9/18/20

 

8900.1 CHG 722

VOLUME 10  SAFETY ASSURANCE SYSTEM POLICY AND PROCEDURES

CHAPTER 9  AIRCRAFT CONFIGURATION CONTROL DOCUMENT

Section 2  Safety Assurance System: Aircraft Configuration Control Document—14 CFR Part 135

10-9-2-1    GENERAL.

Indicates new/changed information.

A.    Purpose. This section provides information and references for the evaluation of an aircraft configuration based on Title 14 of the Code of Federal Regulations (14 CFR) part 135 operational requirements.

B.    Scope. This section applies to participants in the evaluation of an aircraft configuration. Use this process to determine if an aircraft meets the operational requirements. Record all findings in the Safety Assurance System (SAS) automation and the associated Data Collection Tools (DCT). Refer to SAS Elements 2.3.1 (OP) Appropriate Operational Equipment, 4.2.1 (AW) Maintenance/Inspection Requirements, and 4.4.4 (AW) Aircraft Requirements/Acceptance Process. The Aircraft Configuration Control Document (ACCD) includes the following information:

    Guidance in the development of a certificate holder’s aircraft conformity and acceptance programs.

    Configuration and operating requirements of part 135.

    Verification of supporting documents when adding new make or model aircraft to an existing certificate holder’s certificate (operations specification (OpSpec) D085).

    Regulatory and advisory guidance.

NOTE:  The references in this section may not be all-inclusive and are subject to change.

10-9-2-3    RESERVED.

10-9-2-5    BACKGROUND.

A.    General Information. A review of case law relating to airworthiness reveals that an aircraft must meet two conditions to be considered “airworthy,” as defined in 14 CFR part 3, § 3.5(a). Additionally, an aircraft must be determined as eligible for the issuance of an airworthiness certificate under Title 49 of the United States Code (49 U.S.C.) § 44704(d)(1) and 14 CFR part 21, §§ 21.1(b)(1) and 21.183(a), (b), and (c)(3). Two conditions that must be met for issuance of an airworthiness certificate as described in Volume 8, Chapter 5, Section 1 and Federal Aviation Administration (FAA) Order 8130.2, Airworthiness Certification of Aircraft, Chapter 2, Common Policies and Procedures for Issuing an Airworthiness Certificate, are:

1)    The aircraft must conform to its type certificate (TC) (design). This is attained when the aircraft configuration and the engine, propeller, and articles installed are consistent with the drawings, specifications, and other data that are part of the TC. This includes any Supplemental Type Certificate (STC) and repairs and alterations incorporated into the aircraft.
2)    The aircraft must be in a condition for safe operation. This refers to the condition of the aircraft relative to wear and deterioration (e.g., skin corrosion, window delamination/crazing, fluid leaks, and tire wear). (Refer to Order 8130.2, chapter 2.)

B.    Standard Airworthiness Certificate. The aircraft must have a Standard Airworthiness Certificate. This certificate remains valid as long as the aircraft:

1)    Meets its approved type design.
2)    Is in a condition for safe operation.
3)    Has up-to-date maintenance and preventive maintenance.
4)    Alterations are performed in accordance with 14 CFR parts 21, 43, and 91.
5)    Conforms to the “Limitations” and “Supplement” sections within the approved Airplane Flight Manual (AFM).

C.    Request List. Figure 10-9-2A, Request List, is a list of items the aircraft owner/operator should have available to support the aircraft and document evaluation. This list is not all-inclusive.

D.    Related 14 CFR Parts that May be Listed. Title 14 CFR parts 21, 25, 33, 39, 43, 45, 47, 91, and 135.

E.    Related Element Design DCTs (ED DCT) and Element Performance DCTs (EP DCT). The majority of the inspection items within this job aid contain specific regulatory requirements and are supported by the related ED/EP DCTs.

F.    The Physical Inspection of the Aircraft (Including General Visual Inspection (GVI)). This inspection is a visual examination of the interior and exterior areas of the aircraft to evaluate equipment and manual requirements, as required in part 135, and to detect obvious damage, failure, or irregularity. You, the aviation safety inspector (ASI), conduct this level of inspection under normally available lighting conditions, such as daylight, hangar lighting, flashlight, or drop light. This inspection may require the removal or opening of access panels or doors. Stands, ladders, or platforms may be required to access the area of inspection. Use normal inspection aids (as required), such as an inspection mirror, a flashlight, and a mechanic’s 6-inch scale.

NOTE:  This section may reference certification regulations, but they are not listed in the “References” column.

Figure 10-9-2A.  Request List

Request List

Copy of the certificate holder’s inspection document (configuration/conformity inspection).

Copy of the bridging (transfer) document and the Continuous Airworthiness Maintenance Program (CAMP) for the aircraft, including work cards and time limits (may be in electronic format).

The Maintenance Review Board (MRB) and Maintenance Planning Document (MPD) (manufacturer’s recommended maintenance program) for the aircraft.

Aircraft Interior Configuration Document (AICD) for the interior and additional diagrams that might include location of emergency equipment, if not on the AICD.

Passenger briefing cards.

Current aircraft equipment list (as revised).

The Federal Aviation Administration (FAA) will also ensure the operator has the aircraft in its tracking system (forecast, next check due, etc.).

Flight deck checklists.

Flammability test certifications for aircraft interior materials (14 CFR part 23, § 23.2325 and part 25, § 25.853), as appropriate.

Skin-Contour Inspection (Skin Mapping) (repairs) and repair assessment, if applicable (14 CFR part 43 appendix E; part 91, § 91.411; and part 135, § 135.425). (Reduced Vertical Separation Minimum (RVSM), operations specification (OpSpec) B046.)

Airplane Flight Manual (AFM) and company manual (§ 135.21).

Major Repair and Alteration (part 43 appendix B and §§ 43.5, 43.7, 91.417, and 135.439 (as required)).

Minimum equipment list (MEL) (§§ 91.213 and 135.179).

Pilot aircraft operating manual (§ 135.21 not required for single pilot, single pilot in command (PIC), and basic).

Placard diagram and/or manual (§§ 91.9, 91.213, and 91.405).

Records required by §§ 91.417 and 135.439.

In-flight manual (flight attendant (F/A) manual) (§§ 135.107 and 135.341).

Technical documents that firmly establish the digital flight data recorder (DFDR) parameter types and accuracies, and the latest DFDR data download, if available (§ 135.152).

All Supplemental Type Certificates (STC) for the aircraft.

Figure 10-9-2B.  Aircraft Information Form

 

 

 

 

 

 

 

 

 

 

Make/Model/Series

 

Current Registration No.

 

Date of Last “Heavy” CK.

 

Aircraft Interior
Configuration
Document (AICD)

 

A

 

 

 

 

(MM/DD/YY)

 

 

I

Serial No.

 

Previous Registration No.

 

Date of Last “C” CK.

 

Yes   No

 

R

 

 

 

 

(MM/DD/YY)

 

Repair Assessment

 

C

Line or Fuselage No.

 

Total Time (TT)

 

Last Operator

 

Available?

 

R

 

 

 

 

(Designator)

 

Yes   No

 

A

Date of Manufacture

 

Total Cycles (TC)

 

Current Operator

 

Bridging Document

 

F

 

 

 

 

(Designator)

 

Available?

 

T

TC Data Sheet (No.)

 

Interior Configuration

 

 

 

Yes   No

 

 

 

 

(# of PAX)

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

Operator’s Empty
Wgt.

 

Max Structural Wgt.

 

Max Take-Off Wgt.

 

Date of Last Weighing

 

W

 

 

 

 

 

 

(MM/DD/YY)

 

G

Max Zero Fuel Wgt.

 

Max Taxi or Ramp Wgt.

 

Max Landing Wgt.

 

Current Acft Equip
List?

 

T

 

 

 

 

 

 

Yes   No

 

 

Basic Operating
Wgt. (BOW)

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

Power Plant 1

 

Power Plant 2

 

Power Plant 3

 

Power Plant 4

 

P

Make/Model/Series

 

Make/Model/Series

 

Make/Model/Series

 

Make/Model/Series

 

O

 

 

 

 

 

 

 

 

W

Serial No.

 

Serial No.

 

Serial No.

 

Serial No.

 

E

 

 

 

 

 

 

 

 

R

Total Time (TT)

 

Total Time (TT)

 

Total Time (TT)

 

Total Time (TT)

 

P

 

 

 

 

 

 

 

 

L

Total Cycles (TC)

 

Total Cycles (TC)

 

Total Cycles (TC)

 

Total Cycles (TC)

 

A

 

 

 

 

 

 

 

 

N

T

Time Since Overhaul
(TSO)

 

Time Since Overhaul
(TSO)

 

Time Since Overhaul
(TSO)

 

Time Since Overhaul
(TSO)

 

 

 

 

 

 

 

 

 

 

 

Powerplant Type Certificate Data Sheet (No.)

 

 

 

 

 

 

Propeller 1

 

Propeller 2

 

Propeller 3

 

Propeller 4

 

 

Make/Model/Series

 

Make/Model/Series

 

Make/Model/Series

 

Make/Model/Series

 

 

 

 

 

 

 

 

 

 

P

Serial No.

 

Serial No.

 

Serial No.

 

Serial No.

 

R

 

 

 

 

 

 

 

 

O

Total Time (TT)

 

Total Time (TT)

 

Total Time (TT)

 

Total Time (TT)

 

P

 

 

 

 

 

 

 

 

S

Total Cycles (TC)

 

Total Cycles (TC)

 

Total Cycles (TC)

 

Total Cycles (TC)

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

Propeller Type Certificate Data Sheet (No.)

 

 

 

 

 

 

 

 

 

 

 

 

 

 

A

Make/Model/Series

 

Total Time (TT)

 

Time Since Overhaul
(TSO)

 

Applicable to Acft
TCDS?

 

P

 

 

 

 

 

 

Yes   No

 

U

Serial No.

 

Total Cycles (TC)

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

Nose Gear

 

RH Main Gear

 

LH Main Gear

 

Other Gear
Assemblies

 

L

Make/Part Number

 

Make/Part Number

 

Make/Part Number

 

Make/Part Number

 

D

 

 

 

 

 

 

/

 

G

Serial No.

 

Serial No.

 

Serial No.

 

Serial Nos.

 

 

 

 

 

 

 

 

/

 

G

Total Time (TT)

 

Total Time (TT)

 

Total Time (TT)

 

Total Time (TT)

 

E

 

 

 

 

 

 

/

 

A

Total Cycles (TC)

 

Total Cycles (TC)

 

Total Cycles (TC)

 

Total Cycles (TC)

 

R

 

 

 

 

 

 

/

 

 

Time Since Overhaul
(TSO)

 

Time Since Overhaul
(TSO)

 

Time Since Overhaul
(TSO)

 

Time Since Overhaul
(TSO)

 

 

 

 

 

 

 

 

/

 

 

 

 

 

 

 

 

 

 

Indicates new/changed information. Indicates new/changed information. Indicates new/changed information.

Table 10-9-2A.  Configuration-Related Research

ITEM

CONFIGURATION-RELATED RESEARCH

REFERENCES (current editions)

1

Aircraft History. Review aircraft information in Federal Aviation Administration (FAA) databases and other applicable sources.

Safety Performance Analysis System (SPAS)

Foreign Civil Aviation Authority (FCAA)

Manufacturer, etc.

2

Airframe Type Certificate Data Sheets (TCDS).

a. Compare information on the TCDS to aircraft information the certificate holder provides.

b. Research related information, including all TCDS notes (instructions for continued airworthiness (ICA), aircraft certified with a special condition (SC), Reduced Vertical Separation Minimums (RVSM) eligibility, High Intensity Radiated Field (HIRF) requirements, basic equipment list, etc.).

14 CFR part 21, § 21.16, 21.21, and 21.41

FAA Order 8130.2, Airworthiness Certification of Aircraft, Chapter 8, Limited Category (§ 21.189)

Volume 3, Chapter 61, Section 1

3

Engine TCDS. Review the applicability of the TCDS. Verify the compatibility of propellers to the installed engines.

