Type Acceptance Report CESSNA 510

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Aircraft Certification Unit
Type Acceptance Report
TAR 8/21B/14
CESSNA 510
Type Acceptance Report
Rev.0 : 27 March 2008 i TAR 8/21B/14 – Cessna 510
TABLE OF CONTENTS
EXECUTIVE SUMMARY 1
1. INTRODUCTION 1
2. ICAO TYPE CERTIFICATE DETAILS 1
3. TYPE ACCEPTANCE DETAILS 2
4. NZCAR §21.43 DATA REQUIREMENTS 2
5. ADDITIONAL NEW ZEALAND REQUIREMENTS 5
ATTACHMENTS 6
APPENDIX 1 6
Type Acceptance Report
Rev.0 : 27 March 2008 1 TAR 8/21B/14 – Cessna 510
Executive Summary
New Zealand Type Acceptance has been granted to the Cessna 510 based on validation of
FAA Type Certificate number A00014WI. There are no special requirements for import.
Applicability is currently limited to the Models and/or serial numbers detailed in Appendix
1, which are now eligible for the issue of an Airworthiness Certificate in the Standard
Category in accordance with NZCAR §21.177, subject to any outstanding New Zealand
operational requirements being met. (See Section 5 of this report for a review of
compliance of the basic type design with the operating Rules.) Additional variants or serial
numbers approved under the foreign type certificate can become type accepted after supply
of the applicable documentation, in accordance with the provisions of NZCAR §21.43(c).
1. Introduction
This report details the basis on which Type Acceptance Certificate No.8/21B/14 was
granted in the Standard Category in accordance with NZCAR Part 21 Subpart B.
Specifically the report aims to:
(a) Specify the foreign type certificate and associated airworthiness design standard
used for type acceptance of the model(s) in New Zealand; and
(b) Identify any special conditions for import applicable to any model(s) covered by the
Type Acceptance Certificate; and
(c) Identify any additional requirements which must be complied with prior to the issue
of a NZ Airworthiness Certificate or for any subsequent operations.
2. ICAO Type Certificate Details
Manufacturer: Cessna Aircraft Company
Type Certificate: A00014WI
Issued by: Federal Aviation Administration
Model: 510
MCTOW 8645 lb. [3877 kg.]
Max. No. of Seats: 6
Noise Standard: FAR 36 (Stage 4)
Engine: Pratt & Whitney Canada PW615F-A
Type Certificate: E-34
Issued by: Transport Canada
(FAA Type Certificate E00073EN)
Type Acceptance Report
TAR 8/21B/14 – Cessna 510 2 Rev.0 : 27 March 2008
3. Type Acceptance Details
The application for New Zealand type acceptance of the 510 was from the manufacturer,
dated 5 October 2007. The first-of-type example was serial number 510-0054, to be
registered ZK-MUS. The Model 510 is an entry-level 6-seat twin turbofan very light jet.
As part of the validation process a CAA certification specialist visited Cessna in Wichita.
Type Acceptance Certificate No. 8/21B/14 was granted on 27 March 2008 to the Cessna
Model 510 based on validation of FAA Type Certificate A00014WI. (The PW615F-A
engine is covered by Type Acceptance Certificate number 8/21B/21.) Specific applicability
is limited to the coverage provided by the operating documentation supplied. For operation
in New Zealand the Model 510 must have the optional 40 cu. ft. oxygen bottle fitted.
The Model 510 Citation Mustang is an all-new design of light business jet of conventional
all-metal construction with seating for four passengers and a toilet. The configuration is
similar to previous Citations with a T-tail, speedbrake-equipped and a low wing with slight
leading edge sweep. The cockpit uses the Garmin G1000 electronic avionics/instrument
system with dual 10 inch Primary Flight Displays and one 15 inch Multi-Function Display.
The aft-mounted 1460 lb. thrust PW615F engines are FADEC-equipped. VMO/MMO is 250
KCAS/0.63M and maximum operating altitude is 41,000 feet. The Model 510 is approved
for single pilot IFR operation and flight into known icing conditions.
4. NZCAR §21.43 Data Requirements
The type data requirements of NZCAR Part 21B Para §21.43 have been satisfied by supply
of the following documents, or were already held by the CAA:
(1) ICAO Type certificate:
FAA Type Certificate Number A00014WI
FAA Type Certificate Data Sheet number A00014WI at Revision 1 dated 19.09.06
– Model 510 approved September 8, 2006
(2) Airworthiness design requirements:
(i) Airworthiness Design Standards:
The certification basis of the Cessna 510 is FAR Part 23 effective 1 February 1965,
including Amendments 23-1 through 23-54. This is an acceptable certification basis
in accordance with NZCAR Part 21B Para §21.41 and Advisory Circular 21-1, as
FAR 23 is the basic standard for Normal Category Airplanes called up under Part
21 Appendix C. There are no non-compliances and no additional special conditions
have been prescribed by the Director under §21.23.
