Source: http://fsims.faa.gov/wdocs/fsb/c-510%20r1.htm
Timestamp: 2018-02-22 18:54:37
Document Index: 215107510

Matched Legal Cases: ['§ 91', '§ 135', '§ 61', '§ 135', '§ 1', '§ 61', '§ 61', '§ 61', '§ 61', '§ 61', '§ 61', '§ 61', '§ 23', '§ 23', '§ 23', '§ 135', '§ 91', '§ 97', '§ 91', '§ 135', '§ 91', '§ 61', '§ 61', '§ 61', '§ 142', '§ 141', '§ 61', '§ 142', '§ 135', '§ 135', 'art 23', 'art.\n10', 'art 91', '§23', '§23', 'art 23', '§91', '§91', 'art 135', '§135', '§135', '§25']

FSB Report Cessna CE-510
CE 510/510
RECORD of revision........................................................................................................... 3
1. PURPOSE AND APPLICABILITY........................................................................................ 4
2. PILOT TYPE RATING DETERMINATION........................................................................ 4
3. MASTER COMMON REQUIREMENTS........................................................................... 5
4. MASTER DIFFERENCE REQUIREMENTS...................................................................... 7
5. OPERATOR DIFFERENCE REQUIREMENTS................................................................. 7
6. FSB SPECIFICATIONS FOR TRAINING........................................................................... 8
7. FSB SPECIFICATIONS FOR Checking........................................................................ 10
8. FSB SPECIFICATIONS FOR CURRENCY....................................................................... 11
9. FSB SPECIFICATIONS FOR DEVICES OR SIMULATORS.......................................... 11
10. MISCELLANEOUS............................................................................................................ 12
11. AIRCRAFT REGULATORY COMPLIANCE.................................................................. 13
12. ALTERNATE MEANS OF COMPLIANCE TO THIS REPORT.................................. 13
APPENDIX 1 - EFB EVALUATION FOR G1000................................................................... 14
APPENDIX 2 - MDR TABLE.................................................................................................. 17
APPENDIX 3 - ODR TABLES................................................................................................. 18
APPENDIX 4 - AIRCRAFT REGULATORY COMPLIANCE CHECKLIST...................... 21
Number Section Pages Affected Date
Revision 1: Added Electronic Charts Evaluation and Synthetic Vision (SVS). Revised FSB report added: MDR Table, ODR Table, current FSB Template guidance.
Original: Original CE-510 FSB Report.
1.1 The purpose of this Flight Standardization Board (FSB) Report is to specify FAA training, checking and currency requirements applicable to flight crews operating the Cessna Aircraft Company Model 510 aircraft. This report provides guidance to operators who will be operating the Cessna Model 510 under Title 14 Code of Federal Regulations (14 CFR) § 91, Subpart K of 91, and 135.
1.2 The guidelines in this report apply to operations inspectors, principal operations inspectors (POI), training center program managers (TCPM), and aircrew program managers (APM). This report also applies to 14 CFR § 135 air carrier check airmen and instructors, airline transport pilots instructing in air transportation service, certificated flight instructors, aircrew program designees (APD), training center evaluators (TCE), and 14 CFR § 61, 135, 141 and 142 training providers.
1.3 This FSB Report has been written in accordance with the requirements of Advisory Circular (AC) 120-53A. The contents of this FSB report are applicable on the effective date of its final approval and will remain effective unless amended, superseded, or withdrawn by subsequent FSB determinations.
NOTE: The Cessna Model 510 meets the minimum equipment and instrumentation requirements of 14 CFR § 135 for operations conducted with a single pilot.
2.1 In accordance with 14 CFR § 1 and 61, the pilot type ratings for the Cessna Model 510 are designated as CE-510 or CE-510S. For the purposes of pilot certificate endorsement, the CE-510 and the CE-510S are two separate pilot type ratings. Each requires its own endorsement from a qualified instructor in the areas of operation required by the Practical Test Standards (PTS) and separate practical examinations.
2.1.1 CE-510
2.1.1.1 The CE-510 is awarded to pilots that successfully pass the requirements for a pilot type rating utilizing a second in command. Holders of a CE-510 pilot type rating may only conduct operations utilizing a second in command who meet the requirements of 14 CFR § 61.55. PIC's operating the CE-510 using an SIC are subject to the requirements of 14 CFR § 61.58, in that they must have successfully passed a proficiency check in an aircraft requiring a crew of two within the previous 12 months and a 14 CFR § 61.58 proficiency check utilizing an SIC in the CE-510 aircraft within the previous 24 months. This is in accordance with 14 CFR § 61.58 and the minimum crew requirement limitation in the FAA approved Flight Manual. Pilots may obtain a CE-510 pilot type rating in lieu of a 14 CFR § 61.58 proficiency check.
2.1.2 CE-510S
2.1.2.1 The CE-510S is awarded to pilots that successfully pass the requirements for a pilot type rating without a second in command. Holders of a CE-510S pilot type rating may conduct single pilot operations or utilize a second in command. Holders of the CE-510S pilot type rating that are required to utilize an SIC due to the fact that an SIC is required by the lack of equipment specified to be installed and operable by the AFM Limitations (i.e., Autopilot being inoperative) must also be qualified in accordance with 14 CFR § 61.58 requirements.
2.1.2.2 An applicant for a CE-510S type rating who already holds a CE-510 type rating must successfully complete a separate, entire practical examination in accordance with the appropriate Practical Test Standard (PTS) as a single pilot. Applicants awarded the CE-510S pilot type rating in this manner should be issued the CE-510S pilot type rating and retain the CE-510 type rating designation on their pilot certificate.
2.1.3 Second-in Command
2.1.3.1 The Second-in-Command Pilot Type Rating (CE-510 SIC Privileges Only) may be issued in accordance with 14 CFR § 61.55.
3. MASTER COMMON REQUIREMENTS (MCR’S)
3.1.1 The Cessna Aircraft Company Model 510 is a 14 CFR § 23 aircraft. Its maximum takeoff gross weight is 8,645 pounds. For 14 CFR § 23 Normal Category aircraft, the maximum takeoff gross weight is 12,500 pounds. Cessna was issued Special Conditions that require the CE-510 to meet Commuter category (14 CFR § 23) takeoff and landing performance requirements and systems requirements. Although not specifically required by 14 CFR § 135 or 14 CFR § 91, Subpart K, due to passenger capacity or aircraft weight, the aircraft is equipped with such equipment as a Terrain Avoidance and Warning System (TAWS), weather radar, and a Traffic Avoidance System which enhances the single pilot capability and situational awareness. See compliance checklist, Appendix 4.
3.1.2 The aircraft is equipped with Pratt and Whitney 615F engines that produce 1,460 pounds of thrust each. Maximum speed is 250 KIAS, up to 27,120 feet, and then Mmo of .63M. The aircraft has a maximum operating altitude of 41,000 feet. It has a maximum differential cabin pressure limit of 8.5 psi. The airplane is RVSM certified. The maximum seating capacity is 5 passengers when utilizing the copilot seat for a passenger seat with one qualified single pilot.
3.1.3 The Mustang avionics system is based on the Garmin G1000 integrated flight deck with independent airspeed, altitude and attitude standby displays. The G1000 integrated flight deck on the Citation Mustang panel includes the following major sub systems:
a) Dual 10.4 inch diagonal measure color flat-panel primary flight displays (PFD),
b) A 15 inch diagonal measure color flat-panel multi-function display (MFD),
c) Flight Management System (FMS),
d) Audio panel with internal marker beacon receiver and intercom control,
e) Dual integrated radio modules that provide WAAS-capable IFR oceanic-approved GPS; VHF navigation with ILS; and VHF communication with 16-watt transceivers (25 kHz and 8.33 kHz channel spacing),
f) Single Mode S Transponder with Traffic Information Service (TIS) capability,
g) Single Mode S Diversity Transponder with Traffic Information Service (TIS) capability, Dual Air Data Computer (ADC), Dual Attitude and Heading Reference System (AHRS), Crew alerting system (CAS), fuel, and electrical displays presented on the MFD, Datalink XM Weather Service,
h) Automatic Direction Finder (ADF) (optional) integrated into the G1000 System as display only (not coupled to flight director or autopilot),
i) Distance Measuring Equipment (DME) integrated into the G1000 System as display only (not coupled to flight director or autopilot),
j) Airborne Color Weather Radar System.