§ 21.41

14 CFR part 33, § 33.1

4

Propeller TCDS. Review the applicability of the TCDS. Verify that the propellers are approved for operation with installed engines.

§ 21.41

5

Master Minimum Equipment List (MMEL). Obtain a copy of the current MMEL for comparison to the certificate holder’s minimum equipment list (MEL) for correct revision.

https://fsims.faa.gov/
PICResults.aspx?mode=Publication
&doctype=MMEL

6

Airworthiness Directives (AD) (Airframe, Engines, Propellers, and Appliances). Research and generate an applicable AD listing.

NOTE: It may not be possible to complete the list until after reviewing the manufacturer’s and operator’s appliance and equipment lists.

https://www.faa.gov/
regulations_policies/
airworthiness_directives/

7

Additional Information. Review any other information that is available and related to the specific aircraft being evaluated (e.g., SPAS, Safety Assurance System (SAS) automation, Web-based Operations Safety System (WebOPSS) authorization reference).

Will need to enter SAS via:

https://sas.avs.faa.gov/
sas.internal.portal/

https://home.spas.faa.gov/
splash/splash.asp

NOTE: These are internal FAA sites only

8

Review ICAs—(Maintenance Review Board Report (MRBR), Maintenance Planning Document (MPD), etc.). Review ICAs for additional regulatory requirements (e.g., Certification Maintenance Requirements (CMR)).

Advisory Circular (AC) 121-22, Maintenance Review Boards, Maintenance Type Boards, and OEM/TCH Recommended Maintenance Procedures

Indicates new/changed information.

Table 10-9-2B.  Manuals

ITEM

MANUALS

REFERENCES (current editions)

1

Airplane Flight Manual (AFM).

a. Verify that the certificate holder has a current and complete copy of the applicable manufacturer’s Federal Aviation Administration (FAA)-approved AFM for the particular aircraft make, model, and serial number.

b. Verify that all supplements are applicable, complete, and properly approved (including Airworthiness Directives (AD)).

c. Verify that the actual aircraft configuration conforms to the supplements, which includes Supplemental Type Certificate (STC)-derived supplements.

d. Verify all aircraft checklists, including expanded checklists, match the AFM/Airplane Operations Manual (AOM).

14 CFR part 91, § 91.9

14 CFR part 135, § 135.25

2

Flight Deck Check Procedures (Checklist). Verify that flight deck check procedures (checklists) are current and complete, properly approved, and limited to action or verification items. The operator’s manual and training programs must thoroughly describe required actions and decisions for crewmembers performing a checklist.

§ 135.83

Volume 3, Chapter 32, Section 2

3

Performance Requirements. The performance requirements of 14 CFR part 25, §§ 25.101 through 25.125 apply to all aircraft certificated under part 25 subpart A. Each specific aircraft’s performance and limitations for existing aircraft configuration, modifications, improvements, and engine installation must be included in the particular FAA-approved AFM or AOM.

§§ 135.361, 135.363, 135.364, 135.365, 135.367, 135.369, 135.371, 135.373, 135.375, 135.377, 135.379, 135.381, 135.383, 135.385, 135.387, 138.389, 135.391, 135.393, 135.395, 135.397, 135.398, and 135.399

4

Minimum Equipment List (MEL). Verify that the operator’s MEL is FAA-approved, is configured to the subject aircraft, and is current with respect to the Master Minimum Equipment List (MMEL).

§ 91.213

§ 135.179

Volume 4, Chapter 4, Sections 1 through 4

5

Weight and Balance Manual (WBM) (and Cargo Loading Manual, if Applicable).

a. Verify that the certificate holder’s approved WBM is appropriate to the make, model, and series (M/M/S) of the subject aircraft.

b. Verify that listed weights are configured to the Type Certificate Data Sheet (TCDS), AFM/AOM, and Advisory Circular (AC) 120-27, Aircraft Weight and Balance Control.

§ 91.605

§§ 135.23 and 135.185

Volume 3, Chapter 47

AC 120-27

6

Pilot and Flight Attendant (F/A) Crewmember Training Programs. If the type of aircraft requires F/As per § 135.107, verify that the operator has a current, complete, and FAA-accepted manual available. Ensure that the manual accurately depicts the cabin configuration and equipment.

§§ 135.23, 135.107, and 135.341

Volume 3, Chapter 32, Section 13

7

Other Manual Parts by Regulation.

a. Verify that all manual parts required by the operator to be carried on board the aircraft are in fact on board.

b. Verify that the manual is current, is FAA-approved or FAA-accepted (as appropriate), and accurately reflects the aircraft configuration.

c. Verify that the operator has a system to revise and keep current all of its technical manuals (e.g., Aircraft Maintenance Manual (AMM), Illustrated Parts Catalogue (IPC), and other manuals for maintaining its aircraft).

NOTE: Part 135 operators are responsible for their manual system and maintaining the currency of this manual with the source (manufacturer’s) document.

§§ 135.21, 135.23, and 135.427

Volume 3, Chapter 32, Section 11

Indicates new/changed information.

Table 10-9-2C.  Records

ITEM

RECORDS

REFERENCES (current editions)

1

Certificate of Airworthiness.

a. Does the aircraft have a properly issued U.S. Certificate of Airworthiness?

b. Check the applicability and limitations of exemptions/deviations from the Type Certificate Data Sheet (TCDS) or other certification document.

c. For foreign-registered aircraft, does the Foreign Civil Aviation Authority (FCAA)-issued Certificate of Airworthiness meet the regulatory requirements for the U.S. certificate holder service? (Refer to 14 CFR part 135, § 135.25(d).)

14 CFR part 21, § 21.175

14 CFR part 91, § 91.205

§ 135.25

Volume 3, Chapter 17

Volume 3, Chapter 31, Section 5

FAA Order 8130.2, Airworthiness Certification of Aircraft

2

Maintenance Overhaul/Time Controlled/Life-Limited Items/Certification Maintenance Requirements (CMR)/Airworthiness Limitations.

a. Review documentation for all articles subject to time/cycle/life limits. (Are the articles tracked by nomenclature, part number, serial number, lot number, or via records the operator retains?)

b. Review the TCDS for specific tracking requirements.

c. Does the operator have a system to verify inspection status, overhauls, and repetitive maintenance/inspection tasks for this specific aircraft?

d. Are the requirements of the applicable Maintenance Review Board Report (MRBR) evident in the operators program? Have all MRBR requirements been met? (See Table 10-9-2A, Configuration-Related Research, for a description.)

e. Are the records and inspection intervals in accordance with the certificate holder’s authorized Continuous Airworthiness Maintenance Program (CAMP)?

f. Perform a sampling inspection of articles/components installed on the aircraft. (Are the articles/components maintained in accordance with the certificate holder’s authorized CAMP?)

14 CFR part 43, §§ 43.13, 43.15, and 43.16

§§ 91.409 and 91.417

§§ 135.411, 135.413, 135.422, and 135.439

Volume 3, Chapter 31, Section 5

Volume 3, Chapter 64, Section 1

Volume 6, Chapter 2, Section 28

FAA Order 8110.54, Instructions for Continued Airworthiness Responsibilities, Requirements, and Contents

Advisory Circular (AC) 20-62, Eligibility, Quality, and Identification of Aeronautical Replacement Parts

AC 120-16, Air Carrier Maintenance Programs

3

Air Traffic Control (ATC) Transponder Test and Inspection.

a. Do the operator’s records document the completion of the 24‑month tests and inspection of the ATC transponder system (including altitude reporting equipment) in accordance with part 43 appendix F?

b. Do the records support proper transponder reporting of the current aircraft Mode Select (Mode S) address?

c. Do the records follow any installation or maintenance on an ATC transponder where data correspondence error could have been introduced, the integrated system shows to have been tested, inspected, and found to comply with part 43 appendix E, paragraph (c)?

Part 43 appendices E and F

§§ 91.411 and 91.413

§§ 135.141, 135.143, 135.411, and 135.413

4

Temporary Repairs.

a. Check the records of temporary repairs made to the aircraft for compliance with program and regulatory requirements.

b. Perform a spot check of the aircraft for evidence of repairs and correlate those repairs to supporting documentation.

§ 43.13

§ 91.213

§ 135.179

Volume 3, Chapter 36, Section 1

FAA Order 8300.13, Repair Assessment Program

AC 25-22, Certification of Transport Airplane Mechanical Systems

AC 120-73, Damage Tolerance Assessment of Repairs to Pressurized Fuselages

5

Supplemental Type Certificates (STC).

a. Check that Federal Aviation Administration (FAA)‑approved data support the installed STCs.

b. Check that the installations are not partial applications of the STC.

c. Check the installations to the data and ensure that the required changes to the operating manuals (Airplane Flight Manual (AFM) supplements) and maintenance manuals address the change.

d. Review the instructions for continued airworthiness (ICA) provided with the STC and ensure these requirements are addressed in the operator’s maintenance/inspection program and publications.

e. Check STCs installed on the aircraft. Check for evidence that the interrelationship of the installations was reviewed and determined to be acceptable (STC requirement).

14 CFR part 21

§§ 91.403(d) and 91.417

§ 135.411

Volume 3, Chapter 36, Section 1

Volume 4, Chapter 3, Sections 1 and 3

Volume 6, Chapter 11, Section 2

Order 8110.54

6

Airworthiness Directives (AD).

a. Check that the operator has a method to track the current status of all applicable ADs. The records must conform to the requirements of the certificate holder’s manual. The information must be specific enough to identify each AD by the:

1) The date accomplished.

2) The method of accomplishment.

3) One-time or recurring.

4) The time/date of the next required action.

b. Do alternative methods of compliance (AMOC) satisfy an AD requirement (if applicable)?

1) Does documentation exist approving the AMOC, and does it allow the specific certificate holder to use that AMOC as a basis for compliance as specified within its text?

2) Spot check of one-time and recurring ADs (airframe, engine, propeller, and appliance).

3) Does the operator have a system to track and report AD status and compliance?

14 CFR part 39

§§ 43.9 and 43.11

§§ 91.403 and 91.417

§ 135.411

Volume 3, Chapter 59, Sections 1 and 3

Volume 3, Chapter 60, Section 1

FAA Order 8110.103, Alternative Methods of Compliance (AMOC)

7

Major Repairs and Alterations.

a. Review records for current major repairs and alterations for each airframe, engine, propeller (if applicable), and appliance.

b. Is there documentation for each major repair and alteration, and was it accomplished in accordance with FAA‑approved technical data? (e.g., STC, Structural Repair Manual (SRM), Designated Engineering Representative (DER), FAA field approval, etc.)

c. Are there ICAs for each alteration and/or repair included in the certificate holder’s maintenance and inspection program?

§ 43.7

Part 43 appendix A

Part 43 appendix B

§§ 91.407 and 91.417

§ 135.411

Volume 6, Chapter 11, Section 2

AC 120-77, Maintenance and Alteration Data

8

Digital Flight Data Recorder System (DFDRS) or Flight Data Recorder System (FDRS), as Applicable.

a. Does the certificate holder maintain the correlation data required by the applicable part 135 section?

b. Review DFDRS or FDRS download/analysis records required by the certificate holder’s manual.

c. Check the recorder system for all required parameters.

d. Is there a system for the analysis download and documenting discrepancies? Are those discrepancies corrected per the certificate holder’s manual?

e. Verify the record of filtered parameters.

§ 91.609

§§ 135.152 and 135.156

Volume 4, Chapter 14, Section 8

AC 20-141, Airworthiness and Operational Approval of Digital Flight Data Recorder Systems

9

Certification Maintenance Requirements (CMR). Verify that all CMR tasks were properly incorporated into the operator’s programs (e.g., CAMP).