(ii) Special Conditions:
No. 23-158-SC Protection of Systems for High Intensity Radiated Fields – There
must be shown to be no adverse effects for the critical EFIS, ADA and FADEC systems on the
Model 510 aircraft resulting from exposure to the HIRF spectrum specified in this SC.
No. 23-181-SC Flight Performance, Characteristics and Operating Limitations –
Because the Model 510 has high performance not typical of previous Part 23 type aircraft this SC
applied a range of additional requirements which are similar to FAR 25 and the Commuter Category.
Type Acceptance Report
Rev.0 : 27 March 2008 3 TAR 8/21B/14 – Cessna 510
No. 23-192-SC Full Authority Digital Engine Control System – This SC required an
evaluation of 23.1309(a) through (e) at Amendment 23-49 to the digital electronic engine control
systems to check for the possible effects, including environmental, on or by other aircraft systems.
No. 23-193-SC Turbofan Engines and Engine Location – With the engines mounted aft
on the fuselage of the Model 510 there is no early visual indication of an engine fire. Therefore a SC
was imposed to require a fire extinguishing system in each engine compartment with specific
extinguishing agent and container properties, discharge distribution and functional requirements.
(iii) Equivalent Level of Safety Findings:
ACE-05-8 §23.1305(c) and §23.1549 – Digital Indication of N2 and FF – The 510 has
digital only presentation of High-Pressure Turbine Rotor Speed N2 and Fuel Flow indication. The
N2 indicator is used for overspeed monitoring only, as engine speed is automatically controlled by
the FADEC system, while there is no FF limit. The indication locations are such that rate-of-change
information is readily discernible and they meet requirements for visibility, including lighting
conditions and vibration.
ACE-05-9 §23.1555(d)(1) – Usable Fuel Quantity Marking – The Model 510 fuel gauge
provides a direct reading of fuel quantity available calibrated in appropriate units for a turbofan
powered aircraft.
ACE-05-10 §23.807(e) – Ditching Emergency Exits – Cessna uses a “water barrier” at the
main cabin entry door to provide an emergency exit above the waterline on the LHS of the aircraft.
This was accepted, as on previous Citation models, because it is the secondary escape route and the
simplicity of the design is such that no training or experience is required to deploy the water barrier.
ACE-05-11 §23.841(b)(6) – Cabin Pressurization for High Altitude takeoff and
Landing Operations – The 510 is certified for operations from airports up to 14,000 feet
elevation. The rule requires a warning when cabin altitude exceeds 10,000 feet. To avoid nuisance
indications the system inhibits warnings under specific conditions for high altitude operations.
ACE-05-12 §23.1435(a)(2) – Hydraulic Pressure Indication – Cessna uses two EICAS
messages to provide information to the crew about the pressure in the hydraulic system in place of a
pressure gauge, in conjunction with associated Flight Manual procedures.
ACE-05-23 §23.1447(e) – Passenger Oxygen Dispensing Units – At cold temperatures
the passenger oxygen masks become stiff and will not unfold and fall from the dispensing unit
stowage box for presentation to the passengers. To ensure easily accessible emergency oxygen to
passengers in case of cabin decompression the 510 uses a streamer attached to the oxygen mask.
ACE-05-28 §23.841(a) – Cabin Pressurisation – Cabin altitude must not exceed 15,000
feet in the event of any probable failure or malfunction of the system. Because it is designed for high
altitude airport operations, there are circumstances where the 510 cabin altitude will briefly
overshoot the limit. This was accepted because this short exposure will not prevent the crew from
safely operating the aircraft or cause permanent physiological damage to the occupants.
ACE-06-03 §23.1545(b)(4) – Airspeed Indicator – The 510 has only a digital ASI display
which does not fully comply with flap operating range marking requirements. A digital display must
also provide equivalent sensory cues. The 510 display was accepted because the rolling scale and
number presentation, along with colour coding and flags, provide additional compensating factors.
(iv) Airworthiness Limitations:
See Maintenance Manual, Chapter Four
Type Acceptance Report
TAR 8/21B/14 – Cessna 510 4 Rev.0 : 27 March 2008
(3) Aircraft Noise and Engine Emission Standards:
(i) Environmental Standard:
The Model 510 has been certificated under FAR Part 34, including Amendments
34-1 through 34-3, and FAR Part 36, including Amendments 36-1 through 36-26.