3.1.4 Other Model 510 systems are similar to the Model 525 series airplanes.
3.2 Procedure Knowledge
3.2.1 Landing Minima Category (14 CFR § 97.3) The following straight-in approach minima (based on Maximum Landing Weight (MLW) and 1.3 times Vso) for the CE-510 are as follows:
30 deg. 92 KIAS
3.2.2 For the purpose of determining circling approach minima, the minimums are based on the highest speed used during a circling maneuver. As depicted in the table below, the highest speed to be flown (speed category) during the circling maneuver must be used to determine the appropriate minimums. This will ensure that the aircraft will remain within the designated maneuver area and assure obstacle clearance.
Less than 91 Kts. (A)
91 to 120 Kts. (B)
121 to 140 Kts. (C)
141 to 165 Kts. (D)
Above 165 Kts (E)
3.2.3 Takeoff, Climb, Cruise, and Approach Profiles and Speed: The takeoff, climb, cruise and approach profiles and speeds for the CE-510 are very similar to the Model 525 Citation Jet with Model 510 speeds and rate of climb being slightly lower.
3.2.4 Abnormal and Emergency Procedures: Abnormal and emergency procedures are presented in the FAA Approved Pilot’s Abbreviated Checklist and Aircraft Flight Manual, and Garmin G1000 Integrated Flight Deck Pilot’s Guide for the Cessna Citation Mustang.
4.1 MDR’s are requirements applicable to crew qualification, which pertain to differences between variants of the same or related type. MDR requirements apply when differences between a base aircraft and a variant, or differences between two variants, affect flight crew knowledge, skills, or abilities related to flight safety at differences levels of Level A or greater. MDR Table is contained in Appendix 2.
5. OPERATOR DIFFERENCE REQUIREMENTS (ODRs)
5.1 ODR’s are operator specific requirements necessary to address differences between a base aircraft and one or more variants in a transition or differences training program that lists compliance methods relative to training, checking and currency. ODR tables contain design, maneuver and system difference tables. ODR Tables are contained in Appendix 3.
5.2 Difference Levels A through E in the ODR tables using the minimum training methods devices and equipment are described in the table below:
“HO” = Handout, Bulletins, Manual Revisions
“CBT” = Computer Based Training
“SU” = Stand-up Lectures
Maneuvers Devices
“FFS A-D” = Full Flight Simulators (level D or lower )
Simulator C or D, or Aircraft
NOTE: An “X” in an ODR table column indicates that any of the training methods for that level are acceptable. If a specific instruction method is specified in an ODR table column, it must be used. ODR checking and currency level definitions may be found in AC 120-53A.
5.3 ODR tables are an acceptable means to comply with MDR requirements based on those differences and the compliance methods shown. FSB recommended ODR tables are described in Appendix C.
6.1 Airman Experience: The provisions of this section apply to programs for experienced airmen (e.g. airmen who have previous turbine powered aircraft experience in 14 CFR § 91/135 operations, military, commuter or corporate pilots with turbine powered aircraft experience, etc.). For airmen not having such experience, additional requirements may be necessary, as determined by the POI, FSB, and AFS-200.
6.2 Ground training in the following subjects for the CE-510 is required:
b) Cockpit/Garmin G1000 Familiarization
c) Aircraft General Description (Interior/Exterior)
d) Review of the AFM and Operating Manuals
e) Lighting Systems
f) EICAS(Engine Indicating and Crew Alerting System)
g) Powerplants
h) Fire Protection System
i) Electrical System
j) Fuel System
k) Hydraulic System
l) Landing Gear
m) Power/Anti-skid Brake Systems
n) Flight Controls
o) Pneumatics
p) Air Conditioning System
q) Ice & Rain Protection Systems
r) Oxygen System
s) Pressurization System
t) Preflight Procedures
u) PFD and MFD Displays & Controls and Avionics Systems
v) Flight Management System (FMS)
w) Systems Integration Training
x) MMEL Procedures
y) Introduction to Performance
z) Weight & Balance Procedures
aa) Aircraft Performance Procedures and Limitations
bb) Automatic Flight Control System
cc) High Altitude Operations
dd) Electronic Flight Bag (EFB)
ee) Synthetic Vision System (SVS)
6.3 Particular emphasis should be placed upon Commuter category takeoff performance. The definitions of and the significance of: V1, Vr, and V2 should be thoroughly explained. The determination of maximum takeoff weight due to climb capability, obstacle clearance requirements, and brake energy limits should be thoroughly understood by the student. The student should understand the mandatory regulatory applicability of these weight limits to 14 CFR § 135 and 14 CFR § 91 operators, due to the certification special conditions and Airplane Flight Manual Limitations.
6.4 Programmed hours of ground training in approved training programs should comply with the national norms and threshold hours contained in FAA Order 8900.1.
6.5 Flight training for the CE-510 should focus on the following events or maneuvers:
a) Exterior inspection
d) Multiple approaches requiring reprogramming of approaches into the Garmin avionics system
e) Stalls to first indication of stall warning (stall warning horn)
f) No Flap Landing Procedures
g) Normal Procedures
h) Abnormal Procedures
i) Emergency Procedures to include an approach simulating using only Emergency power
j) Flight Operations in the G1000 Reversionary Modes
k) VMC and IMC approaches, with and without Synthetic Vision System (SVS) enabled
l) Engine failure, after V1 or during missed approach with and without Synthetic Vision System (SVS) enabled.
6.6 Programmed hours of flight instruction in approved training hours should comply with the national norms contained in FAA Order 8900.1.
6.7 The underlying objective in both flight and ground training is to train to proficiency.
7. FSB SPECIFCATIONS FOR CHECKING
7.1 All checking requirements should be administered in accordance with the FAA Airline Transport Pilot and Aircraft Type Rating Practical Test Standards (PTS), document number FAA-S-8081-5F, as amended.
7.1.1 Ground: Ground training should be concluded with a written exam covering aircraft systems. The Performance section of the ground training should include a practical examination prior to the conduct of the LOFT scenario. The exam should be completed to determine takeoff and landing performance based upon various airport conditions (i.e., effect of slope and obstacle clearance).
7.1.2 Flight: During checking administered in an aircraft, Inspectors should not use circuit breakers to simulate any system malfunctions. No flap landings should be accomplished and may be demonstrated to a landing. FAA handbook guidance regarding rejected landings only for Transport Category aircraft does not apply. Alternate gear extensions may be examined provided the nitrogen bottle is not used.
8.1 When MDR/ODR specifies Level B Currency, currency is maintained by operating the variant aircraft within the previous 180 days. Currency may be reestablished by a proficiency check in the variant aircraft or by completing applicable differences training requirements for the variant airplane.
8.2 When MDR/ODR specifies Level C Currency, currency is maintained by operating the variant aircraft through a complete flight cycle including an instrument approach procedure within the previous 90 days. Currency may be reestablished by completing a Line Check with a Line Check Airman, completion on a proficiency check in the variant aircraft or compliance with 14 CFR § 61.57(c) or (d) recent flight experience requirements in the variant airplane.
8.3 When MDR/ODR specifies Level D Currency, currency is maintained by operating the variant aircraft through 3 complete flight cycles (takeoff, departure, arrival, approach and landing) within the previous 90 days. Currency may be reestablished by completing a Line Check, completion of a Proficiency Check in the variant aircraft or compliance with 14 CFR § 61.57(c) or (d) recent flight experience requirements in the variant airplane.