Methods and time intervals associated with these tasks must be FAA-approved by the responsible Aircraft Certification Service office and Flight Standards office, as applicable, in the certificate holder’s operations specifications (OpSpecs). CMRs may be located in the applicable MRBR.

14 CFR part 119, § 119.49

§ 135.411

10

Automatic Dependent Surveillance-Broadcast (ADS-B). On May 27, 2010, the FAA published new rules (contained in §§ 91.225 and 91.227) mandating airspace and avionics performance requirements after January 1, 2020. The avionics perform a function that is generally known as “ADS-B Out,” which transmits precise location and other information about the aircraft to ground stations and other ADS-B-equipped aircraft.

The ADS-B rule mandates ADS-B Out avionics performance when operating within the designated airspace, giving aircraft owners approximately 10 years to equip.

The ADS-B rule, like current transponder operating requirements, requires operators to have ADS-B Out avionics installed and operating in order to fly their aircraft in the busiest airspace, as described in the following:

    Classes A, B, and C airspace;

    All airspace at and above 10,000 feet mean sea level (MSL) over the 48 contiguous United States and the District of Columbia;

    Within 30 nautical miles (NM) of airports listed in § 91.225, from the surface up to 10,000 feet MSL; and

    Class E airspace over the Gulf of Mexico from the coastline of the United States out to 12 NM, at and above 3,000 feet MSL.

FAA Technical Standard Orders (TSO) describe the equipment approved for ADS-B operations. The ADS-B rule states that avionics must meet the standards of either TSO-C166b, Extended Squitter Automatic Dependent Surveillance-Broadcast (ADS-B) and Traffic Information Service-Broadcast (TIS-B) Equipment Operating on the Radio Frequency of 1090 Megahertz (MHz), for 1090ES link equipment or TSO‑C154c, Universal Access Transceiver (UAT) Automatic Dependent Surveillance-Broadcast (ADS-B) Equipment Operating on Frequency of 978 MHz, for UAT link equipment. TSO-C166b is required in Class A airspace and either link can be used in all other airspace.

For more information about the FAA’s ADS-B program, visit https://www.faa.gov/nextgen/programs/adsb/.

§§ 91.225 and 91.227

Indicates new/changed information. Indicates new/changed information. Indicates new/changed information.

Table 10-9-2D.    Inspection Program and Programs Covering Other Maintenance, Preventive Maintenance, and Alterations

ITEM

INSPECTION PROGRAM AND PROGRAMS COVERING OTHER MAINTENANCE, PREVENTIVE MAINTENANCE, AND ALTERATIONS

REFERENCES (current editions)

1

Inspection Program and Programs Covering Other Maintenance, Preventive Maintenance, and Alterations. If the certificate holder is adding the same make, model, and series (M/M/S) aircraft that it is operating, verify proper correlation between the operator’s maintenance tasks and time limitations for its approved maintenance program.

If the certificate holder does not have prior operating experience with the M/M/S aircraft being evaluated, verify that the operator-developed maintenance program for aircraft and installed components are based on the manufacturer’s recommended baseline program (e.g., Maintenance Review Board Report (MRBR), Maintenance Planning Document (MPD), etc.) and other Federal Aviation Administration (FAA) requirements. In this manner, the continuing airworthiness of the aircraft and installed components is ensured, and only those tasks that are applicable and effective are performed. If the aircraft was operated under a different maintenance program by a previous operator, verify proper transition (bridging) of the previously accumulated times and/or cycles to the current certificate holder’s instructions for continued airworthiness (ICA).

The maintenance program must include damage-tolerance rating (DTR) evaluations and structural inspection requirements.

NOTE: Refer to the Maintenance Review Board (MRB) and/or Airworthiness Directives (AD), as applicable.

Airplane Configuration Process. Verify that the certificate holder has an aircraft configuration or similar process within its manual system, and that the process results in the aircraft meeting its type design or properly altered condition. Verify that the certificate holder’s inspection program and programs covering other maintenance, preventive maintenance, and alterations are acceptable to the Administrator before the aircraft is added to the operations specification (OpSpec) D085.

14 CFR part 91, § 91.409(h)

14 CFR part 119, § 119.49

14 CFR part 135, §§ 135.25 and 135.411

Volume 2, Chapter 4, Section 8

Volume 3, Chapter 43, Section 1

Volume 6, Chapter 2, Section 28

Volume 6, Chapter 2, Section 36

Advisory Circular (AC) 120-16, Air Carrier Maintenance Programs

AC 120-73, Damage Tolerance Assessment of Repairs to Pressurized Fuselages

2

Very High Frequency Omni-Directional Range Station (VOR) Equipment Checks for Instrument Flight Rules (IFR) Operations. Verify that the aircraft is included in the operator’s program. Ensure that the VOR equipment of the aircraft is maintained, checked, and inspected under an approved procedure, or is operationally checked within the preceding 30 calendar-days and was found to be within the limits of the indicated permissible bearing error set forth in § 91.171. Also see related Table 10-9-2C, Records, Item 4.

§ 91.171

§§ 135.25 and 135.411

Volume 6, Chapter 2, Section 28

3

High Intensity Radiated Field (HIRF)/Lightning Protection Maintenance Program. Verify that the aircraft is included and maintained in accordance with the certificate holder’s HIRF maintenance and inspection programs. Refer to the MRBR and Supplemental Type Certificate (STC).

§§ 135.25 and 135.411

Volume 3, Chapter 43, Section 1

Volume 6, Chapter 2, Section 28

AC 20-53, Protection of Aircraft Fuel Systems Against Vapor Ignition Caused by Lightning

AC 20-136, Aircraft Electrical and Electronic System Lightning Protection

AC 20-158, The Certification of Aircraft Electrical and Electronic Systems for Operation in the High-intensity Radiated Fields (HIRF) Environment

4

Air Traffic Control (ATC) Transponder Tests and Inspections. Verify that the aircraft is included and maintained in accordance with the certificate holder’s program and that the program included 24-month tests and inspections of the ATC transponder systems in accordance with 14 CFR part 43 appendix F. Tests and inspections should include altitude reporting equipment.

Part 43 appendix F

§§ 91.411 and 91.413

§§ 135.25 and 135.411

AC 20-131, Airworthiness Approval of Traffic Alert and Collision Avoidance Systems (TCAS II) and Mode S Transponders

5

Reduced Vertical Separation Minimums (RVSM). If authorized to conduct RVSM operations, verify that the aircraft conforms to its RVSM data package and that the aircraft is maintained in accordance with the certificate holder’s approved program.

§§ 91.3, 91.180, 91.703, and 91.706

Part 91 appendix G

Volume 4, Chapter 1, Section 5

Volume 4, Chapter 10, Section 1

AC 91-70, Oceanic and Remote Continental Airspace Operations

6

Flight Data Recorder System (FDRS). Verify that at a minimum, the certificate holder’s maintenance program meets the requirements of AC 20-141, Airworthiness and Operational Approval of Digital Flight Data Recorder Systems.

§ 91.609

§§ 135.25 and 135.411

Volume 4, Chapter 14, Section 8

AC 20-141

7

Underwater Locating Device (ULD). Verify that operational and battery capacity tests of each ULD were performed in accordance with the certificate holder’s Continuous Airworthiness Maintenance Program (CAMP).

§ 135.152

Volume 4, Chapter 14, Section 8

Volume 4, Chapter 14, Section 9

8

Corrosion Prevention and Control Program (CPCP). Verify that the certificate holder has a CPCP. This program defines the minimum requirements for preventing or controlling corrosion problems that may jeopardize continuing airworthiness of the aircraft.

To meet these requirements, operators must have effective corrosion prevention and control procedures incorporated into the maintenance program for all airplanes reaching or exceeding the implementation age. The level of corrosion found on Principal Structural Elements (PSE) determines the effectiveness of a corrosion control program for a given airplane area.

§§ 135.25 and 135.411

Volume 3, Chapter 43, Section 1

Volume 6, Chapter 2, Section 28

For all MSG – 3rd Task Force (MSG-3) and above aircraft, refer to the manufacturer’s MRBR and/or ADs, as applicable.

9

Engines, Auxiliary Power Unit (APU). Ensure the engines and APU are included and maintained in accordance with the operator’s current maintenance and inspection programs. Refer to the MRBR and/or ADs (as applicable).

§§ 135.25 and 135.411

Volume 2, Chapter 4, Section 8

Volume 3, Chapter 43, Section 1

Volume 6, Chapter 2, Section 28

AC 120-16

10

Lower Landing Minimums. If authorized to conduct Category II/III (CAT II/CAT III) Approach operations, verify that the aircraft conforms to, and is maintained in accordance with, the certificate holder’s approved program. (Refer to OpSpec C060.)

§§ 135.25, 135.78, and 135.411

Volume 2, Chapter 4, Section 8

Volume 3, Chapter 18, Section 5

Volume 4, Chapter 2, Section 11

AC 120-28, Criteria for Approval of Category III Weather Minima for Takeoff, Landing, and Rollout

AC 120-29, Criteria for Approval of Category I and Category II Weather Minima for Approach

11

Aircraft Network Security Program (ANSP). Obtaining operational authorization for an aircraft certified with a special condition (SC) related to security of the onboard computer network. (Refer to OpSpec D301.)

14 CFR part 125, §§ 125.23, 125.91, and 125.241

Volume 3, Chapter 61, Section 1

AC 119-1, Operational Authorization of Aircraft Network Security Program (ANSP)

Indicates new/changed information.

Table 10-9-2E.  Fuselage, Exterior, Engines, and Propellers

ITEM

FUSELAGE, EXTERIOR, ENGINES, AND PROPELLERS

REFERENCES (current editions)

1

Radome Area.

a. Inspect radome, erosion cap, and lightning diverter strips for condition and security.

b. If the radome internal area is accessible, do the following:

1) Inspect exposed electronic/electrical components for condition, security, and proper bonding/grounding (antennas, weather radar waveguide, cable and wire bundles, connectors, etc.).

2) Inspect the exposed airframe area (forward-pressure bulkhead) for condition, corrosion, damage, and repairs. When repairs are noted, including the radome, check the repair data at the certificate holder’s record section for Federal Aviation Administration (FAA)-approved or FAA‑accepted data.

14 CFR part 135, §§ 135.25 and 135.411

Volume 6, Chapter 2, Section 4

Advisory Circular (AC) 43-14, Maintenance of Weather Radar Radomes

2

Pitot Air Probes.

a. Inspect for proper installation, condition, and type. Probes must have a heat function (or equivalent means for preventing malfunctioning due to icing). Ports must be free of obstructions.

b. Visually inspect the critical surface areas around the probes for any irregularity that could impair the effectiveness of the probes. If repairs are noted, check the repair data at the certificate holder’s record section for FAA-approved data.

§§ 135.25, 135.158, 135.163, and 135.411

Volume 6, Chapter 2, Section 4

3

Static Pressure Ports.

a. Check ports for condition. Check that all openings are free of obstructions.

b. Visually inspect the critical surface areas around the probes for any irregularity that could impair the effectiveness of the ports.

c. If repairs are noted, check the repair data at the certificate holder’s record section for FAA-approved data.

§§ 135.25, 135.163, and 135.411

Volume 6, Chapter 2, Section 4

AC 120-73, Damage Tolerance Assessment of Repairs to Pressurized Fuselages

4

External Lights. Inspect the proper installation, condition, and weather sealing of all external lights and light lenses. Check the operation of the following:

a. Anticollision lights, fuselage.

b. Wing tip and tail white gas discharge lights (strobe lights).

c. Exterior emergency lights (if installed).

d. Landing lights.

e. Taxi lights.

f. Position lights.

g. Wing icing detection lights.

h. If high-intensity (strobe) lights are used, verify at the operator’s record repository for the latest luminosity check.

i. Wheel well lights (if installed).