(ii) Compliance Listing:
Cessna Dynamics Report No.D-510-231 – Model 510 – FAR 36 Noise Test Results
(Flyover – 73.9; Lateral – 85.0; Approach 86.0; Stage 4 Margin 26.1 EPNdB)
(4) Certification Compliance Listing:
Cessna Report AW-510-001 – Configuration and Continued Airworthiness Report
Cessna Report No. AW-510-002 – Model No. 510 – Master Compliance Checklist
Cessna Report No. PR-510-005 – Model No. 510 – Master Drawing List
Cessna Report No. S-510-1001 – Model No. 510 – Structural Substantiation
Cessna Engineering Flight Test Report No. FT510-12 – Avionics Systems
Cessna Report EL-510-402 – HIRF and Indirect Effects of Lightning Compliance
Cessna Report No. EV-510-101 – Model 510 – Oxygen System Compliance Report
Cessna Report No. C-510-99 – Model No. 510 – Structural Substantiation, Interiors
Cessna Report No. C-510-106 – Model 510 – Crashworthiness Evaluation, Interiors
(5) Flight Manual: FAA-Approved Airplane Flight Manual Citation Mustang – Serial
Number 510-0001 through -0004 Incorporating SL510-99-1 and
510-0005 and On – P/N 510FM – CAA Accepted as AIR 3020
(6) Operating Data for Aircraft and Engine:
(iii) Maintenance Manual:
Publication 510MM – Model 510 Maintenance Manual
Publication 510WD – Model 510 Wiring Diagram Manual
Publication 510SR – Model 510 Structural Repair Manual
Publication 510ND – Model 510 Nondestructive Testing Manual
Publication 510WB – Model 510 Weight and Balance Manual
Publication 510TE – Model 510 Illustrated Tool and Equipment Manual
Publication 510CM – Model 510 Component Maintenance Manual
(iv) Current service Information:
Model 510 Service Bulletins and Service Letters
(v) Illustrated Parts Catalogue:
Publication 510PC – Model 510 Illustrated Parts Catalogue
(7) Agreement from manufacturer to supply updates of data in (5), and (6):
CAA 2171 from Cessna Director of Airworthiness & Product Safety dated 05.10.07
(8) Other information:
Citation Mustang – Specification and Description – September 2006
Citation Mustang – Optional Equipment Selection Guide – June 2007 – Effective
for Aircraft to be Delivered in 2008 – Units 510-0053 and On
Publication 510OM – Citation Mustang Operating Manual
Type Acceptance Report
Rev.0 : 27 March 2008 5 TAR 8/21B/14 – Cessna 510
5. Additional New Zealand Requirements
Compliance with the retrospective airworthiness requirements of NZCAR Part 26 is a
prerequisite for the grant of a type acceptance certificate.
Civil Aviation Rules Part 26
Subpart B – Additional Airworthiness Requirements
Appendix B – All Aircraft
PARA: REQUIREMENT: MEANS OF COMPLIANCE:
B.1 Marking of Doors and Emergency Exits To be determined on an individual aircraft basis
B.2 Crew Protection Requirements – CAM 8 Appdx. B # .35 Not Applicable – Agricultural Aircraft only
Compliance with the following additional NZ operating requirements has been reviewed
and were found to be covered by either the original certification requirements or the basic
build standard of the aircraft, except as noted:
Civil Aviation Rules Part 91
Subpart F – Instrument and Equipment Requirements
PARA: REQUIREMENT: MEANS OF COMPLIANCE:
91.505 Seating and Restraints – Safety belt/Shoulder Harness FAR §23.785/ FAR §23.2
91.507 Pax Information Signs – Smoking, safety belts fastened Not Applicable – Less than 10 passenger seats
91.509
Min.
VFR
(1) ASI
(2) Machmeter
(3) Altimeter
(4) Magnetic Compass
(5) Fuel Contents
(6) Engine RPM
(7) Oil Pressure
FAR §23.1303(b)(1) *
FAR §23.1303(c)(2) *
FAR §23.1303(b)(2) *
FAR §23.1303(a)(3)) *
FAR §23.1305(a)(2) *
FAR §23.1305(c)(3) *
FAR §23.1305(a)(4) *
(8) Coolant Temp
(9) Oil Temperature
(10) Manifold Pressure
(11) Cylinder Head Temp.
(12) Flap Position
(13) U/c Position
(14) Ammeter/Voltmeter
Not Applicable – Turbojet
FAR §23.1305(a)(6) *
Not Applicable – Turbojet
Not Applicable – Turbojet
FAR §23.699 *
FAR §23.729(e) *
FAR §23.1351 (b)(6) *
91.511 Night VFR Instruments and Equipment * Fitted as Standard
91.513 VFR Communication Equipment * Fitted as Standard
91.517 IFR Instruments and Equipment * Fitted as Standard
91.519 IFR Communication and Navigation Equipment * Fitted as Standard
* Garmin G1000 Integrated Instrument and Avionics System has dual GDC74B Air Data Computers; dual GRS77 Attitude
Heading Reference Systems; Dual GMU44 magnetometers; dual GIA63W with VHF Nav/Comm and GPS; single KN63
DME; dual GMA1347D audio control panels; and GWX68 weather radar, Fitted as Standard.
