Annex B: Certification Plan and Certification Basis (Steps 2a and 2b)

1. General

1.1 This annex provides guidance on developing the surveillance system certification plan and certification basis.

2. Rationale and Guidance – Certification Plan

2.1 The Applicant is responsible for developing the certification plan and, if the design change is out of scope, for submitting it to DTAES 3 for approval.  DTAES 3 will staff the plan to DTAES 6 for the review of the surveillance system technical aspects of the plan, specifically the certification basis, means and methods of compliance, and surveillance system criteria. During the development of the plan, it is recommended that the Applicant consult DTAES 6 staff for assistance.

2.2 In addition to the standard certification plan requirements defined in the TAM (regulatory reference 3.2.1.a), Parts 2 and 3, the plan must include the following:

  1. the currently approved type design and any already approved surveillance system capabilities;
  2. the new surveillance system capabilities to be certified (Step 1);
  3. the current and proposed aircraft surveillance system equipment configuration to be approved, including any differences across the fleet;
  4. any operating configurations and equipment restrictions that affect surveillance capabilities, including those for mission equipment and external stores. This information is used to determine the scope of compliance demonstration tests and analyses; and
  5. the proposed certification basis (Step 2a).

3. Rationale and Guidance – Certification Basis

3.1 As described in paragraph 4.2.2.b.(1) of the advisory, the certification requirements that will form the certification basis must be selected from one of the approved civil or military airworthiness codes identified in the ADSM (regulatory reference 3.2.1.b).

3.2 Table B-1 provides a listing of the certification requirements that should be considered when defining the certification basis for a surveillance system design change. This table provides only an example of requirements, it does not constitute an exhaustive list of requirements involving Surveillance systems certification. Certain changes could involve, for example, control and stability requirements due to installation of large antennas on the exterior part of the aircraft.

3.3 The Applicant must include aircraft cybersecurity requirements within the certification basis. Table B-1 is FAA-centric and, at the time this TAA advisory was published, the FAA, unlike EASA, did not have specific Title 14 Code of Federal Regulations (14 CFR) paragraphs that dealt with Aircraft Cybersecurity. EASA has codified Aircraft Cybersecurity requirements by including paragraph 1319 into the following Certification Specifications (CS) 25, 27, and 29 (Table B-1 item 23). The EASA Aircraft Cybersecurity requirements for CS -2323 are addressed in EASA Guidance Material (GM) 23.2500(b). The ADSM (regulatory reference 3.2.1.b) Part 2, Chapter 6 – “Aircraft Cybersecurity” provides additional details on establishing an aircraft cybersecurity certification basis. Furthermore, DTAES 8 staff can provide assistance in establishing the aircraft cybersecurity certification basis.