§§ 135.25 and 135.411

Volume 6, Chapter 2, Section 4

AC 20-30, Aircraft Position Light and Anticollision Light Installations

AC 20-74, Aircraft Position and Anticollision Light Measurements

AC 43.13-2, Acceptable Methods, Techniques, and Practices—Aircraft Alterations

5

Antennas. Inspect for proper installation and condition, such as leading edge erosion and cracking of the composite covering. Pay particular attention to possible corrosion under antenna bases.

§§ 135.25 and 135.411

Volume 6, Chapter 2, Section 4

6

Miscellaneous Fuselage Sensors (e.g., Ice Detection, Total Air Temperature, Vibration). Inspect sensors for condition, security, and corrosion on fuselage skin.

§§ 135.25 and 135.411

Volume 6, Chapter 2, Section 4

7

Static Dischargers. Inspect for proper condition and security, and for the proper discharger types, quantities, and locations. Consult the appropriate aircraft documentation for the proper type.

Refer to Master Minimum Equipment List (MMEL) and Configuration Deviation List (CDL) for minimum required.

§§ 135.25 and 135.411

Volume 6, Chapter 2, Section 4

8

Aircraft Inspection (With Doors, Compartment Doors, and Service Panels Opened; Flaps and Slats Down).

a. Inspect the aircraft exterior for general condition, damage, corrosion, fluid leaks, etc. Check fuel drains, fuel vents, fuel filler caps, and underwing fuel filler hard point.

b. Check the security of attachment of control surfaces and corrosion prevention treatment application.

c. Check wing and tail leading edges for dents and erosion.

d. Check heating pads on top of wing surfaces above inboard fuel tanks for condition.

e. Examine joints, seams, and skin for wrinkles, bulges, fasteners, skin erosion, corrosion, and oxidation.

f. When dents are noted, verify at the operator’s record repository and/or the aircraft maintenance log that a limit check is performed and noted.

g. Check composite material panels for moisture contamination and bonding, delaminating, or separation of skin-bonding.

h. Check windshield wipers for condition, security, and operation.

i. Compare repair mapping with aircraft. Pay attention to critical areas.

j. If repairs are noted, check the repair data at the certificate holder’s record repository for FAA-approved data.

§§ 135.25 and 135.411

Volume 6, Chapter 2, Section 4

AC 20-116, Marking Aircraft Fuel Filler Openings With Color Coded Decals

9

Aircraft Painting.

a. Check for condition, flaking, and evidence of corrosion at seams and fasteners; and for filiform corrosion under painted surfaces.

b. Verify at the operator’s record repository that accepted materials and procedures were followed, including the balancing of flight control surfaces.

§§ 135.25 and 135.411

Volume 6, Chapter 2, Section 4

AC 120-27, Aircraft Weight and Balance Control

10

Identification of Aircraft. Verify that a fireproof identification plate or other approved marking is attached to the aircraft with all pertinent data as required by, and in accordance with, applicable 14 CFR parts.

14 CFR part 45, §§ 45.11 and 45.13

§§ 135.25 and 135.411

AC 45-2, Identification and Registration Marking

11

Name of Certificate Holder. Verify that the aircraft legibly displays the business name or certificate number appearing on the aircraft certificate holder’s operations specifications (OpSpecs). Ensure the display is clearly visible and readable to a person standing on the ground at any time except during flight.

14 CFR part 119, § 119.9

12

Placards, Markings, Exterior Exit Markings.

a. Check that all placards are properly installed at the location specified by the FAA-approved Airplane Flight Manual (AFM), aircraft type certification basis, applicable operating rules, and the operator’s manual.

b. Check that all placards and/or markings are not easily erased, disfigured, or obscured. Check that each passenger emergency exit is marked on the outside of the aircraft by a 2-inch contrasting colored band.

c. Check that instructions for the means of opening those exits from the outside are marked on the outside of each passenger emergency exit.

d. If the emergency exit is located only on one side of the fuselage, check that it has a conspicuous marking on the other side.

14 CFR part 91, § 91.9

§§ 135.25, 135.178, and 135.411

Volume 6, Chapter 2, Section 4

AC 20-88, Guidelines on the Marking of Aircraft Powerplant Instruments (Displays)

13

Exterior Escape Route.

a. Check that the surface of each emergency escape route is made of slip-resistant material.

b. Check general condition of emergency slip-resistant escape route.

§§ 135.25, 135.178, and 135.411

Volume 6, Chapter 2, Section 4

14

Windows.

a. For passenger compartment windows, inspect for general condition, security, visibility, scratches, crazing, and condensation.

b. For flight deck windshield, side windows, direct-view windows, or operable sliding windows, check for condition and delamination.

c. Check condition of windshield wipers.

§§ 135.25, 135.178, and 135.411

Volume 6, Chapter 2, Section 4

AC 25.775-1, Windows and Windshields

15

Doors (Cabin, Cargo Compartment, Emergency Escape, Service, and Access).

a. Inspect all exterior doors, hatches, and servicing access panels for general condition and installation.

b. Check for damage, corrosion, security of attachment, and the application of corrosion prevention treatment. Pay particular attention to doorjamb areas and door seals. Check doors for proper operation.

c. Check the hold open latches on floor-level doors for general condition and proper operation.

d. For aircraft with a ventral exit, check that it has provisions to prevent it from being opened during flight. For inward opening doors, check for a means to prevent crowding against the door.

e. Check that the emergency doors and/or hatches/plugs can be opened from the inside by the flightcrew, as well as from the outside of the aircraft in normal ground configuration by emergency rescue personnel.

f. Check viewing ports for damage, deterioration, distortion, and security to permit viewing the conditions outside the exit(s) when closed.

g. Check for a provision for a visual inspection of the door-locking mechanism to determine that doors are fully closed and locked (excluding inward-opening doors).

h. If repairs are noted, check the repair data at the certificate holder’s record repository for FAA-approved data.

i. Check for the appropriate amount and type of exits.

§§ 135.25 and 135.411

Volume 6, Chapter 2, Section 4

AC 25-17, Transport Airplane Cabin Interiors Crashworthiness Handbook

AC 25.783-1, Fuselage Doors and Hatches

16

Fuel Tank Impact Resistant Access Doors. Inspect for general condition, security, and position marking. (Refer to 14 CFR part 25, § 25.963.)

§§ 135.25 and 135.411

Volume 6, Chapter 2, Section 4

Engines

17

Engines, Mounting Structure, and Compartments.

a. Inspect for cleanliness, general condition, loose/missing equipment, breakage, signs of fluid leaks, corrosion, proper installation, and other indications of defects.

b. Check fire extinguishing system components and extinguishing agent indicators.

c. Inspect the visible inlet guide vanes and compressor and turbine blades for dents, erosion, nicks, and other irregularities. Check the electronic engine control (EEC)/Full-Authority Digital Engine Control (FADEC) unit (if installed) for general condition, corrosion, and security.

d. Check electrical wiring for condition, proper placement (routing), and security.

§§ 135.25 and 135.411

Volume 6, Chapter 2, Section 4

AC 43-206, Inspection, Prevention, Control, and Repair of Corrosion on Avionics Equipment

18

Engine Nacelles.

a. Check for general condition, dents, scratches, loose or missing fasteners, corrosion, erosion, etc.

b. Check acoustic panels for general condition.

§§ 135.25 and 135.411

Volume 6, Chapter 2, Section 4

AC 43-206

19

Thrust Reversers and Blocker Doors. Check for general condition, dents, corrosion, fluid leaks, proper installation, and indications of defects. If repairs are noted, verify at the operator’s records repository repair data for FAA-approved data.

§§ 135.25 and 135.411

Volume 6, Chapter 2, Section 4

20

Auxiliary Power Unit (APU).

a. Inspect the APU for cleanliness, fire containment shrouds, and seals for general condition.

b. Check exhaust ducts for general condition, signs of leaks, and proper mounting.

c. Check for loose/missing equipment, breakage, signs of fluid leaks, corrosion, proper installation, and indications of defects.

d. Check the APU EEC/FADEC unit (if installed) for general condition, corrosion, and security.

e. Check APU compartment for general condition, corrosion, and damage.

f. If the rear pressure bulkhead is visible, check for condition, corrosion, and evidence of damage and repairs.

g. Check the exposed airframe structure for general condition, corrosion, damage, and repairs.

h. Check the condition of the fire extinguishing system components and extinguishing agent indicators.

i. Check that the power cable(s) is isolated from flammable fluid lines, or shrouded by a nonmetallic, flexible conduit in addition to the cable insulation.

j. Check all wiring and power cables for proper attachment, routing, and security to the airframe structure.

§§ 135.25 and 135.411

Volume 6, Chapter 2, Section 4

AC 43-206

21

Identification of Engines.

a. Check for the presence of a fireproof identification plate or other approved marking on each engine, as required by the referenced data.

b. Verify the data with the operator’s supplied data sheet.

§§ 45.11 and 45.13

AC 45-2

AC 45-3, Installation, Removal, or Change of Identification Data and Identification Plates on Aircraft Engines

22

Identification of the APU.

a. If applicable, check for the presence of a fireproof identification plate or other approved marking containing the data required by the referenced data.

b. Verify the data with the operator’s supplied data sheet.

§§ 45.11 and 45.13

AC 45-2

AC 45-3

23

EECs Including APU FADEC.

a. If applicable, check for installation and security of the EEC and mounting hardware.

b. Check electrical cabling and connectors for general condition, corrosion, and security.

c. Verify the installation of proper version software at the operator’s records repository.

14 CFR part 33, § 33.28

AC 33.28-1, Compliance Criteria for 14 CFR § 33.28, Aircraft Engines, Electrical and Electronic Engine Control Systems

Propellers

24

Identification of Propellers, Propeller Blades, and Propeller Hubs.

a. Verify that each propeller, propeller blade, and propeller hub is identified in accordance with the referenced guidance material.

b. Verify the data with the operator’s supplied data sheet.

§§ 45.11 and 45.13

AC 45-2

25

Propeller Inspection.

a. Inspect the condition and security of spinner, blades, hub, pitch locks (if installed or visible), anti/deicing slip ring, brushes and wiring (if installed), boots and electrical wiring, etc.

b. Check composite blades for erosion, disbonding, and delamination, and check the ultraviolet coating for condition.

c. Check leading edges for condition and attachment.

d. For metal blades, check for general condition and leading edges for erosion, nicks, and dents.

e. Check the aircraft records for FAA-approved repair data.

AC 43-206

Indicates new/changed information. Indicates new/changed information. Indicates new/changed information. Indicates new/changed information. Indicates new/changed information. Indicates new/changed information. Indicates new/changed information. Indicates new/changed information. Indicates new/changed information. Indicates new/changed information. Indicates new/changed information. Indicates new/changed information. Indicates new/changed information. Indicates new/changed information.

Table 10-9-2F.  Fuselage Interior

ITEM

FUSELAGE INTERIOR

REFERENCES (current editions)

1

Aircraft Registration. Each aircraft must have at least one of the following documents inside it:

    An effective U.S. registration certificate issued to its owner;

    The second copy (pink copy) of the Aircraft Registration Application if a Certificate of Aircraft Registration has been applied for but has not yet been received; or

    A registration certificate issued under the laws of an International Civil Aviation Organization (ICAO) Member State displayed in accordance with the certificate holder’s requirements.

14 CFR part 47, § 47.31

14 CFR part 91, § 91.203

14 CFR part 135, § 135.25

Volume 6, Chapter 2, Section 4

FAA Order 8130.2, Airworthiness Certification of Aircraft

2

Airworthiness Certificate. Except as provided in § 91.715, there must be within the aircraft an appropriate and current airworthiness certificate. It must be the original (not a copy), and must be displayed at the cabin or flight deck entrance so that it is legible to passengers or crew, and is in accordance with the certificate holder’s requirements.

NOTE: For a foreign airworthiness certificate, check for the expiration date.

§§ 91.203 and 91.715

§ 135.25

Volume 6, Chapter 2, Section 4

Volume 8, Chapter 5, Section 1

3

Federal Communications Commission (FCC) Radio Station License. This is required for other-than-domestic operations. This license must be issued to the aircraft operator and must be updated if the addition of the aircraft results in the operator’s fleet exceeding the number of aircraft for which the license was issued.