Note: The Model 510 is approved for Day and Night VFR and IFR, and Flight Into Known Icing Conditions
RVSM – Model 510 is certificated and equipped as standard for RVSM Operations (See Flight Manual Page 2-21)
RNP/BRNAV – Model 510 is approved under FAA AC 20-138A to RNP5/BRNAV and RNP-1 (See AFM Page 2-30)
91.523
Emrgcy
Eqpmt.
(a) More than 9 pax - First Aid Kits/Fire Extinguishers
(b) More than 20 pax - Axe readily accessible to crew
(c) More than 61 pax - Portable Megaphones per Table 9
Not Applicable – Less than 10 passenger seats
Not Applicable – Less than 20 passenger seats
Not Applicable – Less than 61 passenger seats
91.529 ELT – TSO C91a after 1/4/97 – C126 after 22/11/07 Artex C406-N Fitted as Standard
91.531 Oxygen Indicators - Volume/Pressure/Delivery FAR §25.1441 and FAR §25.1443
91.535 Oxygen for Pressurised Aircraft
(1) Flight Crew Member On-Demand Mask; 15 min PBE
(2) 1 Set of Portable 15 min PBE
(3) Crew Member - Pax Oxygen Mask; Portable PBE 120l
(4) Spare Oxygen Masks/PBE
(5) Minimum Quantity Supplemental Oxygen
(6) Required Supplemental/Therapeutic Oxygen
Above FL250 - Quick-Donning Crew On-Demand Mask
- Supplemental O2 Masks for all Pax/Crew
- Supplemental Mask in Washroom/Toilet
Above FL300 - Total Outlets Exceed Pax by 10%
- Extra Units Uniformly Distributed
- Automatically Presented Above FL140
- Manual Means of Deploying Pax Masks
Maximum Operating Altitude is 41,000 ft.
(Model 510 Oxygen System is similar to the Model 525).
EROS MC10-16-101 TSO C89/99 Quick-donning pressure
demand masks are provided at each pilot seat;
Automatic dropout constant-flow TSO C64a oxygen masks
are provided in the cabin: Two double units above the club
seats and one single unit by the toilet.
Oxygen bottle contents displayed on cockpit gauge.
Cessna calculates a minimum quantity of 749 litres of
oxygen to meet the requirements of §91.535(a)(4) & (5).
Therefore OPTIONAL 40 cu. ft. bottle MUST BE FITTED.
To allow high altitude airport operations, pax oxygen masks
are only made available automatically at 14,800 ± 200 feet.
Exemption 8/EXE/40 against §91.535(d)(3) was granted.
91.541 SSR Transponder and Altitude Reporting Equipment Dual GTX33/D Mode S transponders Fitted as Standard
91.543 Altitude Alerting Device - Turbojet or Turbofan * Fitted as Standard
91.545 Assigned Altitude Indicator N/A – Altitude alerting device fitted
A.15 ELT Installation Requirements To be determined on an individual aircraft basis
Type Acceptance Report
TAR 8/21B/14 – Cessna 510 6 Rev.0 : 27 March 2008
Civil Aviation Rules Part 135
Subpart F – Instrument and Equipment Requirements
PARA: REQUIREMENT: MEANS OF COMPLIANCE:
135.355 Seating and Restraints – Shoulder harness flight-crew seats FAR §23.785/ FAR §23.2
135.357 Additional Instruments (Powerplant and Propeller) Certificated to FAR Part 23, including §23.1305
135.359 Night Flight Landing light, Pax compartment Operational requirement – Compliance as applicable
135.361 IFR Operations Speed, Alt, spare bulbs/fuses Operational requirement – Compliance as applicable
135.363 Emergency Equipment (Part 91.523 (a) and (b)) Operational requirement – Compliance as applicable
135.367 Cockpit Voice Recorder N/A – Only for 2-crew helicopters with more than 10 pax
135.369 Flight Data Recorder Not Applicable – Less than 10 passenger seats
135.371 Additional Attitude Indicator Fitted as Standard (Mid-Continent P/N S3100-432)
Attachments
The following documents form attachments to this report:
Photographs first-of-type example Cessna 510 s/n 510-054 ZK-MUS
Drawing 7000510 - Model 510 Three View and General Arrangement
Copy of FAA Type Certificate Data Sheet Number A00014WI
Sign off
…………………………………….. ……………………………...............
David Gill Checked – Peter Gill AWE3
Team Leader Airworthiness Date: 27 March 2008
Appendix 1
List of Type Accepted Variants:
Model: Applicant: CAA Work Request: Date Granted:
510 Cessna Aircraft Company 8/21B/14 27 March 2008

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march20042004

c的飞机呀 谢谢