Table B-1 Example of Certification Requirements from Civil and Military Airworthiness Codes to Be Used in Developing the Certification Basis for a Surveillance System Design Change
No. Civil Aiworthiness Codes Military Airworthiness Codes 
(Mil-HDBK-516, EMACC)
1 AWM/14 CFR xx.581 Lightning Protection 13.2.4 Lightning Protection
2 AWM/14 CFR xx.899 Electrical bonding and protection 12.2 Electrical Power Distribution, Bonding and Grounding
3 AWM/14 CFR xx.1301 Function and Installation 11.1.1 Avionics Subsystems Architecture
11.1.1.5 Navigation subsystem
4 AWM/14 CFR xx.1307 Miscellaneous equipment 11.1.1 Avionics subsystems architecture
5 AWM/14 CFR xx.1309 Equipment, Systems and Installations 11.1 Undetected Failure Modes, Redundancy, Deterministic
11.2 Safety and Flight Critical Control Functions, Integrity
14.1.1 System safety, Fail-safe Design
14.2. Safety Design Requirements, Single Point Failure
14.3 Software Safety Program
15. Computer Systems and Software
6 AWM/14 CFR xx.1310 Power Source Capacity and Distribution 12.1 Electrical Power Generation
12.2 Electrical Wiring and Power Distribution
7 AWM/14 CFR xx.1316 Electrical and Electronic System Lightning Protection
(.1306 for AWM/14 CFR 23)
13.2.4 Lightning Effects  
8 AWM/14 CFR xx.1317 High-intensity Radiated Fields (HIRF) Protection
(.1308 for AWM/14 CFR 23 .2520 for AWM523)
13.2.3 Compatibility of Air System with Electromagnetic Environment
9 AWM/14 CFR xx.1321 Flight Instrument - Arrangement and Visibility 9.2.1 Crew station arrangement
9.2.1.1 Controls and display readability
9.2.2 Controls and display usability
10 AWM/14 CFR xx.1322 Flight Crew Alerting 9.2.3 Aircrew alerting systems
11.2.1.3 Warnings, cautions, and advisories
11 AWM/14 CFR xx.1325 Static pressure systems 11.1.1.1 Air data system
12 AWM/14 CFR xx.1329 Flight Guidance Systems 6.1.13 Characteristics of secondary flight control systems
6.2 Vehicle control functions (VCF)
13 AWM/14 CFR xx.1331 Instruments using a power supply 12.1.5 Uninterruptible power
14 AWM/14 CFR xx.1333 Instrument systems 9.2.1 Crew station arrangement
9.2.1.1 Controls and display readability
9.2.2 Controls and display usability
15 AWM/14 CFR xx.1351 Electrical Systems and Equipment -General 12.1 Electrical Power Generation
12.1.4 Power quality
16 AWM/14 CFR xx.1353 Electrical equipment and installations 12.1.3 Safe operation of integrated electrical power system
13.2.1 Electromagnetic Compatibility
13.2.2 Mutual compatibility of antenna-connected and other equipment.
17 AWM/14 CFR xx.1357 Circuit protective devices 12.2.3 Circuit protection
18 AWM/14 CFR xx.1419 Ice protection 8.2.9.1 Ice detection and protection
19 AWM/14 CFR xx.1431 Electronic equipment 11.1.5.3 Interface/interconnect failures
11.2.5 Electrical power quality
13.2.1 Electromagnetic Compatibility
13.2.2 Mutual compatibility of antenna-connected and other equipment.
20 AWM/14 CFR xx.1529 Instructions for Continued Airworthiness 16.1 Maintenance manuals/checklists
16.2 Inspection requirements
21 AWM/14 CFR xx.1533(b) Additional operating limitations 11.3.2 Necessary limitations
22 AWM/14 CFR xx.1581(a)(2) Airplane Flight Manual 11.3.2 Necessary limitations
12.1.7 Subsystem limitations
12.1.8 Procedures
23 EASA CS-25/27/29.1319 Equipment, systems and network information
protection
4.1.2 Safety critical hardware and software
6.2.9.2 Security
15.2.8 Security techniques

4. Rationale and Guidance – Standards, Means and Methods of Compliance, and Guidance Documents

4.1 Table B-2 should be consulted to identify the appropriate standards, means and methods of compliance, and guidance material applicable to the required surveillance capabilities identified in Step 1. Once identified, the criteria should be collated to create the Surveillance Criteria Table, as described in Step 2c – Setting up the Surveillance Criteria Table.

Notes: 1. For clarity, only the FAA TSOs are listed in Table B-2. However, the equivalent Canadian TSO (CAN-TSO) or EASA TSOs (E-TSO) are also acceptable, unless otherwise indicated.
2. The FAA TSOs, CAN-TSOs and E-TSO will generally reference RTCA and EUROCAE specifications. Frequently, the TSO will add new requirements, modify or delete specific RTCA and EUROCAE requirements. Therefore, the RTCA and EUROCAE specifications associated with the TSOs identified in Table B-2 may also constitute acceptable standards, provided the TSO additions, modifications and/or deletions are addressed.

4.2 Specialist knowledge and experience are required to interpret and select the appropriate criteria. The DTAES 6 engineering support staff can be contacted to assist in the selection of the applicable criteria and the development of the Surveillance Criteria Table. Guidance material for the development of the Surveillance Criteria Table is provided in Annex C of this advisory.

4.3 The final step in demonstrating compliance is the identification of compliance artefacts, which will be provided to support the findings of compliance and design assessment. Examples of compliance artefacts include:

  1. Design description documents;
  2. Design analysis reports;
  3. Integration lab test reports;
  4. Aircraft ground and flight test reports;
  5. TSO Authorization (TSOA) or Military Standard Order (MSO) approval references; and
  6. Approvals from other Airworthiness Authorities.

4.4 Table B-3 provides an ADS-B Out example of surveillance system certification basis and compliance matrix. The first three columns in the table relate to the certification basis.