NOTE: Requirement of FCC, ICAO Article 29, Documents Carried in Aircraft, and Article 30, Aircraft Radio Equipment.

(As required)

4

General Placards and Markings. Verify the presence and inspect the condition of cabin interior placards and markings in accordance with the certificate holder’s manual, Type Certificate Data Sheet (TCDS), Supplemental Type Certificate (STC), Airplane Flight Manual (AFM), and chapter 11 of the Aircraft Maintenance Manual (AMM).

§ 91.9

§§ 135.25 and 135.411

Volume 6, Chapter 2, Section 4

5

General Equipment Installation. Inspect the proper condition, security, and configuration of equipment and systems.

§§ 135.25 and 135.411

Volume 6, Chapter 2, Section 4

6

Flight Deck Voice Recorder. Large, turbine‑engine‑powered, or large pressurized airplanes with multiengine aircraft having a passenger seat configuration with six or more seats, must have an approved flight deck voice recorder installed. Check for proper condition (e.g., color of recorder case and reflective tape), security, and configuration.

§ 91.609

§ 135.151

Volume 4, Chapter 14, Section 9

7

Flight Data Recorder System (FDRS). Check for proper condition (e.g., color of recorder case and reflective tape), security, and configuration.

§ 91.609

Volume 4, Chapter 14, Section 8

8

Compartment Interiors/Fire Resistance.

a. Look on the backs of cushions to identify if the seats have been fire-blocked. The cushions must meet the requirements of 14 CFR part 25, § 25.853(c). Review documentation of flame testing. This includes material for walls, furnishings, and ceiling.

b. The following is excerpted from § 135.170(c):

“(c) Thermal/acoustic insulation materials. For transport category airplanes type certificated after January 1, 1958:

(1) For airplanes manufactured before September 2, 2005, when thermal/acoustic insulation is installed in the fuselage as replacements after September 2, 2005, the insulation must meet the flame propagation requirements of § 25.856 of this chapter, effective September 2, 2003, if it is:

(i) Of a blanket construction, or

(ii) Installed around air ducting.

(2) For airplanes manufactured after September 2, 2005, thermal/acoustic insulation materials installed in the fuselage must meet the flame propagation requirements of § 25.856 of this chapter, effective September 2, 2003.”

§ 25.853(c)

§ 135.170

Advisory Circular (AC) 20-178, Flammability Testing of Aircraft Cabin Interior Panels After Alterations

9

Fuselage Interior (Cabin and Equipment Compartments).

a. Inspect interior and compartments for cleanliness, general condition, loose and/or missing equipment, deterioration, leakage, corrosion, proper installations, and other indications of defects. Pay particular attention to control cables and fluid lines.

b. Inspect for the proper application of corrosion prevention treatments in the forward and rear pressure bulkheads, interior, and accessible under-floor areas.

§§ 135.25 and 135.411

Volume 6, Chapter 2, Section 4

Volume 6, Chapter 2, Section 6

10

Lavatory Placard. The lavatory must have a sign or placard stating, “Federal Law provides for a penalty of up to $2,200 as applicable, for tampering with the smoke detector installed in this lavatory.”

§ 135.127

Volume 6, Chapter 2, Section 4

11

Waste Receptacle. Each receptacle used for the disposal of flammable waste material must be fully enclosed, constructed of at least fire resistant materials, and must be able to contain fires likely to occur in it under normal use. The capability of the receptacle to contain those fires under all probable conditions of wear, misalignment, and ventilation expected in service must be demonstrated by test. Airworthiness Directive (AD) 74-08-09, Various Transport Category Airplanes, requires operators to inspect all lavatory paper and linen waste receptacle enclosure access doors and disposal doors for proper operation, fit, sealing, and latching for the containment of possible trash fires. A placard containing the legible words “No Cigarette Disposal” must be located on or near each disposal receptacle door.

14 CFR part 39

§ 91.417

AD 74-08-09

12

Ventilation. Where partitions between compartments have louvers or other means that allow air to flow between compartments, there must be a means convenient to the crew for closing the flow of air through the partitions, when necessary.

NOTE: Emphasize with new or altered interiors (STC).

Part 135 appendix A

13

Carriage of Cargo in Passenger Compartments.

a. Ensure that each compartment or area used for the stowage of cargo and/or baggage provides protection to the passengers and crewmembers from injury by its contents.

b. Ensure that there are provisions to prevent the cargo/baggage from becoming a hazard by shifting.

c. Ensure that a compartment used for stowage is placarded for its weight limits.

§ 135.87

Volume 3, Chapter 33, Section 6

AC 121-29, Carry-On Baggage

14

Galleys/Service Centers. Verify proper approval. Inspect the following: trash bin lids for fit, storage compartment restraints, stationary cart tie-downs, lower lobe equipment and restraints, lift operation, and galley supplies stowage.

§§ 135.25, 135.122, and 135.411

15

Stowage Compartments. Check weight restriction placards and the doors for proper latching, if applicable. Each compartment for the stowage of cargo, baggage, carry-on articles, and equipment (such as liferafts), and any other stowage compartment must be designed for:

a. Its placarded maximum weight of contents.

b. The critical load distribution at the appropriate maximum load factors corresponding to the specified flight and ground load conditions.

If the airplane has a passenger-seating configuration (excluding pilots’ seats) of 10 seats or more, each stowage compartment in the passenger cabin (except for under-seat and overhead compartments for passenger convenience) must be completely enclosed. There must be a means to prevent the contents in the compartments from becoming a hazard by shifting under the specified loads. For stowage compartments in the passenger and crew cabin, if the means used is a latched door, the design must consider in-service wear and deterioration.

§§ 135.25, 135.87, and 135.411

Volume 3, Chapter 33, Section 6

AC 121-29

16

Retention of Items of Mass in Passenger and Crew Compartments and Galleys. Means must be provided to prevent each item of mass (that is part of the airplane type design) in a passenger or crew compartment or galley from becoming a hazard by shifting under the appropriate maximum load factors corresponding to the specified flight and ground load conditions, and to the emergency landing conditions of § 25.561(b).

§§ 135.25, 135.87, 135.122, and 135.411

Volume 3, Chapter 33, Section 6

17

Pax Recovery Plan. Each certificate holder conducting domestic or flag operations must show that it has an approved system for obtaining, maintaining, and distributing to appropriate personnel current aeronautical data for each airport it uses to ensure a safe operation at that airport. The aeronautical data must include the following:

    Airports,

    Facilities, and

    Public Protection.

After February 15, 2008, for Extended Operations (ETOPS) beyond 180 minutes or operations in the North Polar area and South Polar area, this includes facilities at each airport or in the immediate area sufficient to protect the passengers from the elements and to see to their welfare.

AC 120-42, Extended Operations (ETOPS and Polar Operations), states: “A minimum of two cold weather anti‑exposure suits must be on board each airplane, so that outside coordination at a diversion airport with extreme climatic conditions can be accomplished safely. A short term MEL relief for this item may be granted provided the certificate holder has arranged ground support provisions for providing such protective clothing at alternate airports. The FAA may also relieve the certificate holder from this requirement during those periods of the year when the seasonal temperature makes the equipment unnecessary.”

The passenger recovery plan is approved in operations specification (OpSpec) B055 and states that airplanes are to be equipped with a minimum of two cold weather anti-exposure suits.

§§ 135.98 and 135.345

Volume 3, Chapter 18, Section 4

Volume 4, Chapter 1, Section 5

AC 120-42

OpSpec B055

18

Emergency Equipment for Extended Overwater Operations/Uninhabited Terrain Areas. Ensure the following for each item of emergency and flotation equipment:

a. Is regularly inspected in accordance with inspection periods established in the OpSpecs to ensure its condition for continued serviceability and immediate readiness to perform its intended emergency purposes.

b. Is readily accessible to the crew, and regarding equipment located in the passenger compartment, to passengers.

c. Is clearly identified and marked to indicate its method of operation.

d. Is stored in a compartment or container marked as to its contents. The compartment, container, or the item must indicate date of last inspection.

§ 135.167

Part 135 appendix G

Volume 3, Chapter 18, Section 4

OpSpec B055

AC 120-47, Survival Equipment for Use in Overwater Operations

 

Life Preservers. Ensure that the aircraft is equipped with an approved flotation means for each occupant. Each life preserver must:

a. Be equipped with an approved survivor locator light.

b. Be readily removable from the airplane.

§ 135.167

Volume 6, Chapter 2, Section 4

AC 120-47

 

Liferafts. Ensure the aircraft is equipped with enough liferafts of a rated capacity to accommodate the occupants of the airplane.

a. Ensure the rafts have approved survivor locator lights.

b. Ensure that the total capacity of the equipped rafts will accommodate all the passengers of the airplane in the event there is a loss of one raft with the largest capacity.

NOTE: Liferaft deviation allowed with OpSpec A013.

§ 135.167

Volume 6, Chapter 2, Section 4

AC 120-47

 

Survival Kits. Must be attached to each required liferaft.

§ 135.167

AC 120-47

 

Pyrotechnic Signaling Device. Ensure there is at least one device for each liferaft. Uninhabited terrain: suitable pyrotechnic devices.

§ 135.167

AC 120-47

 

Survival Emergency Locator Transmitters (ELT).

a. Check for proper approval.

b. Check for the expiration date.

c. Refer to § 135.167(c) for battery information.

§ 135.167

AC 120-47

19

Oxygen Equipment and Supply (Drop-Down Oxygen Masks). Verify:

a. Oxygen pressure vessel inspections comply with the Department of Transportation (DOT) (if applicable).

b. Continuous flow oxygen mask assemblies meet the requirements of Technical Standard Order (TSO)-C64b, Passenger Oxygen Mask Assembly, Continuous Flow.

c. Demand-type oxygen regulators meet the requirements of TSO-C89a, Crewmember Oxygen Regulators, Demand.

d. Hydrostatic test dates of all fixed oxygen bottles (if applicable).

e. Aircraft documents properly describe distribution of the oxygen masks in the passenger compartment, ensuring that the quantity of oxygen masks exceeds the number of seats by at least 10 percent.

f. The 10 percent of extra oxygen masks are uniformly distributed throughout the cabin.

g. Each lavatory oxygen-dispensing unit is equipped with two oxygen masks.

h. Each lavatory oxygen-dispensing unit above the flight attendant (F/A) jump seats is equipped with two oxygen masks. Since flightcrews have been made aware of AD 2011-04-09, Various Transport Category Airplanes, by the actions in the individual notices and these procedures were to be applied for a limited time (30 calendar-days) only, the procedures are no longer considered necessary and are not included in this AD. Flightcrews are still made aware of corrective actions taken as a result of this AD since maintenance activities are recorded and available to the flightcrew using existing maintenance procedures.

NOTE: Flightcrews are made aware of corrective actions taken as a result of an airplane lavatory(ies) modified by AD 2011‑04-09, since maintenance activities are recorded and available to the flightcrew using existing maintenance procedures.

i. All oxygen masks are designed to cover the nose and mouth, and are equipped with a means to secure the mask to a person’s face.

§ 91.211

§§ 135.91 and 135.157

49 CFR parts 171, 172, and 173, except § 173.24(a)(1)

49 CFR § 173.115(b)

Volume 6, Chapter 2, Section 4

TSO-C64b

TSO-C89a

20

Emergency Equipment. Check to ensure that each item of emergency and flotation equipment listed below:

a. Is readily accessible to the crew and, regarding equipment located in the passenger compartment, to passengers.

b. Is clearly identified and clearly marked to indicate its method of operation.

c. Is in a compartment or container marked as to its contents; and the compartment, container, or the item must indicate the date of last inspection.

d. Meets preflight requirements per the F/A manual and/or the Flight Operations Manual (FOM), as applicable.