8.4 Takeoffs and landings, either performed as a single pilot or as a crew of two, satisfy the recent flight experience (14 CFR § 61.57) required for either and/or both pilot type ratings, CE-510 and CE-510S.
9. FSB SPECIFICATIONS FOR DEVICES OR SIMULATORS
9.1 All requests for the use of training devices or flight simulators in an operator’s training program, or at a 14CFR § 142 approved training center, 14CFR § 141 approved school, or other training provider, should be addressed to the appropriate FSDO. Requests for device or simulator approval should be made through the POI. Guidance is available in AC 120-40B, AC 120-45A and FAA Order 8900.1. POI’s should seek additional assistance through the FAA’s National Simulator Program (NSP) Office.
9.2 The training, checking, and currency requirements of 14 CFR § 61, 91, Subpart K of 91 and 135, as well as the ATP/Type Rating PTS, allow partial or full credit in approved training devices and flight simulators. Cessna has partnered with a 14 CFR § 142 training provider for type rating training.
9.3 Level C training devices have characteristics that are typically part task trainers or FTD Level 2-5 per the following table listed in the section of Operator Difference Requirements (ODR) Tables.
10.1 PROVING TESTS – Proving tests, which may be required by an operator to comply with the requirements of 14 CFR § 135.145, should be conducted in accordance with FAA Order 8900.1.
10.2 FORWARD OBSERVER SEAT – A forward observer seat on or near the flight deck, equipped with a headset or speaker, is required to be provided for use by the Administrator during en route inspections by 14 CFR § 135.75 (b) and for the administration of flight tests leading to pilot certification or operating privileges. On small jet aircraft type certificated in accordance with 14 CFR § Part 23, there generally is no available space for the installation of a jump seat that will meet the intent of the applicable regulations. The right cockpit seat is the primary seat in the Cessna Model 510 that will substitute as a jump seat for the purposes of the 14CFR cited above. If the right pilot seat is occupied, an inspector will be required to sit in the nearest available seat in the cabin to perform en route inspections or to administer a flight check if communications, oxygen, adequate lighting and ventilation are available.
10.3 ELECTRONIC CHARTS-Two electronic chart applications have been evaluated: FliteCharts and ChartView. Reference Appendix 1 for Electronic Flight Bag (EFB) evaluation.
10.3.1 FliteCharts are an electronic display of the paper version of the National Aeronautical Charting Office procedure charts and provided by Garmin.
FliteCharts are:
a) Displayed on MFD
b) Have a 28 day revision cycle
c) Inoperative 180 days after chart expiration date
d) Not available outside the US
e) Subscription to the FliteChart service is required.
Note: FliteCharts do not have a moving display. It is an electronic display of the paper chart.
10.3.2 ChartView is the electronic version of Jeppesen terminal procedures charts.
ChartView is:
a) Displayed on MFD as moving map
b) Has a 14 day revision cycle
c) Inoperative 70 days after chart expiration date
10.3.3 Chart databases are available by subscription from Jeppesen, Inc.
Included charts are:
a) Arrivals (STAR)
b) Departure Procedures (DP)
c) Approaches
d) Airport Diagrams
e) NOTAMs
11. AIRCRAFT REGULATORY COMPLIANCE
11.1 The Aircraft Regulatory Compliance Checklist is of benefit to the FAA Certificate Holding District Office (CHDO) and assigned principal inspectors, because it identifies regulatory and operational requirements for which compliance has already been demonstrated to the FAA for a particular type aircraft or variant model. It is the responsibility of the CHDO to review compliance with FAA rules, policies and processes not covered by the Regulatory Compliance Checklist before the Cessna Model 510 is introduced into commercial service. This checklist found in Appendix 4.
12.1 The FSB Chairman should be consulted by the POI when alternate means of compliance other than those in this report are proposed. Alternate means of compliance must be approved by AFS-1. Analysis, demonstrations, proof of concept testing, or other evidence may be required.
Electronic Flight Bag (EFB) Operational Evaluation for Cessna Model 510 Aircraft
2. Suitability Determination
5. Display and Reflectivity
6. Database Revisions
7. Specifications for Training
8. Specifications for Checking
9. Specifications for Currency
10. Environmental Testing (HIRF, EMI)
11. Continued Airworthiness
12. List of Affected Document
The following is provided for the benefit of FAA Principal Inspectors and aircraft operators for their use in determining the acceptance of EFB applications. As described in AC 120-76A, Guidelines for the Certification, Airworthiness, and Operational Approval of Electronic Flight Bags Computing Devices, the G1000 electronic charts are certified Class 3 EFB Hardware and Type C applications. Class 3 hardware is installed equipment and requires AIR involvement and AEG involvement. Applications are classified as Type C due to interaction of the Electronic Charts with the aircraft. The charts can be manipulated (i.e. zoomed, scrolled, etc.) as Type B, but are classified Type C because aircraft present position is provided on the installed display on the airport depictions and charts.
The EFB evaluation determined chart display functions to be suitable as one source for electronic display of airport diagrams, approach plates, arrival procedures, and departure procedures. Since chart information cannot be displayed while on emergency power, or in the event of certain avionics failures, a suitable backup is required. Approved airplane flight manual provides operating limitations for the installation.
The G1000 includes “FliteChart” and optional “ChartView” electronic charts. A specific system description for the system configuration appropriate to the installation is available in the approved Airplane Flight Manual, and Garmin G1000 Integrated Flight Deck Pilot’s Guide for the Cessna Citation Mustang (Model 510).
EFB applications are displayed on the Multi-function Display and have been certified as part of the type design.
The EFB has been evaluated as part of the type design.
The database currency requirements are specified in the approved Airplane Flight Manual, and Garmin G1000 Integrated Flight Deck Pilot’s Guide for the Cessna Citation Mustang (Model 510).
As a minimum, the crew should use the FMS to flight plan and the EFB electronic chart functions to display the airport depiction charts, SID’s, Arrival Procedures, and approach charts. Pilots should master the weather functions to obtain METARS and TAF’s for origin, destination, and alternate, airports if XM weather functions are enabled.
8. Specification for Checking
Recommended tasks include demonstrating competency in using the FMS to integrate use of the electronic chart functions to display departures, arrivals, and approaches, and utilizing the graphical weather functions if XM weather functions are enabled.
9. Specification for Currency
Currency level is variable as set in MDR table. If level C currency is indicated by MDR table, recommended tasks include demonstrating competency in using the FMS to integrate use of the electronic chart functions to display departures, arrivals, and approaches, and utilizing the graphical functions if XM weather functions are enabled.
Intensity Radiated Fields and Indirect Effects of Lightning for system were tested per High Intensity Radiated Fields (HIRF) and Indirect Effects of Lightning Test Procedure. The system meets Certification Basis requirements and special conditions for High Intensity Radiated Fields and Indirect Effects of Lightning.
Instructions for Continued Airworthiness for the system are addressed in accordance with aircraft certification requirements and available through normal ICA distribution processes.
The following is a list of Procedures, Documents and Affected Manuals concerning Operational Approval of G1000 electronic charts for use as an Electronic Flight Bag:
• Airplane Flight Manual (AFM)
• Garmin G1000 Integrated Flight Deck Pilot’s Guide for the Cessna Citation Mustang (Model 510)
• Flight Crew Training Program
• Training Courseware (Flight Crew, Maintenance Personnel, Operations Personnel)
• Company Maintenance Procedures
• Data Delivery and Management Procedures
• EFB Configuration Control Procedures
CE-510***
CE-510 w/Charts**
CE-510 w/SVS enabled
A/A/B*
w/Charts**
w/SVS enabled
Notes: * Differences to account for optional equipment.