Table B-2 Design Standards, Means and Methods of Compliance, and Guidance Material by Type of Surveillance Capability

Mode A/C

Design Standards Means and Methods of Compliance or
Guidance Material

FAA TSO-C74 (b), (c) or (d)

FAA TSO-C88 (AR) 

FAA AC 23-8C – Transponder specific content

FAA AC 25-7C – Transponder specific content

FAA AC 27-1B – Transponder specific content

FAA AC 29-2C – Transponder specific content

EASA CS-ACNS Issue 4 EASA CS-ACNS Issue 4

Mode S

Design Standards Means and Methods of Compliance or
Guidance Material

FAA TSO-C112 (e)

FAA AC 20-131A – Mode S specific content

FAA AC 20-151C – Mode S specific content

EASA CS-ACNS Issue 4 EASA CS-ACNS Issue 4

ADS-B Out

Design Standards Means and Methods of Compliance or
Guidance Material
TCCA AWM 551.103 TCCA AC 500-029 Issue 2

FAA TSO-C166 (b)

FAA AC 20-165B

EASA CS-ACNS Issue 4 EASA CS-ACNS Issue 4

ADS-B In

Design Standards Means and Methods of Compliance or
Guidance Material

FAA TSO-C195 (b)                     

FAA AC 20-172B

IFF Mode 1, 2, 3 and 5

Department of Defense (DoD) Air Traffic Control Radar Beacon System, Identification Friend or Foe, Mark XII/Mark XIIA, Systems (AIMS) 17-1000

NOTE: Although not explicitly considered as technical airworthiness standards, the U.S. DoD AIMS standards have been included for reference purposes.

Table B-3 Example of ADS-B Out Surveillance Certification Basis and Compliance Matrix

Certification Requirement and Title

Certification Requirement Text

[Caution: Exact requirement will depend on
specific 14 CFR Part and amendment level]

Notes Means of Compliance Compliance Artefacts Finding Authority

14 CFR xx.1301

Function and Installation

Each item of installed equipment must:
(a)    Be of a kind and design appropriate to its intended
function;
(b)    Be labeled as to its identification, function, or operating
limitations, or any combination of these factors;
(c)   Be installed according to limitations specified for that
equipment; and
(d)   Function properly when installed.
n/a Applicable portions of: 
AC 23-8C. 25-7D, 27-1B , 29-2C, and 20-165B, as defined in the Criteria Table 

Design Data, Analysis and Test Reports

Design Assessment Report

FA
Avionics
and
Software

14 CFR xx.1309

Equipment, Systems and Installations 

The equipment, systems, and installations whose functioning
is required by this subchapter, must be designed to ensure
that they perform their intended functions under any foreseeable
operating condition.
n/a AC 23/25.1309, and applicable portions of AC 27-1B, 29-2C, AC 20-165B, as defined in the Criteria Table 

Design Data, Analysis and Test Reports

Design Assessment Report

FA
Avionics
and
Software

14 CFR xx.1309

Equipment, Systems and Installations

The airplane systems and associated components, considered
separately and in relation to other systems, must be designed
so that
(1) The occurrence of any failure condition which would prevent
the continued safe flight and landing of the airplane is extremely
improbable, and
(2) The occurrence of any other failure conditions which would
reduce the capability of the airplane or the ability of the crew
to cope with adverse operating conditions is improbable.
n/a AC 23/
25.1309, and applicable portions of AC 27-1B, 29-2C, AC 20-165B, as defined in the Criteria Table

Design Data, Analysis and Test Reports

Design Assessment Report

FA Avionics/ Software and System Safety

14 CFR 25.1310

Power Source and Distribution

Each installation whose functioning is required for type
certification or under operating rules and that requires a
power supply is an “essential load” on the power supply. The
power sources and the system must be able to supply the
following power loads in probable operating combinations
and for probable durations 
n/a Applicable portions of AC 25-7D and AC 20-165B, as defined in the Criteria Table

Design Data, Analysis and Test Reports

Design Assessment Report

FA Electrical

Mil HDBK 516 section 13.2.4

Lightning Effects  

516-Criterion:

Verify that the air system has met all requirements for lightning,
either direct (physical) or indirect (electromagnetic) effects and
that any potential for ignition of fuel vapors is eliminated.