§§ 135.25 and 135.411

Volume 6, Chapter 2, Section 4

 

Portable Oxygen Bottles (POB). Check:

a. That the required number(s) of POBs are on board and that the POBs provide oxygen flow of at least 4 liters per minute, but not less than 2 liters per minute.

b. That each POB has its own mask and tubing, and that the crew can determine if oxygen is being delivered.

c. That the continuous flow oxygen mask assemblies meet the requirements of TSO-C64b.

d. That the oxygen pressure vessel inspections comply with the DOT.

e. The hydrostatic test dates.

§§ 135.89, 135.91, and 135.157

 

Flotation Devices. Verify that:

a. The aircraft is equipped with an approved (TSO-C72c, Individual Flotation Devices) flotation means for each occupant (includes lap children).

b. The flotation means are within easy reach of each seated occupant.

c. The flotation means are readily removable from the airplane.

§ 91.205

AC 20-56, Marking of TSO-C72b Individual Flotation Devices

 

Hand Fire Extinguishers.

a. Ensure that each extinguisher is an approved type, and that the type and quantity of extinguishing agent is the most suitable for the kinds of fires that are likely to occur in the compartment.

b. At least one hand fire extinguisher must be provided and conveniently located on the flight deck for use by the flightcrew.

Passenger Compartment.

a. At least one hand fire extinguisher must be conveniently located in the passenger compartment of each airplane accommodating more than 6 but less than 31 passengers, and at least two hand fire extinguishers must be conveniently located in the passenger compartment of each airplane accommodating more than 30 passengers.

§ 135.155

Volume 6, Chapter 2, Sections 4 and 8

AC 20-42, Hand Fire Extinguishers for Use in Aircraft

 

Portable Lights. Ensure that the aircraft is equipped with a flashlight stowage provision that is accessible from each F/A seat.

§ 135.178

 

Protective Breathing Equipment (PBE).

a. If there is a Class A, B, or E cargo compartment, ensure that PBE is installed for the use of appropriate crewmembers.

b. Ensure that PBE is installed in each isolated, separate compartment in the airplane, including upper and lower lobe galleys, in which crewmember occupancy is permitted during flight for the maximum number of crewmembers expected to be in the area during any operation. (Refer to § 25.1439 for requirements.)

c. Ensure the PBE meets the requirements of TSO-C99a, Flight Deck (Sedentary) Crewmember Protective Breathing Equipment.

d. Ensure the PBE meets the preflight requirement in the F/A manual or FOM.

§ 25.1439

Volume 6, Chapter 2, Section 4

21

First Aid Kits.

a. First aid kits for treatment of injuries likely to occur in flight or in minor accidents must be provided. Ensure the minimum number of first aid kits are on board.

b. Ensure the first aid kits meet the contents that are required by § 135.177.

c. Ensure that the first aid kits meet the preflight requirements in the F/A manual or FOM.

NOTE: Arm and leg splints may not fit in the first aid kit. They are to be stowed in a readily accessible location that is near the kit.

§ 135.177

Volume 6, Chapter 2, Section 4

AC 121-33, Emergency Medical Equipment

22

Passenger Seats, Berths, Safety Belts, and Harnesses. Verify that:

a. Seats do not block the emergency escape exit.

NOTE: Verify seat backs are not capable of reclining to interfere with passenger egress.

b. Seats are secure in seat track (random sample).

c. Seat break-over pressure is in accordance with operator’s maintenance program (random sample).

d. The “Fasten Seatbelt While Seated” placards are viewable from all seats.

e. Seatbelts have metal-to-metal latches and are in good condition (random sample).

f. Each seat, berth, safety belt, and harness (if installed) is designed so that a person properly using these devices will not suffer serious injury in an emergency landing.

g. Each passenger seat or berth is equipped with a safety belt (TSO-C22g, Safety Belts) with a metal-to-metal latching device.

h. Each seat and berth is normally approved by TSO‑C39c, 9g Transport Airplane Seats Certified by Static Testing, or other approved methods. For sideward-facing seats, ensure that a safety belt and shoulder harness (TSO‑C114, Torso Restraint Systems) will prevent the head from contacting any object that would injure the person sitting in such a seat.

i. Each occupant is protected from head injury by a safety belt when there are no objects within head strike range that would cause injury. Ensure a safety belt plus a cushioned rest supports the arms, shoulders, head, and spine.

j. If the seat backs do not provide a firm handhold, there is a handgrip or rail along each aisle (seat back break-over).

k. Any projecting object that could cause injury is padded to ensure that people who are seated or moving about the airplane in normal flight will not be injured.

l. There are no more than three seats on each side of the aisle if the aircraft has a single aisle.

§ 91.107

§§ 135.25, 135.128, and 135.411

Volume 6, Chapter 2, Section 8

23

Cabin Attendant Seats, Berths, Safety Belts, and Harnesses. Pull the jump seat down to ensure it retracts (those in path of exits). The seats should be positioned so that when not in use, they will not interfere with the use of the passageways and exits.

a. If applicable, ensure that the jump seat retracts automatically.

b. Ensure that F/A jump seats are in the passenger compartment near approved floor-level emergency exits, unless another location has been approved.

c. Ensure that each F/A jump seat position is equipped with a combination shoulder harness and lap belt that has a single-point, metal-to-metal latching system.

d. Inspect seatbelts for proper approval (e.g., TSO-C22g or equivalent), metal-to-metal latching, and general condition.

e. Ensure the torso restraint meets the requirements of TSO-C114 or equivalent.

f. Ensure that the shoulder harness/lap belt has a means to be secured when not in use to prevent rapid egress in an emergency.

g. Ensure that the F/A, when seated, has a direct view of the cabin that they are responsible for without compromising their proximity to the floor-level exit.

h. Ensure that the F/A jump seats are located in an area that would minimize the probability that the occupants would suffer injury by being struck by items that were dislodged from service areas, stowage compartments, or service equipment.

i. If the aircraft was manufactured after March 6, 1980, verify that F/A jump seats provide a direct view of the cabin area for which the occupant of each of the seats is responsible. Direct view is defined as a view (without head movement) of at least 50 percent of the entire passenger seating areas, at least 25 percent of any zone, and 100 percent of passenger aisles.

§ 135.128

AC 25.785-1, Flight Attendant Seat and Torso Restraint System Installations

24

Passenger Safety Information Briefing Cards. While on board the aircraft, perform a random sampling of the passenger briefing cards to ensure its proper distribution, that it is conveniently located for each passenger, and that the card:

a. Includes information that is pertinent to that type and model of aircraft.

b. Contains diagrams of and methods of operating the emergency exits. Ensure that the cards concur with the placards located on and/or near the emergency exits.

c. If applicable, contains instructions necessary for the use of emergency equipment.

d. No later than June 12, 2005, for scheduled Commuter passenger-carrying flights, include the sentence, “Final assembly of this aircraft was completed in [INSERT NAME OF COUNTRY].”

§ 135.117

Volume 6, Chapter 2, Sections 4 and 8

AC 121-24, Passenger Safety Information Briefing and Briefing Cards

25

“Fasten Seatbelt” Signs. Signs that notify when seatbelts should be fastened and that are installed to comply with the operating rules of this chapter must be operable by a member of the flightcrew, and when illuminated, must be legible under all probable conditions of cabin illumination to each person seated in the cabin. Symbols that clearly express the intent of the sign or placard may be used in lieu of letters.

§ 135.178

26

Doors (Other than Flight Deck). There must be means for direct visual inspection of the locking mechanism by crewmembers to determine whether external doors and exits, for which the initial opening movement is outward, are fully locked. In addition, there must be a visual means to signal to crewmembers when normally used external doors are closed and fully locked.

Part 135 appendix A

27

Door Placard. A placard is required on each door that is the means of access to a required passenger emergency exit, to indicate that it must be open during takeoff and landing.

§ 135.178

28

Emergency Exits.

a. Ensure that the number of emergency exits meets or exceeds requirements of the passenger seating configuration.

b. If applicable, ensure that the step-down distance for Types II, III, and IV exits meet § 25.809.

c. For an airplane that is required to have more than one emergency exit for each side of the fuselage, no passenger exit may be more than 60 feet from any adjacent passenger emergency exit on the same side, same deck, as measured parallel to the airplane’s longitudinal axis between the nearest exit edges.

d. A ventral or tailcone exit must be designed and constructed so that it cannot be opened during flight. It must be marked with a placard that is readable from 30 inches away. The placard must be placed conspicuously near the means for opening the exit; it must state that the exit was designed and constructed so that it cannot be opened during flight.

e. Passenger compartment emergency exits that are in excess of the minimum number of required emergency exits must be readily accessible and meet all of the applicable provisions of § 135.178.

§ 135.178

AC 25-17, Transport Airplane Cabin Interiors Crashworthiness Handbook

29

Emergency Evacuation. Ensure that each crew and passenger area has an emergency means to allow rapid evacuation in crash landings with landing gear extended or retracted. (Refer to § 25.803.)

a. Passageways that lead to emergency exits must be unobstructed.

b. There must be adequate space to allow crewmember(s) to assist in the evacuation of passengers.

§ 135.178

30

Emergency Exit Markings. Verify that:

a. Each passenger emergency exit, its means of access, and its means of opening must be conspicuously marked. Means must be provided to assist occupants in locating exits in conditions of dense smoke.

b. The identity and location of each passenger emergency exit must be recognizable from a distance equal to the width of the cabin.

c. A sign visible to occupants approaching along the main aisle must indicate the location of each emergency exit.

d. There must be a locating sign:

1) Above the aisle near each over-the-wing passenger emergency exit, or at another ceiling location if it is more practical because of low headroom.

2) Next to each floor-level passenger emergency exit (one sign may serve two exits if both can be readily seen from the sign).

3) On each bulkhead or divider that prevents fore and aft vision along the passenger cabin (if this is not possible, the sign may be placed at another appropriate location).

e. Each passenger emergency exit locator sign and each passenger emergency exit marking sign must have red letters at least 1 inches high on an illuminated white background.

NOTE: The above colors can be reversed.

Emergency Exit Operating Handles.

a. For an aircraft in which the type certification (TC) was filed before May 1, 1972, the location of each passenger emergency exit operating handle, and instructions for opening the exit, must be shown by a marking on or near the exit that is readable from 30 inches away.

b. For Types I and II emergency exits with a locking mechanism released by rotary motion of the handle, the instructions must be shown by:

1) A red arrow with a shaft at least inch wide and a head twice the width of the shaft.

2) The word “open” in red letters, 1 inch tall, placed horizontally near the head of the arrow.

c. Each Type A, Type B, Type C, Type I, or Type II passenger emergency exit operating handle must be self‑illuminated or be conspicuously located and well illuminated by the emergency lighting even in conditions of occupant crowding at the exit.

d. Type III exits must be placarded with the weight of the exit and indicating an appropriate location to place the hatch after removal.

§ 135.178

Volume 6, Chapter 2, Sections 4 and 8

31

Emergency Lighting.

a. Inspect the interior and exterior emergency lighting and escape path markings to the applicable airworthiness and operating rules, and to its approved configuration (STC, TC, etc.).

b. Verify the system is designed so that each light is manually operable, both from the flight deck and from a point in the passenger cabin that is readily accessible to the F/A seat.

c. The lights must be safeguarded to prevent inadvertent operation.

d. Verify that each light has a flight deck control device that has “on,” “off,” and “armed” positions.

e. There must be a flightcrew warning light that illuminates when power is on in the airplane and the emergency lighting control device is not armed.

f. Ensure that the system, when activated, illuminates each passenger exit marking and locating sign, and includes floor proximity lighting emergency escape path markings that meet the requirements of § 25.812.