** Either ChartView or FliteCharts
*** Both CE-510 and CE-510S
Sample ODR Tables available thru Kansas City AEG
CE-510 (G1000) TO CE-510 (G1000 w/Charts) DIFFERENCES – GENERAL (Sample)
Base Aircraft: CE-510 (G1000)
Difference Aircraft: CE-510 (G1000 w/Charts)
Checking / Currency
FLT CHK
Instrument Display (MFD)
CE-510 (G1000 w/Charts)
FliteCharts are the electronic display of the National Aeronautical Charting Office procedure charts. FliteCharts do not have a moving display. It is an electronic display of the paper chart. Charts only on MFD.
ChartView is the electronic version of Jeppesen terminal procedures charts. Displayed as moving map only on MFD.
CE-510 (G1000 w/Charts) TO CE-510 (G1000) DIFFERENCES – GENERAL (Sample)
Base Aircraft: CE-510 (G1000 w/Charts)
Difference Aircraft: CE-510 (G1000)
CE-510 (G1000)
CE-510 (G1000) TO CE-510 (G1000 w/Synthetic Vision (SVS)) DIFFERENCES – GENERAL
Difference Aircraft: CE-510 (G1000 w/Synthetic Vision (SVS))
Instrument Display (PFD)
CE-510 (G1000 w/SVS)
Single-Cue Command Bars only.
Attitude Indicator pitch scaling is reduced from 200 up and 150 down to 100 up and 7.50 down.
Flight Path Marker indicates the actual flight path (track) whereas the aircraft symbol indicates aircraft heading. White zero pitch line across the display may not align with the terrain horizon. Terrain display is intended for situational awareness only.
CE-510 (G1000 w/Synthetic Vision (SVS)) TO CE-510 (G1000) DIFFERENCES – GENERAL
Base Aircraft: CE-510 (G1000 w/Synthetic Vision (SVS))
CE-510 (G1000 w/Charts) TO CE-510 (G1000 w/Synthetic Vision (SVS)) DIFFERENCES – GENERAL
CE-510 (G1000 w/SVS) TO CE-510 (G1000 w/Charts) DIFFERENCES – GENERAL (Sample)
CE-510 OPERATING RULE COMPLIANCE CHECKLIST
2.0 14 CFR 91 – GENERAL OPERATING AND FLIGHT RULES
TABLE 2-1 SUBPART A – GENERAL
14 CFR Part 91 Section
Equipment STD/OPT
Cessna Compliance & P/N Information
DOA Approved AFM
Fireproof Plate Reference drawing 7005510-1 Model 510 Maintenance Manual Chapter 4 will list life limited parts by serial number and part number. All life limited parts are placarded with serial number and part number.
TABLE 2-2 SUBPART B – FLIGHT RULES
91.191(a)
Model 510 is not approved for category II or category III operations.
91.191(b)
91.191(c)
TABLE 2-3 SUBPART C – EQUIPMENT, INSTRUMENTS, AND CERTIFICATE REQUIREMENTS
Cessna issues AW certificate upon closure of all engineering and certifying documents are released and approved.
In order to appropriately identify per 91.9 (c) US Registered aircraft, Cessna, fills out AC Form 8050-1 and files necessary documents with the FAA If the aircraft is foreign registered it is the operator’s responsibility to register the aircraft with the Foreign Authorities
Operator’s Responsibility. Cessna provides storage location for certificate.
Not applicable to Model 510. Fuel tanks are located in the wing bays.
Reference: Cessna report D-510-231 “FAR 36 TEST RESULTS”
Airspeed, Altitude and Heading information are displayed via the Garmin G1000 avionics package on the Pilot and Copilot’s Primary Flight Displays (also with MFD in reversion) in accordance with 14 CFR 23.1323. GDU1040A, P/N: 011-00916-00 qty (2); GDC74B, P/N: 011-01110-00 qty (2); GRS77, P/N: 011-00868-10 qty (2) A third airspeed display (P/N 261440-1143) is installed as standard equipment in the center panel of the aircraft.
Airspeed, Altitude and Heading information are displayed via the Garmin G1000 avionics package on the Pilot and Copilot’s Primary Flight Displays (also with MFD in reversion) in accordance with 14 CFR 23.1303 and 23.1325. GDU1040A, P/N: 011-00916-00 qty (2); GDC74B, P/N: 011-01110-00 qty (2); GRS77, P/N: 011-00868-10 qty (2) A standby altimeter (P/N 162350-1161) is also installed.
Airspeed, Altitude and Heading information are displayed via the Garmin G1000 avionics package on the Pilot and Copilot’s Primary Flight Displays (also with MFD in reversion). GDU1040A, P/N: 011-00916-00 qty (2); GDC74B, P/N: 011-01110-00 qty (2); GRS77, P/N: 011-00868-10 qty (2) A magnetic compass (P/N C66501-0102) is installed in accordance with 14 CFR 23.1303 and 23.1327.
Tachometer, Oil Pressure, Oil Temperature, Manifold Pressure and Fuel Quantity information is displayed on the Multifunction Display of the Multi-Function Display (MFD) of the Garmin G1000 system. GDU1500, P/N: 011-1108-00 qty (1)
Not applicable to Model 510 aircraft, engines are not liquid cooled.
Not applicable to Model 510 aircraft
Model 510 aircraft incorporate landing gear panels that include status indicators for each landing gear.
Model 510 aircraft are equipped with anti-collision lighting (P/Ns 9912679-1, -2) per 14 CFR 23.1401.
All seats certified for taxi, t/o, and landing are equipped with three-point restraint systems (shoulder harness and lap belt) that is designed with metal-to-metal latching buckle. The restraint system was certified by test to protect the occupants from serious head injury when exposed to inertia forces prescribed by §23.561(b)(2).
All seats certified for taxi, takeoff, and landing are equipped with three-point restraint systems (shoulder harness and lap belt) that is designed with metal-to-metal latching buckle. The restraint system was certified by test to protect the occupants from serious head injury when exposed to inertia forces prescribed by §23.561(b)(2).
C406N Three Frequency ELT Main Assy, P/N: 453-5060 qty (1), Buzzer, P/N: 130-4004 qty (1)
Model 510 is not a rotorcraft.
See response to 91.205(b)
Model 510 aircraft are equipped with two landing lights (P/N 9912677-2).
Model 510 aircraft have two engine driven 9KW generators (P/N 9912676-1) and a 28 AH battery (P/N RG-390E). Adequacy of electrical power is addressed in report EL-510­200
Model 510 aircraft have no fuses that require replacement in flight.
See response to 91.205(b) and (c).
Communication, Navigation, DME, and optional ADF Frequency Tuning all reside on the Pilot and Copilot’s Primary Flight Displays. Each GIA63W contains a Communication Transceiver and Navigation Receiver. VHF, DME, and optional ADF Navigation information are all displayed on the Pilot and Copilot’s Primary Flight Displays (also with MFD in reversion). GDU1040A, P/N: 011-00916-00 qty (2); GIA63W, P/N: 011-1105-00 qty (2); KN63, P/N: 066-01070-0001
P/N: 011-00916-00 qty (2); GIA63W, P/N: 011-1105-00 qty (2); KN63, P/N: 066-01070-0001 qty (1); RA3502 optional ADF, P/N: 013-00166-00 (qty 1), RMI Converter, P/N: 013-00167-00
Rate-of-turn, Slip-Skid, Pitch and Bank, and Direction Indications are all displayed on the Pilot and Copilot’s Primary Flight Displays. A Standby Attitude Indicator is also installed as an isolated third Attitude source GDU1040A, P/N: 011-00916-00 qty (2); GRS77, P/N: 011-00868-10 qty (2) Standby ATT Indicator P/N: 4200-21 qty (1)
Rate-of-turn, Slip-Skid, Pitch and Bank, and Direction Indications are all displayed on the Pilot and CP’s Primary Flight Displays. A Standby Attitude Indicator is also installed as an isolated third Attitude source GDU1040A, P/N: 011-00916-00 qty (2); GRS77, P/N: 011-00868-10 qty (2) Standby ATT Indicator P/N: 4200-21 qty (1)
Rate-of-turn, Slip-Skid, Pitch and Bank, Altitude, and Direction Indications are all displayed on the Pilot and Copilot’s Primary Flight Displays. A Standby Attitude Indicator is also installed as an isolated third Attitude source. A Standby Altitude Indicator is installed as a third display of Altitude. The Standby Altimeter is connected to the Pilot’s Pitot-Static System. GDC74B, P/N: 011-01110-00 qty (2). Standby ALT Indicator P/N: 162350-1161 qty (1)
A digital clock displaying hours, minutes and seconds is available on the lower right-hand corner of the Pilot and Copilot’s Primary Flight Displays.
