb
engine isolation requirements of CS–27, the
over a 15 m (50 ft) obstacle is
minimum rate of descent airspeed and the best
determined for each weight, altitude, and
angleofglide airspeed must be determined in
temperature within the range for which
autorotation at:
certification is requested; or
(a) Maximum weight; and
(ii) At least 1:6 under standard
sealevel conditions. (b) Rotor speed(s) selected by the applicant.
(b) Each helicopter must meet the following
requirements:
CS 27.75 Landing
(1) V must be determined:
Y (a) The rotorcraft must be able to be landed
(i) For standard sealevel with no excessive vertical acceleration, no
conditions;
Amendment 2
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CS–27 BOOK 1
tendency to bounce, nose over, ground loop, limits and at the minimum installed
porpoise, or water loop, and without exceptional specification power available for the most
piloting skill or exceptionally favourable critical combination of approved ambient
conditions, with: temperature and pressure altitude resulting in
2134m (7000 ft) density altitude or the
(1) Approach or autorotation speeds
maximum altitude capability of the helicopter,
appropriate to the type of rotorcraft and
whichever is less; and
selected by the applicant;
(3) For other rotorcraft, conditions
(2) The approach and landing made
appropriate to the type.
with:
(i) Power off, for singleengine [Amdt. No.: 27/1]
rotorcraft and entered from steady state
autorotation; or
FLIGHT CHARACTERISTICS
(ii) Oneengine inoperative (OEI)
for multiengine rotorcraft with each
operating engine within approved
operating limitations, and entered from CS 27.141 General
an established OEI approach.;
The rotorcraft must:
(b) Multiengine rotorcraft must be able to
(a) Except as specifically required in the
be landed safely after complete power failure
applicable paragraph, meet the flight
under normal operating conditions.
characteristics requirements of this Subpart:
[Amdt. No.: 27/1]
(1) At the altitudes and temperatures
expected in operation;
CS 27.79 Limiting heightspeed envelope (2) Under any critical loading
condition within the range of weights and
(a) If there is any combination of height and
centres of gravity for which certification is
forward speed, including hover, under which a
requested;
safe landing cannot be made under the applicable
power failure condition in subparagraph (b), a (3) For poweron operations, under any
limiting heightspeed envelope must be condition of speed, power, and rotor rpm for
established, including all pertinent information, which certification is requested; and
for that condition, throughout the ranges of:
(4) For poweroff operations, under
(1) Altitude, from standard sealevel any condition of speed and rotor rpm for
conditions to the maximum altitude capability which certification is requested that is
of the rotorcraft, or 2134 m (7 000 ft) density attainable with the controls rigged in
altitude, whichever is less; and accordance with the approved rigging
instructions and tolerances;
(2) Weight from the maximum weight
at sealevel to the weight selected by the (b) Be able to maintain any required flight
applicant for each altitude covered by sub condition and make a smooth transition from any
paragraph (a)(1) of this paragraph. For flight condition to any other flight condition
helicopters, the weight at altitudes above sea without exceptional piloting skill, alertness, or
level may not be less than the maximum strength, and without danger of exceeding the
weight or the highest weight allowing limit load factor under any operating condition
hovering out of ground effect whichever is probable for the type, including:
lower.
(1) Sudden failure of one engine, for
(b) The applicable power failure conditions multiengine rotorcraft meeting category A
are: engine isolation requirements of CS–29;
(1) For singleengine helicopters, full (2) Sudden, complete power failure for
autorotation; other rotorcraft; and
(2) For multiengine helicopters, OEI, (3) Sudden, complete control system
where engine isolation features ensure failures specified in CS 27.695; and
continued operation of the remaining engines,
(c) Have any additional characteristic
and the remaining engine(s) within approved
required for night or instrument operation, if
Amendment 2
1–B– 5
Description:Subpart E. • CS 27.903. Amendedаа(NPA 11/2006). Subpart G Book 2. • AMC 27 General. Amendedаа(NPA 200717). • AMC 27.351 EASA Certification Specifications for. SMALL ROTORCRAFT. CS27. Book 1 . up only of the weight of all or part of the .. the margin of cyclic control must allow.