§ 135.178

AC 25.812-1, Floor Proximity Emergency Escape Path Marking

AC 25.812-2, Floor Proximity Emergency Escape Path Marking Systems Incorporating Photoluminescent Elements

32

Emergency Evacuation Assist Means. Verify that each exit (other than over-wing exits) that is higher than 6 feet from the ground has an approved means to assist the occupants to the ground (slides, ramp/slides, etc.). For floor-level exits, verify that:

a. Slide-bottle pressures are within acceptable levels.

b. Slide containers are properly marked for content (as applicable).

c. Slides meet the requirements of TSO-C69c, Emergency Evacuation Slides, Ramps, Ramp/Slides, and Slide/Rafts.

§ 25.810

§ 135.178

33

Crewmember Interphone System. For airplanes with a seating capacity for more than 19 passengers, verify the installation of a crewmember interphone system that meets the requirements of the applicable airworthiness and operating rules.

§ 135.150

34

Public Address (PA) System. For airplanes with a seating capacity for more than 19 passengers, verify installation of an approved PA system that meets the requirements of the applicable airworthiness and operating rules.

§ 135.150

35

Automatic Type ELT. Verify that the unit is approved (e.g., TSO-126b, 406 MHz Emergency Locator Transmitter (ELT)) and properly installed for those operations not exempt from the applicable operating rule. For new installations after June 21, 1995, the installed unit may not have been approved under TSO-C91a, Emergency Locator Transmitter (ELT) Equipment.

§ 91.207

TSO-126b

Indicates new/changed information. Indicates new/changed information. Indicates new/changed information. Indicates new/changed information. Indicates new/changed information. Indicates new/changed information.

Table 10-9-2G.  Flight Deck

ITEM

FLIGHT DECK

REFERENCES (current editions)

1

Two-Way Radio Communications Systems. For 14 CFR part 25 aircraft, verify the installation of two complete two‑way radio communications systems, with controls for each accessible from each pilot station, designed and installed so that failure of one system will not preclude operation of the other system. The systems must include two microphones and two headsets (or one headset and one speaker).

For non-part 25 aircraft, verify that the installation meets the basic requirements for at least one complete radio communications system for instrument flight rules (IFR) operations. For overwater and extended overwater operations, two complete communication systems must be installed. Those systems must include two microphones and two headsets (or one headset and one speaker). For extended overwater operations, the two systems must be independent.

14 CFR part 91, § 91.205

14 CFR part 135, § 135.161

2

Two-Way Radio Communications System (or Other Means of Communication Approved by the Administrator). For communications between each airplane and appropriate air traffic control (ATC) facility.

§ 91.205

§§ 135.161 and 135.165

3

Radio Navigation Systems. For part 25 aircraft, verify the installation of two-radio navigation systems, with controls for each accessible from each pilot station, designed and installed so that failure of one system will not preclude operation of the other system. Notwithstanding the above, for all aircraft, verify the installation of the equipment required by the referenced operating rules and the operations specifications (OpSpecs) for specific operational approvals.

§ 91.205

§ 135.165

4

Collision Avoidance System. Unless otherwise authorized by the Administrator, after December 31, 1995, no person may operate a turbine-powered airplane that has a passenger seat configuration, excluding any pilot seat, of 10 to 30 seats unless it is equipped with an approved Traffic Alert and Collision Avoidance System (TCAS). If a TCAS II system is installed, it must be capable of coordinating with TCAS units that meet Technical Standard Order (TSO)-C119, Traffic Alert and Collision Avoidance System (TCAS) Airborne Equipment, TCAS II with Hybrid Surveillance.

§ 91.221

§ 135.180

Volume 4, Chapter 14, Section 2

Advisory Circular (AC) 20-131, Airworthiness Approval of Traffic Alert and Collision Avoidance Systems (TCAS II) and Mode S Transponders

5

ATC Transponder. Verify the installation of a transponder that meets the requirements of § 91.215. If installed on or before January 1, 1992, the transponder must meet TSO‑C74b, Airborne ATC Transponder Equipment; TSO‑C74c, Airborne ATC Transponder Equipment, as appropriate (provided that the equipment was manufactured before January 1, 1990); or the appropriate class of TSO‑C112, Air Traffic Control Radar Beacon System/Mode Select (ATCRBS/Mode S) Airborne Equipment, (Mode S). If installed after January 1, 1992, the transponder must be the appropriate class of TSO-C112 (Mode S).

NOTE: “Installation” does not include temporary installation of TSO-C74b or TSO-C74c (as appropriate) substitute equipment during maintenance of the permanent equipment, reinstallation of equipment after temporary removal for maintenance, or for fleet operations, installation of equipment in a fleet aircraft after removal of the equipment for maintenance from another aircraft in the same operator’s fleet.

§ 91.215

§ 135.143

Volume 4, Chapter 14, Section 2

AC 91-50, Importance of Transponder Operation and Altitude Reporting

6

Airborne Weather Radar System. No person may operate a large transport category aircraft in passenger-carrying operations unless approved airborne weather radar equipment is installed in the aircraft.

§ 135.175

7

Radio Altimeter (RA). Verify that the installation meets the requirements of the Airplane Flight Manual (AFM) and approved Category II (CAT II) Approach /Category III (CAT III) Approach program(s), as applicable.

§§ 135.25 and 135.411

AC 120-28, Criteria for Approval of Category III Weather Minima for Takeoff, Landing, and Rollout

AC 120-29, Criteria for Approval of Category I and Category II Weather Minima for Approach

8

Global Positioning System (GPS). Verify that installations meet appropriate system descriptions, operational procedures, and limitations in the AFM/Airplane Operations Manual (AOM), as applicable. Also verify that the software version meets the AFM/AOM and certificate holder’s requirements. Ensure the aircraft conforms to the appropriate approved documents.

§§ 135.25 and 135.411

AC 20-138, Airworthiness Approval of Positioning and Navigation Systems

9

Terrain Awareness and Warning System (TAWS).

a. Verify that all turbine-powered airplanes manufactured after March 29, 2002, are equipped with a Federal Aviation Administration (FAA)-approved TAWS. The installation must also include an approved terrain situational awareness (SA) display. All turbine-powered airplanes manufactured on or before March 29, 2002, must be equipped as described above by March 29, 2005.

b. Verify the installation of proper operational and terrain database software versions, and that the AFM/AOM contains appropriate procedures for use of the system and proper flightcrew reaction in response to the system’s audio and visual warnings.

c. Verify all TAWS functions required to meet TSO‑C151, Terrain Awareness and Warning Systems (TAWS), are operable. Pay particular attention to the 500‑foot altitude callout.

§ 91.223

§§ 135.25, 135.154, and 135.411

TSO-C151

 

Helicopter Terrain Awareness and Warning System (HTAWS). After April 24, 2017, no person may operate a helicopter in helicopter air ambulance (HAA) operations unless that helicopter is equipped with an HTAWS that meets the requirements in TSO-C194, Helicopter Terrain Awareness and Warning System (HTAWS), and Section 2 of RTCA DO-309, Minimum Operational Performance Standards (MOPS) for Helicopter Terrain Awareness and Warning System (HTAWS) Airborne Equipment.

§ 135.605

10

Instrument Arrangement, Visibility, and Markings.

a. Verify the arrangement and visibility of flight and navigation instruments in accordance with the applicable regulations.

b. Verify that displayed information and ranges are appropriate to the aircraft and the installed equipment.

c. Verify that when markings are on the cover glass of the instrument, there is a means to maintain the correct alignment of the glass cover with the face of the dial.

d. Verify appropriate powerplant instrument markings.

§ 91.205

§§ 135.25 and 135.411

11

Electronic Flight Information Systems (EFIS) and Electronic Centralized Aircraft Monitoring (ECAM). Verify display/pictures in the book match the aircraft’s AFM/AOM and current software configuration/revision date.

§§ 135.25 and 135.411

AC 25-11, Electronic Flight Displays

12

Instrument Requirements (Equipment Requirements).

a. Airspeed Indicating System. Verify the installation of an approved instrument at each pilot station that is calibrated in knots, and that each airspeed limitation and item of related information in the AFM and pertinent placards are expressed in knots. The system must include a heated pitot tube or equivalent means for preventing malfunctioning due to icing, and must meet all pertinent airworthiness standards.

b. Sensitive Altimeter. Verify installation of an approved instrument at each pilot station. The instruments must be adjustable for barometric pressure.

c. Sweep-Second Hand Clock. Verify the installation of an approved clock displaying hours, minutes, and seconds with a sweep-second pointer, digital presentation, or approved equivalent.

d. Standby Horizon Additional Attitude Instrument. Verify that, if required by 14 CFR part 121, § 121.305(j), an additional approved third such instrument is installed in accordance with § 121.305(k). (Refer to § 135.149(c).)

e. Gyroscopic Bank and Pitch Indicator (Artificial Horizon, Attitude Indicator, etc.). Verify the installation of an approved instrument at each pilot station.

f. Free Air Temperature Indicator. Verify the installation of an approved free air temperature indicator or an air temperature indicator that provides indications that are convertible to free air temperature.

g. Gyroscopic Rate-of-Turn Indicator. Verify that the installation of an approved instrument at each pilot station is combined with an integral slip/skid indicator (turn and bank indicator), except that only slip/skid indicators are required when a third attitude instrument system is installed in accordance with § 121.305(k). (Refer to § 135.149(c).)

h. Gyroscopic Direction Indicator. Verify the installation of an approved directional gyro, or equivalent, at each pilot station.

i. Vertical Speed (Rate of Climb) Indicator. Verify the installation of approved instruments at each pilot station.

j. Magnetic Compass. Verify the installation meets the approved TSO or other approved installation documents (refer to § 91.205 and 14 CFR part 23, § 23.2610).

§§ 91.205, 91.217, and 91.219

§§ 135.25, 135.149, 135.159, 135.163, and 135.411

Part 135 appendix A

AC 43-215, Standardized Procedures for Performing Aircraft Magnetic Compass Calibration

 

Radio Altimeter (RA) Requirements. After April 24, 2017, no person may operate a rotorcraft unless that rotorcraft is equipped with an operable FAA-approved RA, or an FAA-approved device that incorporates an RA, unless otherwise authorized in the certificate holder’s approved minimum equipment list (MEL).

§ 135.160

13

Speed Warning Device. Verify installation of an aural speed warning device on turbine-engine-powered airplanes, and airplanes with a maximum operating limit speed (VMO/MMO) greater than 0.8 demonstrated flight diving speed (VDF/MDF) or 0.8 VDF/MDF. The speed warning device must give effective aural warning (differing distinctively from aural warnings used for other purposes) to the pilots, whenever the speed exceeds VMO plus 6 knots or MMO plus 0.01. The upper limit of the production tolerance for the warning device may not exceed the prescribed warning speed.

§ 91.603

§§ 135.25 and 135.411

14

Automatic Pilot System. Verify that indicators and controls meet applicable airworthiness standards, including the requirement that quick release (emergency) controls must be on both control wheels, on the side of each wheel opposite the throttles. Verify that the AFM (and certificate holder’s AOM, if applicable) show minimum altitude for use of autopilot.

NOTE: If the certificate holder is authorized for CAT II or CAT III operations, the aircraft autopilot can be used for lower altitudes when approved by OpSpecs.

§ 135.93

15

Instrument Lighting. Verify that instrument lights provide enough light to make each required instrument, switch, or similar instrument easily readable and installed so that the direct rays are shielded from flightcrew members’ eyes and that no objectionable reflections are visible to them. There must be a means of controlling the intensity of illumination unless it is shown that non-dimming instrument lights are satisfactory.

§ 135.159(f)(2))

16

Pitot Heat Indication Systems. Verify that the indication system incorporates an amber light that is in clear view of a flightcrew and that is designed to alert the flightcrew if the pitot heating system is switched off, or the pitot heating system is switched on, and any pitot tube heating element is inoperative.

§ 135.158

17

Required Powerplant Instruments. Verify the installation of approved instruments as listed below:

a. Fuel pressure indicator for each engine and either an independent fuel pressure warning device for each engine, or a master warning device for all engines with a means for isolating the individual warning circuits from the master warning device.

b. Fuel flow indicator for each engine not equipped with an automatic altitude mixture control.

c. Fuel quantity indicator for each fuel tank to be used.

d. Oil pressure indicator for each engine.

e. Oil quantity indicator for each oil tank.