Model 510 aircraft have two separate engine driven 9KW (P/N 9912676-1) generators and a 28 AH battery (P/N RG­390E). l
DME Frequency Tuning and Navigation Information are both displayed on the Pilot and Copilot’s Primary Flight Displays. GDU1040A, P/N: 011-00916-00 qty (2); KN63, P/N: 066-01070-0001 qty (1).
C406N Three Frequency ELT Main Assy, P/N: 453-5060 qty (1), Buzzer, P/N: 130-4004 qty (1) TSO-C126 (Type AF)
C406N Three Frequency ELT installed as Standard equipment on the Model 510 airplane
Passenger masks are located above the aisle in the cabin overhead. Crew masks are located over their outboard shoulder on the divider panel. The oxygen bottle/regulator is located under the RH nose baggage compartment. The regulator can be turned on/off with a pull cable on the crew panel. Passengers: Avox Passenger Mask Assy 9919073-1, 9919073-2 Crew: Eros Crew Mask Assy 9914067-41 Bottle/Regulator Assy: BE 4441073-022 (STD), 4441073-040 (OPT)
Operator Responsibility Note: Operator is to provide MEL for his chosen operations. Cessna will submit to FAA a MMEL for approval. Reference: FAA Approved MMEL
91.213(d)(1)
DOA Approved AFM Reference: Cessna Flight manual 510FM-00
GTX33D, P/N: 011-00779-01 qty (1), TSO-C112 (CLASS 2A) GTX33, P/N: 011-00779-10 qty (1), TSO-C112 (CLASS 2A
Transponders: GTX33D, P/N: 011-00779-01 qty (1), TSO-C112 (CLASS 2A) GTX33, P/N: 011-00779-10 qty (1), TSO-C112 (CLASS 2A ADC: GDC74B, P/N: 011-01110-00 qty (2).
GTX33D, P/N: 011-00779-01 qty (1), TSO-C112 (CLASS 2A) GTX33, P/N: 011-00779-10 qty (1)
GDC74B, P/N: 011-01110-00 qty (2). TSO-C106
GDU1040A, P/N: 011-00916-00 qty (2);GDC74B, P/N: 011-01110-00 qty (2);GIA63W, P/N: 011-1105-00 qty (2);
Standard TIS system GTX33D, P/N: 011-00779-01 qty (1) GTX33, P/N: 011-00779-10 qty (1) GDU1040A, P/N: 011-00916-00 qty (2) GDC74B, P/N: 011-01110-00 qty (2) Optional TAS system KTA870, P/N: 066-01152­0101 qty (1), Config Module, P/N: 071-00112-0200 qty (1) GDU1040A, P/N: 011-00916-00 qty (2) GDC74B, P/N: 011-01110-00 qty (2)
Class B TAWS system is standard equipment on Model 510 although it is not required. TAWS functionality resides in each of the three displays and utilizes GPS altitude. GDU1040A, P/N: 011-00916-00 qty (2) GDU1500, P/N: 011-1108-00 qty (1) GIA63W, P/N: 011-1105-00 qty (2) TSO-C151b.
Class B TAWS system is standard equipment on Model 510 although it is not required. TAWS functionality resides in each of the three displays and utilizes GPS altitude. GDU1040A, P/N: 011-00916-00 qty (2) GDU1500, P/N: 011-1108-00 qty (1) GIA63W, P/N: 011-1105-00 qty (2) TSO-C151b
Model 510 is not designed or configured for parachuting or firefighting operations.
TABLE 2-4 SUBPART E – MAINTENANCE, PREVENTIVE MAINTENANCE, AND ALTERATIONS
Not applicable to Model 510.
Cessna will provide operators with a single approved inspection program at time of aircraft delivery. Inspection information will be in Ch 5, sec 10 of the Model 510 Maint Manual, per ATA specification 2200. Maint Manual Ch 4 will list life limited parts by serial number and part number. All life limited parts are placarded with serial number and part number.
Operator Responsibility Cessna will provide operators with a single approved inspection program at time of aircraft delivery. Inspection information will be in Chapter 5, section 10 of the Model 510 Maintenance Manual, per ATA specification 2200.
Reference: Garmin Installation Manual Garmin Documents Minimum Performance Specifications GDC 74A and GDC 74B, P/N: 004-00139-00. GTX330/33 Mode S Transponder Minimum Performance Specification, P/N: 004-00099-00.
DOA Approved AFM for RVSM limits
TABLE 2-5 SUBPART F – LARGE AND TURBINE POWERED MULTI-ENGINED AIRPLANES AND FRACTIONAL OWNERSHIP PROGRAM AIRCRAFT
Paper charts will still be required in the cockpit, as the Model 510 will NOT be certified as a paperless cockpit. Flashlight provided.
Checklist provided as std. (3) and (4) are operator responsibility, (5) provided in AFM and checklist performance.
DOA Approved Checklist Reference: Cessna Abbreviated Checklist 510CL-00
Operator Responsibility Note: Paper charts will still be required in the cockpit, as the Model 510 will NOT be certified as a paperless cockpit
Operator Responsibility Over water survival gear is not provided as type design or option on this aircraft.
Radio equipment for overwater operations.
GDU1040A, P/N: 011-00916-00 qty (2) GIA63W, P/N: 011-1105-00 qty (2) GMA1347D, P/N: 011-01257-00 qty (2) KN63, P/N: 066-01070-0001 qty (1); RA3502 optional ADF, P/N: 013-00166-00 (qty 1), RMI Converter, P/N: 013-00167-00 Hand MIC, P/N: 63333-008 qty (1) Headsets, P/N: 301317-000 qty (2) Cockpit Speakers, P/N: EN4S-4FR qty (2) Optional High Frequency (HF), KPA1052 Power Amp P/N: 064-01072-0101 qty (1), KRX1053 Receiver/Exciter P/N: 064-01073-0101 qty (1), KAC1052 Ant Coupler P/N: 064-01074-0101, HF Ctrl Unit P/N: 071-01605-0201 qty (1). Communication, Navigation, DME, and optional ADF Frequency Tuning all reside on the Pilot and Copilot’s Primary Flight Displays. Each GIA63W contains a Communication Transceiver, Navigation Receiver, and GPS Receiver. VHF, DME, optional ADF, and GPS Navigation information are all displayed on the Pilot and Copilot’s Primary Flight Displays (also with MFD in reversion).
GDU1040A, P/N: 011-00916-00 qty (2) A Communication Transceiver, Navigation Receiver and a GPS Receiver each reside within the GIA63W. Dual GIA63Ws, P/N: 011-1105-00 qty (2), are installed in the Model 510 airplane. On-side and Off-side Communication
GDU1040A, P/N: 011-00916-00 qty (2) A Communication Transceiver, Navigation Receiver and a GPS Receiver each reside within the GIA63W. Dual GIA63Ws, P/N: 011-1105-00 qty (2), are installed in the Model 510 airplane. On-side and Off-side Communication and Navigation Frequency Tuning and Display are capable on the Pilot and Copilot’s Primary Flight Displays. Dual GMA1347D, P/N: 011-01257-00 qty (2)Audio Panels are installed in the Model 510 airplane and are capable of On-side and Off-side Communication transmission and reception, and Navigation reception.
Reference 91.511(a) for Cessna Compliance and P/N Information.
