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paragraph.
Certificate Holder Representative: (Name & Signature)
Position: Date(Y/M/D):
CCAR-121 / 135 OPERATIONS SPECIFICATIONS
CAAC DOCUMENT
APPROVAL NO
AC-121-001R1
(Company Name) H0001-1 Certificate No:
Effective Date: D M Y
PART H: ROTORCRAFT
H0001 PERFORMANCE REQUIREMENTS FOR TRANSPORT CATEGORY HELICOPTERS
The certificate holder is authorized to operate the transport category helicopters listed in the following
table with the appropriate minimum level of performance and operating requirements according to
performance data contained in the Rotorcraft Flight Manual (RFM) and the special operational
conditions and limitations listed in subparagraphs a, b and c, as appropriate.
HELICOPTER
(MAKE/MODEL/SERIES)
SEAT CONFIGURATION
a. For transport category helicopters configured with 9 or less passenger seats:
(1) The gross weight of the helicopter at take-off must not exceed the maximum gross weight
specified in the RFM for hover in-ground-effect with all engines operating at take-off power for
the specific take-off altitude, temperature, and wind conditions.
(2) The gross weight of the helicopter on landing must not exceed the maximum gross weight
specified in the RFM for hover in-ground-effect with all engines operating at take-off power for
the specific landing altitude, temperature, and wind conditions.
(3) In either of the above cases, if it is expected that a hover in-ground-effect will not be
established due to operating conditions (such as confined area vertical take-off/landing or
pinnacle take-off/landing), the gross weight must not exceed the maximum gross weight
specified in the RFM for hover out-of-ground-effect with all engines operating at take-off
power for the specific altitude, temperature, and wind conditions.
b. For transport category helicopter configured with 10-19 passenger seats, the weight limitations
should comply with that specified in sub-paragraph a(1) and a(2) of this paragraph and in
addition;
(1) The gross weight of the helicopter at take-off must not exceed the maximum gross weight
specified in the RFM for a rate of climb of 150 ft (45m)/min. at 1000 ft (300m) above the takeoff
surface with the critical engine inoperative and the remaining engine operating at 30
minute or maximum continuous one-engine-inoperative (OEI) power for the specific take-off
altitude and temperature.
(2) The gross weight of the helicopter on landing must not exceed the maximum gross weight
specified in the RFM for a rate of climb of 150 ft (45m)/min. at 1000 ft (300m) above the
landing surface with the critical engine inoperative and the remaining engine operating at 30
minute or maximum continuous one-engine-inoperative (OEI) power for the specific landing
altitude and temperature.
CCAR-121 / 135 OPERATIONS SPECIFICATIONS
CAAC DOCUMENT
APPROVAL NO
AC-121-001R1
(Company Name) H0001-2 Certificate No:
Effective Date: D M Y
c. Transport category large helicopters configured with 20 or more passenger seats, or configured
with10 or more seats and used for schedule operations, should conduct operations in
accordance to the approved procedures in this operations specification, and:
(1) The gross weight of the helicopter at take-off must not exceed the maximum gross weight so
that in an event when an engine fails at or before Take-Off Decision Point, the helicopter can
land within the Abort Take-Off Distance; or in the event the engine fails after Take-Off
Decision Point, the helicopter can continue to fly away, clear all obstacles and fulfill all climb
performance requirements specified in subparagraph b(1), for the specific take-off altitude,
temperature.
(2) During en route operations, if an engine fails, the helicopter should be able to maintain a
cruising altitude not below the minimum enroute altitude (MEA) if applicable, to either its
destination or alternate airport.
(3) The gross weight of the helicopter at landing must not exceed the maximum gross weight so
that in an event when an engine fails at or before the Landing Decision Point, the helicopter
can land within the touchdown zone or conduct a missed approach, clear all obstacles and
fulfill all climb performance requirements specified in subparagraph b(2); or in the event the
engine fails after the Landing Decision Point, the helicopter can continue to land within the
touchdown zone, for the specific landing altitude, temperature.
1. Issued by (Branch Name) ,Regional Administration of CAAC
2. These Operations Specifications are approved by direction of CAAC
Principal Operations Inspector: (Name & Signature of POI)
3. Date Approval is effective (Y/M/D) Amendment Number:
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CCAR121_135 Operations Specifications(83)