Or CFR 23.1306 or CFR 25/27/29.1316

Lightning Protection

Mil Std 464 or AC 20-136B, and applicable portions of AC 27-1B, 29-2C, and AC 20-165B, as defined in the Criteria Table

Design Data, Analysis and Test Reports

Design Assessment Report

FA E3

14 CFR 23.1308, 25/27/29.1317

High-intensity Radiated Fields (HIRF) Protection.

Each electrical and electronic system that performs a function
whose failure would prevent the continued safe flight and
landing of the airplane must be designed and installed so that:

(1) The function is not adversely affected during and after the
time the airplane is exposed to HIRF environment I, as described
in appendix L to this part;[…]

n/a FAA AC 20-158A, and applicable portions of AC 27-1B, 29-2C and AC 20-165B, as defined in the Criteria Table

Design Data, Analysis and Test Reports

Design Assessment Report

FA E3

14 CFR xx.1321

Flight Instruments 

Each flight, navigation, and power plant instrument for use by any pilot must be plainly visible to him from his station
with the minimum practicable deviation from his normal position and line of vision when he is looking forward along the flight path. 
n/a Applicable portions of AC 27-1B, 29-2C and AC 20-165B, as defined in the Criteria Table

Design Data, Analysis and Test Reports

Design Assessment Report

FA TN – Avionics/
HFE

14 CFR xx.1322

Flight Crew Alerting

Flight crew alerts must:

(1) Provide the flight crew with the information needed to:
     (i) Identify non-normal operation or airplane system conditions,
     (ii) Determine the appropriate actions, if any.
(2) Be readily and easily detectable and intelligible by the flight
crew under all foreseeable operating conditions, including
conditions where multiple alerts are provided.
(3) Be removed when the alerting condition no longer exists

n/a Applicable portions of AC 27-1B, 29-2C and AC 20-165B, as defined in the Criteria Table

Design Data, Analysis and Test Reports

Design Assessment Report

FA
Avionics
14 CFR xx.
Electronic Equipment

(a) In showing compliance with § 25.1309 (a) and (b) with respect to radio and electronic equipment and their installations, critical environmental conditions must be considered.

(b) Radio and electronic equipment must be supplied with power under the requirements of § 25.1355(c).

(c) Radio and electronic equipment, controls, and wiring must be installed so that operation of any one unit or system of units will not adversely affect the simultaneous operation of any other radio or electronic unit, or system of units, required by this chapter.

(d) Electronic equipment must be designed and installed such that it does not cause essential loads to become inoperative as a result of electrical power supply transients or transients from other causes.

  Applicable portions of AC 27-1B, 29-2, 20-151C and AC 20-165B, as defined in the Criteria Table

 Design Data, Analysis and Test Reports

Design Assessment Report

FA EMC
 14 CFR xx.1529 Instructions for Continued Airworthiness (ICAs) n/a Applicable portions of AC 20-151C and 20-165B, as defined in the Criteria Table Reports DTAES 4

14 CFR xx.1581

Flight Manual

An Airplane Flight Manual must be furnished with each airplane,
and it must contain the following:
(1) Information required by §§25.1583 through 25.1587;
(2) Other information that is necessary for safe operation because
of design, operating, or handling characteristics. 
n/a AC 25.1581, applicable portions of AC 23-8C, 25-7D, 27-1B, 29-2C and 20-165B, as defined in the Criteria Table FM/AOI and/or FM/AOI changes FA AFM

Aircraft Cybersecurity

EASA CS 25.1319

Equipment, systems and network information protection

Note: CS 27/29.1319 contain similarly worded requirements.

Note: Guidance on CS 23 is provided in GM 23.2500(b).

Consulting ADSM Part 2, Chapter 6 and DTAES 8 when developing
the Aircraft Cyber Security Certification Requirement is recommended.

An example of an acceptable cybersecurity requirement that could
be applied to DND aircraft follows:

(a) Aeroplane equipment, systems and networks, considered
separately and in relation to other systems, must be protected
from intentional unauthorised electronic interactions (IUEIs) that may result in adverse effects on the safety of the aeroplane. Protection must be ensured by showing that the security risks have been identified, assessed and mitigated as necessary.

(b) When required by paragraph (a), the applicant must make procedures and ICA available that ensure that the security protections of the aeroplane’s equipment, systems and networks are maintained.

n/a

EASA AMC - 25.1319

EASA AMC 20-42

Design Assessment Report

Design Data, Analysis and Test Reports

DTAES 8

Page details

2024-06-12