Operator Responsibility. Inspection is up to the Operator. The emergency equipment that is required to be accessible to the crew will be located in reach of the crew. Location and method of operation will be indicated as required.
The installed fire extinguisher is accessible from both crew and passenger compartments.
Not applicable to Model 510. Model 510 has less than 19 passengers.
Not applicable to Model 510. Model 510 has less than 60 passengers.
Model 510 aircraft incorporate a manually controlled “passenger safety switch which controls the no smoking and seat belt signs No smoking fasten seat belt signs are provided
No passenger address system is installed.
Operator Responsibility Passenger Address System not installed. Cessna provides a passenger briefing card.
Although this requirement is not applicable for the Model 510, each seat is equipped with three-point restraint systems that is designed and certified to the inertia load factors of the aircraft
91.525(a)
91.525(b)
Model 510 has no cargo compartment areas
91.527(b)
The Model 510 ice protection systems will meet the requirements of SFAR 23 Section 34. The Model 510 will be certified for flight in known icing conditions.
91.527(c)
The Model 510 will not be approved for flight into known or forecast severe icing conditions.
91.527(d)
91.531(a)
DOA Approved AFM limitations.
91.531(b)
91.531(c)
DOA Approved AFM limitations, PIC type rating will specify single pilot or crew.
91.531(d)
Fully equipped second crew seat is standard equipment on this aircraft.
TABLE 2-6 SUBPART G – ADDITIONAL EQUIPMENT AND OPERATING REQUIREMENTS FOR LARGE AND TRANSPORT CATEGORY AIRCRAFT
Not required although Model 510 aircraft are equipped with an aural warning unit (P/N 7014118-5) that’s includes a speed warning.
91.605(a)
Model 510 is not a transport category aircraft.
91.605(b)
Not applicable to Model 510. Model 510 will not provide provisions for clearway performance and will not provide clearway data.
91.605(c)
Not applicable to Model 510. Model 510 will comply with part 23 commuter category for takeoff performance.
Not applicable to Model 510. Model 510 does not include cockpit voice or flight recorders or the provisions for recorders.
Not applicable to Model 510. There are no reqmtsfor a cockpit voice or flight recorder. Therefore provisions for Recorder Inop Equipment do not apply.
Model 510 does not seat 10 passengers.
A flight recorder is not required for the Model 510, due to 4 passenger seating configuration.
The Model 510 airplane has a passenger-seating configuration of 4 passengers.
A cockpit voice recorder is not req’d for the Model 510, due to 4 pax seating configuration.
A fl recorder and CVR are not required for the Model 510, due to 4 pax seating configuration.
Not Applicable to Model 510
TABLE 2-7 SUBPART K – FRACTIONAL OWNERSHIP OPERATIONS
DOA Approved Checklist. Reference: Cessna Checklist 510CL-00
Operator Responsibility Cessna will not certify wet landing performance data.
Use 115 % of runway length required.
Aircraft proving and validation tests
91.1041(b)
Model 510 has fewer than 30 passenger seats.
91.1045 (b)(1)
Model 510 seats less than 6 passengers.
91.1045 (b)(2)
Model 510 seats less than 10 passengers.
91.1045 (b)(3)
TAWS functionality resides in each of the three G1000 displays and utilizes GPS altitude. GDU1040A, P/N: 011-00916-00 qty (2) GDU1500, P/N: 011-1108-00 qty (1) GIA63W, P/N: 011-1105-00 qty (2) TSO-C151b
91.1045 (b)(4)
Although not required, Model 510 has a standard TIS system and an optional TAS system. Standard TIS functionality included in Transponders. GTX33D, P/N: 011-00779-01 qty (1) GTX33, P/N: 011-00779-10 qty (1) GDU1040A, P/N: 011-00916-00 qty (2) GDC74B, P/N: 011-01110-00 qty (2) Optional TAS System KTA870, P/N: 066-01152-0101 qty (1), Config Module, P/N: 071-00112-0200 qty (1) GDU1040A, P/N: 011-00916-00 qty (2) GDC74B, P/N: 011-01110-00 qty (2)
91.1045 (b)(5)
On board weather radar and optional XM satellite weather are standard in the G1000 system. GDU1500, P/N: 011-1108-00 qty (1) GWX68, P/N: 011-00883-20 qty (1) GDL69A, P/N: 011-00987-00 qty (1). Note: XM Graphical Weather is not certified for in-flight navigation. It is intended to be utilized for flight trip planning ONLY.
FAA/EASA approved MMEL will be provided to enable operator to assemble a MEL
North Atlantic Track (NAT) Minimum Navigational Performance Specification (MNPS) Airspace (as defined in AC91-49 and AC91-70) – Provided that the proper documentation and approval is obtained. Two FMS’s are required to be installed, Gander Oceanic Control Area, and the western boundary of New York Oceanic Control Area, excluding the areas west of 60 degrees west and south of 38 degrees 30 minutes north. Section 2 The navigation performance capability required for aircraft to be operated in the airspace defined in section 1 of this appendix is as follows: (a) The standard deviation of lateral track errors shall be less than 6.3 NM (11.7 Km). Standard deviation is a statistical measure of data about a mean value. The mean is zero nautical miles. The overall form of data is such that the plus and minus 1 standard deviation about the mean encompasses approximately 68 percent of the data and plus or minus 2 deviations encompasses approximately 95 percent. (b) The proportion of the total flight time spent by aircraft 30 NM (55.6 Km) or more off the cleared track shall be less than 5.3×10−4 (less than 1 hour in 1,887 flight hours). (c) The proportion of the total flight time spent by aircraft between 50 NM and 70 NM (92.6 Km and 129.6 Km) off the cleared track shall be less than 13 × 10−5 (less than 1 hour in 7,693 flight hours.) Section 3 Air traffic control (ATC) may authorize an aircraft operator to deviate from the requirements of §91.705 for a specific flight if, at the time of flight plan filing for that flight, ATC determines that the aircraft may be provided appropriate separation and that the flight will not interfere with, or impose a burden upon, the operations of other aircraft which meet the requirements of §91.705.
DOA Approved AFM limitations group approval. . GDU1040A, P/N: 011-00916-00 qty (2); GDC74B, P/N: 011-01110-00 qty (2); GRS77, P/N: 011-00868-10 qty (2) GIA63W, P/N: 011-1105-00 qty (2) GTX33D, P/N: 011-00779-01 qty (1) GTX33, P/N: 011-00779-10 qty (1) GMA1347D, P/N: 011-01257-00 qty (2) GMC710, P/N: 011-01020-00 qty (1) GSA81, P/N: 011-00878-00 qty (2) GSA80, P/N: 011-00877-00 qty (2) GSM85A, P/N: 011-01436-A0 qty (1) GSM85A, P/N: 011-01436-A1 qty (1) GSM85A, P/N: 011-01436-A2 qty (1) GSM85A, P/N; 011-01436-A3 qty (1) Pitot-Static Installation P/N: 7014150-1 XPDR Antenna, P/N: 610-611-14 qty (3) GTP59, P/N: 011-00978-00 qty (2) GMU44, P/N: 011-00870-00 qty (2)
TABLE 3-1 SUBPART A – GENERAL
14 CFR Part 135 Section
135.21(e)
135.21(f)
135.21(h)
TABLE 3-2 SUBPART B – FLIGHT OPERATIONS
135.75(b)
Either aft or forward facing passenger seats are considered satisfactory and available on Model 510.
Aft facing seat better.
135.76(b)
DOA Approved AFM and Checklist. Reference: Cessna AFM 510FM-00 and Checklist 510CL-00 Note: Paper charts will still be required in the cockpit, as the Model 510 will NOT be certified as a paperless cockpit.
135.83(b)
135.83(c)
Autopilot: Minimum altitudes for use.
135.93(a)
DOA Approved AFM Airplane Limitations. Reference: Cessna AFM 510FM-00. Certification rules no longer require AFM to specify loss, but does specify minimum use height
AFM Minimum Use Height for Takeoff, Climb, Enroute and Descent is 1000 feet AGL.
135.93(b)
DOA Approved AFM Airplane Limitations. Reference: Cessna AFM 510FM-00 Note: Certification rules no longer require AFM to specify loss, but it does specify minimum use height.
135.93(c)
DOA Approved AFM Airplane Limitations. Reference: Cessna AFM
AFM specifies 200 feet AGL minimum use height
135.93(d)
Not applicable to Model 510. The autopilot on Model 510 is not approved for takeoff or landing.
135.93(e)
135.127(a)
Lighted signs provided
135.127(b)
135.127(c)
Model 510 does not have a lavatory.
135.127(d)
135.127(e)
Model 510 does not have a smoke detector requirement.
135.127(f)
Not applicable to Model 510. §135.177(a)(3) is required for aircraft with more than 19 seats, Model 510 only has 5 passenger seats. Per §135.127(a), Model 510 “No Smoking” placards comply with §25.1541.
135.127(g)
135.127(h)
135.128(a)
The Model 510 has crew and cabin passenger seats that are equipped with three-point restraint systems that are approved for use during taxi, takeoff and landing. The number of persons onboard the aircraft occupying the available seats shall not exceed the maximum passenger configuration approved for the aircraft. Passenger briefing cards are supplied to provide instructions for holding a child that does not occupy an approved child seat or restraining device. It is the operator responsibility to ensure that any child restraint or child seat that is used onboard the aircraft conforms to the
requirements defined in this section. It is also the operator’s responsibility to ensure that the child seat is installed and secured properly to the seat.
135.128(b)
Operator’s responsibility. Passenger briefing cards are supplied to provide instructions for holding a child that does not occupy an approved child seat or restraining device. It is the operator’s responsibility to ensure that any child restraint or child seat that is used onboard the aircraft conforms to the requirements defined in this section. It is also the operator’s responsibility to ensure that the child seat is installed and secured properly to the seat.
CHDO to determine
135.129(d)
Operator Responsibility Note: Passenger Briefing cards will be provided
135.129(e)
Operator Responsibility Operator is to provide instructions/cards in appropriate language for intended operations.
TABLE 3-3 SUBPART C – AIRCRAFT AND EQUIPMENT
GTX33D, P/N: 011-00779-01 qty (1), TSO-C112 (CLASS 2A) GTX33, P/N: 011-00779-10 qty (1), TSO-C112 (CLASS 2A)
Dual Avionics controls (Pilot and Copilot) are installed as standard equipment in the Model 510 airplane and are as follows: PTT, Pitch Trim, AP CWS, and XPDR Ident.
GDU1040A, P/N: 011-00916-00 qty (2); GDC74B, P/N: 011-01110-00 qty (2)
Model 510 is a turbine powered aircraft.
Model 510 is equipped with bleed air engine anti-ice.
The Model 510 airplane has a passenger-seating configuration of 4 passenger seats.
135.151(e)
135.153(a)
This is not required for Model 510; class B TAWS functionality resides in each of the three displays and utilizes GPS alt. GDU1040A, P/N: 011-00916-00 qty (2) GDU1500, P/N: 011-1108 - 00 qty (1) GIA63W, P/N:011-1105 -00 qty (2) TSO-C151b
135.153(c)
DOA Approved AFM Reference: Cessna AFM
135.154(a)
This is not required for Model 510, however class B TAWS functionality resides in each of the three displays and utilizes GPS altitude. GDU1040A, P/N: 011-00916-00 qty (2) GDU1500, P/N: 011-1108-00 qty (1) GIA63W, P/N: 011-1105-00 qty (2) TSO-C151b
135.154(b)
135.154(c)
Halon fire extinguisher provided.
135.155(b)
Not Applicable to Model 510. Model 510 has less than 10 seats. Same extinguisher available to crew is also available in passenger compartment.
Passenger masks are located above the aisle in the cabin overhead. Crew masks are located over their outboard shoulder on the divider panel. The oxygen bottle/regulator is located under the RH nose baggage compartment. The regulator can be turned on/off with a pull cable on the crew panel. Reference: Passengers: Avox Passenger Mask Assy 9919073-1, 9919073-2 Crew: Eros Crew Mask Assy 9914067-41 Bottle/Regulator Assy: BE 4441073-022 (STD), 4441073-040 (OPT)
135.157(b)
compartment. The regulator can be turned on/off with a pull cable on the crew panel. Reference: Passengers: Avox Passenger Mask Assy 9919073-1,
Passenger masks are located above the aisle in the cabin overhead. Crew masks are located over their outboard shoulder on the divider panel. The oxygen bottle/regulator is located under the RH nose baggage
compartment. The regulator can be turned on/off with a pull cable on the crew panel. Reference: Passengers: Avox Passenger Mask Assy 9919073-1,9919073-2 Crew: Eros Crew Mask Assy 9914067-41 Bottle/Regulator Assy: BE 4441073-022 (STD), 4441073-040 (OPT)
Oxygen pressure gauge is located on the RH side of the crew panel. D: Oxygen Pressure Gauge: Midcontinent InstrumentsMD97-1
Model 510 is not a transport category aircraft; however pitot heat indication is standard.
135.159(a)
Rate-of-turn Indication is displayed on the Pilot and Copilot’s Primary Flight Displays. A Standby Attitude Indicator is also installed as an isolated third Attitude source.
GDU1040A, P/N: 011-00916-00 qty (2); GRS77, P/N: 011-00868-10 qty (2) Standby ATT Indicator P/N: 4200-21 qty (1).
135.159(b)
Slip-Skid Indication is displayed on the Pilot and Copilot’s Primary Flight Displays. GDU1040A, P/N: 011-00916-00 qty (2); GRS77, P/N: 011-00868-10 qty (2)
135.159(c)
Pitch and Bank Indication is displayed on the Pilot and Copilot’s Primary Flight Displays. GDU1040A, P/N: 011-00916-00 qty (2); GRS77, P/N: 011-00868-10 qty (2)
135.159(d)
Direction Indication is displayed on the Pilot and Copilot’s Primary Flight Displays. GDU1040A, P/N: 011-00916-00 qty (2); GRS77, P/N: 011-00868-10 qty (2)
135.159(e)
Model 510 aircraft have two engine driven 9KW generators (P/N 9912676-1) Adequacy of electrical power is addressed in report EL-510­200.
135.159(f) (1)
135.159(f) (2)
Instruments are internally illuminated and secondarily lit by flood lights (P/N CL12200)
135.159(f) (3)
Flashlights are provided as standard equipment or the operator may supply their own.
135.159(g)
Adequacy of electrical power is addressed in report
Radio and navigational equipment: Carrying passengers under VFR at night or under VFR over-the-top.
135.161(b)
Navigation, DME, and optional ADF Frequency Tuning all reside on the Pilot and Copilot’s Primary Flight Displays. Each GIA63W contains a Navigation Receiver. VHF Navigation, DME, and optional ADF Navigation information are all displayed on the Pilot and Copilot’s Primary Flight Displays (also with MFD in reversion). GDU1040A, P/N: 011-00916-00 qty (2); GIA63W, P/N: 011-1105-00 qty (2); KN63, P/N: 066-01070-0001 qty (1);
RA3502 optional ADF, P/N: 013-00166-00 (qty 1), RMI Converter, P/N: 013-00167-00.
135.161(c)
Navigation, DME, and optional ADF Frequency Tuning all reside on the Pilot and Copilot’s Primary Flight Displays. Each GIA63W contains a Navigation Receiver. VHF Navigation, DME, and optional ADF Navigation information are all displayed on the Pilot and Copilot’s Primary Flight Displays (also with MFD in reversion). GDU1040A, P/N: 011-00916-00 qty (2); GIA63W, P/N: 011-1105-00 qty (2); KN63, P/N: 066-01070-0001 qty (1); RA3502 optional ADF, P/N: 013-00166-00 (qty 1), RMI Converter, P/N: 013-00167-00
135.163(a)
Vertical Speed information is displayed on Pilot and Copilot’s Primary Flight Displays (also with MFD in reversion). GDU1040A, P/N: 011-00916-00 qty (2); GDC74B, P/N: 011-01110-00 qty (2);
135.163(b)
Outside Air Temperature information is displayed on Pilot and Copilot’s Primary Flight Displays (also with MFD in reversion). GDU1040A, P/N: 011-00916-00 qty (2); GDC74B, P/N: 011-01110-00 qty (2);
135.163(c)
7014150-1 Pitot/Static System Installation Discipline: Avionics/ECS Reference: Compliance Report: EV-510-102.
135.163(d)
Model 510 aircraft incorporate electric power failure annunciations in the Crew Alerting System portion of the Garmin G1000 system.
135.163(e)
Model 510 Aircraft provides a pilot and copilot side static pressure source.
135.163(g)
135.163(h)
Model 510 aircraft have two engine driven 9KW generators (P/N 9912676-1) Adequacy of elec power is addressed in report EL-510­200.
135.163(i)
Adequacy of electrical power is addressed in report EL-510­200
Radio and navigational equipment: Extended overwater or IFR operations.
135.165(b)
Communication, Navigation, DME, and optional ADF Frequency Tuning all reside on the Pilot and Copilot’s Primary Flight Displays. Each GIA63W contains a Communication Transceiver and Navigation Receiver. VHF, DME, and optional ADF Navigation information are all displayed on the Pilot and Copilot’s Primary Flight Displays (also with MFD in reversion). GDU1040A, P/N: 011-00916-00 qty (2); GIA63W, P/N: 011-1105-00 qty (2); KN63, P/N: 066-01070-0001 qty (1); RA3502 optional ADF, P/N: 013-00166-00 (qty 1), RMI Converter, P/N: 013-00167-00 GMA1347D (Internal Marker Beacon), P/N: 011-01257-00 qty (2) Hand MIC, P/N: 63333-008 qty (1) Headsets, P/N: 301317-000 qty (2)
Cockpit Speakers, P/N: EN4S-4FR qty (2) High Frequency (HF), KPA1052 Power Amp P/N: 064-01072-0101 qty (1), KRX1053 Receiver/Exciter P/N: 064-01073-0101 qty (1), KAC1052 Ant Coupler P/N: 064-01074-0101, HF Ctrl Unit P/N: 071-01605-0201 qty (1).
135.165(c)
A Communication Transceiver, Navigation Receiver and a GPS Receiver each reside within the GIA63W. Dual GIA63Ws are in 510 airplane. On-side and Off-side Communication and Navigation Frequency Tuning and Display are capable on the Pilot and Copilot’s Primary Flight Displays.
135.165(d)
Dual GPS STD HF COMM OPT
Dual GIA63Ws are installed in the Model 510 airplane. A GPS Receiver resides within the GIA63W. North Atlantic Track (NAT) Minimum Navigational Performance Specification (MNPS) Airspace (as defined in AC91-49 and AC91-70) – Provided that the proper documentation and approval is obtained. Two FMS’s are required
to be installed, operating and receiving usable signals from independent GPS sensors. High Frequency (HF), KPA1052 Power Amp P/N: 064-01072-0101 qty (1), KRX1053 Receiver/Exciter P/N: 064-01073-0101 qty (1), KAC1052 Ant Coupler P/N: 064-01074-0101, HF Ctrl Unit P/N: 071-01605-0201 qty (1).
135.167(a)
135.167(b)
135.167(c)
135.170(a)
Not Applicable to Model 510. Aircraft weighs less than 12,500 pounds
135.170(b)
135.170(c)
Not Applicable to Model 510. Aircraft is not Transport Category.
Standard on board weather radar system and optional XM satellite weather are in the G1000 system. GDU1500, P/N: 011-1108-00 qty (1) GWX68, P/N: 011-00883-20 qty (1) GDU1500, P/N: 011-1108-00 qty (1) GDL69A, P/N: 011-00987-00 qty (1) Note: XM Graphical Weather is not certified for in-flight navigation. It is intended to be utilized for flight trip
Standard on board wx radar system and optional XM satellite wx are in the G1000 system. GDU1500, P/N: 011-1108-00 qty (1) GWX68, P/N: 011-00883-20 qty (1) GDU1500, P/N: 011-1108-00 qty (1) GDL69A, P/N: 011-00987-00 qty (1). Note: XM Graphical Wx is not certified for in-flight navigation. It is intended to be utilized for flight trip
135.175(a)
Operator will obtain MEL based on the FAA/EASA approved MMEL.
135.180(a)
Standard TIS functionality included in Transponders. GTX33D, P/N: 011-00779-01 qty (1) GTX33, P/N: 011-00779-10 qty (1) GDU1040A, P/N: 011-00916-00 qty (2) GDC74B, P/N: 011-01110-00 qty (2) Optional TAS system
KTA870, P/N: 066-01152­0101 qty (1), Config Module, P/N: 071-00112-0200 qty (1) GDU1040A, P/N: 011-00916-00 qty (2) GDC74B, P/N: 011-01110-00 qty (2) Reference: Compliance Report: AV-510-112 Compliance Report: AV-510-122.
Standard TIS functionality included in Transponders. GTX33D, P/N: 011-00779-01 qty (1) GTX33, P/N: 011-00779-10 qty (1) GDU1040A, P/N: 011-00916-00 qty (2) GDC74B, P/N: 011-
01110-00 qty (2) Optional TAS system KTA870, P/N: 066-01152­0101 qty (1), Config Module, P/N: 071-00112-0200 qty (1) GDU1040A, P/N: 011-00916-00 qty (2) GDC74B, P/N: 011-01110-00 qty (2)
135.181(a)
DOA approved AFM performance enroute climb gradient. Reference: Cessna AFM 510FM-00
135.183(c)
Model 510 meets 14 CFR 23 Commuter category takeoff performance as published in the Airplane Flight Manual
Cessna provides this information at the aircraft delivery thereafter it is the operator’s responsibility to maintain compliance
TABLE 3-4 SUBPART D – VFR/IFR OPERATING LIMITATIONS AND WEATHER REQUIREMENTS
135.227(a)
Operator Responsibility The Model 510 AFM will require the aircraft to be free of frost, snow, or ice prior to takeoff. Takeoff with polished frost per 135.227(a)(1) is prohibited. Refer to DOA Approved AFM limitations for flight icing.
135.227(b)
135.227(c)
The Model 510 ice protection systems will meet the requirements of SFAR 23 Section 34. The Model 510 will be certified for flight in known icing conditions. Refer to AI­510-100, Ice and Rain Protection System Design Compliance and FT510-9, Icing. Discipline: Ice Protection, Flight Test Reference: AI-510-100; FT510-9
135.227(e)
135.227(f)
TABLE 3-5 SUBPART I – AIRPLANE PERFORMANCE OPERATING LIMITATIONS
135.398(a)
Not Applicable. Model 510 is not certificated as a Commuter category aircraft.
135.398(b)
135.398(c)
135.398(d)
135.399(a)
Model 510 does not have a reciprocating engines or turbopropeller powered engines.
135.399(b)
These rules, by omission, do not apply to small turbojet airplanes or to airplanes with fewer than 10 passenger seats. Therefore, they do not apply to the Model 510.
TABLE 3-6 SUBPART J – MAINTENANCE, PREVENTATIVE MAINTENANCE, AND ALTERATIONS
Nine seats or less
135.419(a)
135.419(b)
135.419(c)
135.419(d)
135.419(e)
135.419(f)
135.419(g)
135.419(h)
135.425(a)
Operator Responsibility Cessna will provide operators with a single approved inspection program at time of aircraft delivery. Inspection information will be in Chapter 5, section 10 of the Model 510 Maintenance Manual, per ATA specification 2200
135.425(b)
135.425(c)
135.427(b)