NOTE: Indicator may not always be located on the flight deck.

f. Oil temperature indicator for each engine.

g. Oil pressure warning means for each engine.

h. Tachometer for each engine. For turbine engine-powered aircraft, the indicators must display speed rotors (i.e., N1, N2, N3) that have established limiting speeds.

i. Augmentation liquid quantity indicator for each tank (if applicable).

j. An approved means to ensure prompt detection of a fire in designated fire zones (engine or auxiliary power unit (APU) compartments for parts 23 and 25 aircraft). There must also be a means to allow the crew to check, in-flight, the functioning of each fire detector electric circuit.

k. Reverse pitch indication for each reversible propeller (if applicable).

l. Gas temperature (e.g., exhaust gas temperature (EGT)) indicator for each turbine engine (if applicable).

m. Engine starter indication for each turbine engine‑powered part 25 aircraft (if applicable).

n. Ice protection system indication for each turbine engine (if applicable).

o. Fuel filter bypass indication for each turbine engine (if applicable).

p. Oil strainer or filter warning indication for each turbine engine (if no bypass is installed) to warn the flightcrew of the occurrence of contamination of the strainer or filter before it reaches maximum capacity (if applicable).

q. A means to indicate proper functioning of any heater(s) used to prevent ice clogging of fuel system components.

r. Thrust (or directly related (e.g., N1)) indicator for each turbojet or turbofan engine (if applicable).

s. Thrust reversing indicator for each engine using a thrust-reversing device, to indicate to the flightcrew when the thrust-reversing device is in the reverse thrust position (if applicable).

t. Rotor system unbalance indicator for part 25 turbojet‑powered aircraft (if applicable).

u. Torque indication for each turbine propeller-powered aircraft engine (if applicable).

v. Propeller position indication for each propeller of turbopropeller-powered aircraft (if applicable). For airplanes equipped with fluid systems (other than fuel) for thrust or power augmentation, an approved means must be provided to indicate to the flightcrew the proper functioning of that system, if applicable.

w. For part 23 turbine-engine-powered aircraft, a fuel low level warning means for any fuel tank that should not be depleted of fuel in normal operations (if applicable).

x. Carburetor air temperature indicator.

y. For air-cooled engines, a cylinder head temperature indicator for each engine.

§ 91.205

§§ 135.25 and 135.411

18

Takeoff Warning System. Verify the installation of a takeoff warning system.

Part 25, § 25.703

19

Flap Operated Landing Gear Warning Device. The following is excerpted from part 135 appendix A:

“Airplanes having retractable landing gear and wing flaps must be equipped with a warning device that functions continuously when the wing flaps are extended to a flap position that activates the warning device to give adequate warning before landing, using normal landing procedures, if the landing gear is not fully extended and locked. There may not be a manual shut off for this warning device. The flap position sensing unit may be installed at any suitable location. The system for this device may use any part of the system (including the aural warning device) provided for other landing gear warning devices.”

Part 135 appendix A

20

Flight Deck Inspection. Inspect the flight deck for cleanliness, poor condition, loose/missing equipment, deterioration, breakage, leakage, corrosion, proper installation, and other indications of defects. Pay particular attention to windshields, windows, paneling, flooring, controls, lighting, and wiring installations.

§§ 135.25 and 135.411

21

Flight Deck Interiors/Fire Resistance. Examine seat dress cover assemblies for meeting the flammability requirements of § 25.853(a). Review documentation of flame testing (AC 25.853-1, Flammability Requirements for Aircraft Seat Cushions).

§ 135.170

22

Flightcrew Emergency Exits. For airplanes in which the proximity of passenger emergency exits to the flightcrew area does not offer a convenient and readily accessible means of evacuation for the flightcrew, and for all airplanes having a passenger-seating capacity greater than 20:

a. Verify that flightcrew exits are located in the flightcrew area.

b. Verify that such exits are of sufficient size and are located to permit rapid evacuation by the crew. One exit must be provided on each side of the airplane, or a top hatch may be provided. Each exit must encompass an unobstructed rectangular opening of at least 19 by 20 inches, unless satisfactory exit utility can be demonstrated by a typical crewmember.

§ 23.2330

§ 25.807(j)

§§ 135.25 and 135.411

23

Emergency Equipment. Verify that each item of emergency and flotation equipment meet the following requirements:

a. Be inspected regularly in accordance with inspection periods established in the OpSpecs to ensure its condition for continued serviceability and immediate readiness to perform its intended duty.

b. Be readily accessible to the crew.

c. Be clearly identified and marked to indicate its method of operation.

d. When carried in a compartment or container, be carried in a compartment or container marked as to contents. The compartment or container, or the item itself, must be marked as to date of last inspection.

§§ 135.25 and 135.411

Volume 6, Chapter 2, Section 4

24

First Aid Kit (If Located on Flight Deck). See the requirements of Table 10-9-2F, Fuselage Interior, Item 21.

§ 135.177

25

Hand Fire Extinguishers for Flightcrew. Verifythat at least one hand fire extinguisher is conveniently located on the flight deck for use by the flightcrew. The type and quantity of extinguishing agent must be suitable for the kinds of fires likely to occur in the compartment where the extinguisher is intended to be used. Check for fire extinguisher security, pressure, hydrostatic test dates, and seal.

§§ 135.25, 135.155, and 135.411

AC 20-42, Hand Fire Extinguishers for Use in Aircraft

26

Oxygen Equipment and Supply.

a. Verify that the aircraft is equipped with oxygen equipment per §§ 25.1441 through 25.1453.

b. Oxygen/fire extinguisher pressure vessel inspections must comply with Title 49 of the Code of Federal Regulations (49 CFR) part 180, § 180.205, Department of Transportation (DOT), or United States Coast Guard (USCG) requirements.

c. Check all portable and fixed oxygen bottles and fire bottles for hydrostatic test dates.

§ 91.211

§§ 135.25, 135.91, and 135.411

27

Seats, Berths, Safety Belts, and Harnesses. Verify that each seat at a flight deck station has a restraint system consisting of a combined safety belt and shoulder harness with a single-point release that permits the flight deck occupant, when seated with the restraint system fastened, to perform all of the necessary flight deck functions.

§ 135.171

28

Flight Deck Check Procedures Checklist. Verify that flight deck check procedures (checklists) are current and complete, properly approved, and limited to action or verification items. The operator’s manual and training programs must thoroughly describe required actions and decisions for crewmembers performing a checklist.

§ 135.83

29

Observer Seat. Verify installation, security, and condition of flight deck observer seat and all required peripheral equipment.

§ 135.76

30

Placards. Verify that manufacturer-required placards are installed. Refer to chapter 11 of the Aircraft Maintenance Manual (AMM) for data. All placards required by either the approved AFM, the applicable operating rules, operators’ placard manual, or the certification basis must be installed in the airplane. Refer to the Type Certificate Data Sheet (TCDS); Supplemental Type Certificates (STC); AC 20-88, Guidelines on the Marking of Aircraft Powerplant Instruments (Displays); and the AMM.

§ 91.9

§§ 135.25 and 135.411

31

Portable Electronic Devices (PED) and Electronic Flight Bags (EFB).

a. Verify that the certificate holder has properly determined that permitted PEDs and/or EFBs will not cause interference with the navigation and communication systems of the subject aircraft.

b. Verify that the software version meets the AFM/AOM and certificate holder’s requirements. (Refer to AC 120-76, Authorization for Use of Electronic Flight Bags.)

§ 135.144

32

Protective Fuses. If protective fuses are installed on the airplane, the certificate holder’s manual must describe the number of spare fuses approved for that airplane.

§ 91.205

AC 25-16, Electrical Fault and Fire Prevention and Protection

AC 25.1357-1, Circuit Protective Devices

33

Crash Ax. Each transport-category airplane must be equipped with a crash ax.

§ 135.177

Indicates new/changed information.

Table 10-9-2H.  Equipment and Cargo Compartments

ITEM

EQUIPMENT AND CARGO COMPARTMENTS

REFERENCES (current editions)

1

General Visual Inspection (GVI).

a. Check electronic/electrical components including wiring and connectors for condition, proper bonding, and security.

b. Check that wiring is properly grouped, bundled, routed, and secured to airframe structure.

c. Check with the current aircraft equipment list for installed equipment.

d. Check for metal shavings or other debris that can cause electrical shorts and fire.

e. Check the exposed airframe structure (forward pressure bulkhead, if accessible) for general condition, corrosion inhibiting compound (CIC) application, and evidence of fluid leaks and damage.

f. Check insulation blankets for condition and liquid saturation.

g. If repairs are noted to the airframe structure (major repair), verify that the repair data is Federal Aviation Administration (FAA)-approved.

h. Check that all placards required by the FAA-approved Airplane Flight Manual (AFM), aircraft Type Certificate Data Sheet (TCDS), and applicable operating rules are properly installed at the location specified by those documents.

i. Check each compartment for general condition and that the flammability requirements of ceiling, sidewall liners, and floor material are met (no holes or tears and seams sealed with approved tape).

j. Check all visible cables, wiring, hydraulic and fuel lines, and equipment for security and damage.

k. Verify that the equipment and cargo compartments meet their type design per the TCDS and any changes that have a Supplemental Type Certificate (STC) approved by the FAA and the aircraft is in compliance with that data.

l. Check that the digital flight data recorder (DFDR) and flight deck voice recorder are protected from any contact with shifting baggage or cargo (when applicable).

14 CFR part 135, §§ 135.25 and 135.411

Volume 6, Chapter 2, Section 4

Advisory Circular (AC) 43-206, Inspection, Prevention, Control, and Repair of Corrosion on Avionics Equipment

2

Crew Emergency Exits.

a. Check that the crew has access to emergency exits under all cargo loading conditions. These emergency exits cannot be located within the “E” cargo compartment.

b. Check for required placards and markings of the emergency exit(s).

c. Check aircraft that have two flight deck windows that cannot be opened from the outside, the most forward left main (L1) fuselage door is designated as the required emergency exit.

d. Depending on the type certificate (TC) or STC, marking and designation of the emergency exits will vary. Some aircraft have designated the flight deck windows as the emergency exit.

e. On certain aircraft, an overhead hatch may be provided as an emergency exit.

f. Check that the path from the flight deck to the designated emergency exit is free from obstacles and properly marked.

§§ 135.25, 135.178, and 135.411

Volume 6, Chapter 2, Sections 4 and 5

3

Baggage and Cargo Restraint System.

a. Perform the configuration evaluation check per the approved or accepted data of the Original Equipment Manufacturer (OEM) or STC holder.

b. Check that the restraint system meets Technical Standard Order (TSO)-C90, Cargo Pallets, Nets and Containers (Unit Load Devices), or other approved means, as required.

c. Check that the certificate holder has a maintenance program for its cargo system, including restraint system, pallets, nets, and unit load device (ULD).

d. Check the existing aircraft baggage and cargo restraint system installation (restraint system, pallets, and nets) for general condition, security, and to verify if they are properly identified to its weight or load limits.

§§ 135.25, 135.87, and 135.411

Volume 6, Chapter 2, Sections 4 and 5

AC 25-18, Transport Category Airplanes Modified for Cargo Service

AC 120-85, Air Cargo Operations

TSO-C90

4

Major Alterations of Aircraft Modified to Cargo Freighters (Including Palletized Restraint Systems, Cargo Doors, etc.).

a. Check that the certificate holder’s aircraft has been modified to a cargo freighter in accordance with an FAA‑approved STC.

b. When other than the STC holder’s parts and components are used, verify compliance with approved data obtained from the certificate holder’s records repository.

14 CFR part 43, § 43.5

Part 43 appendix B

§§ 135.25, 135.411, and 135.417

Volume 4, Chapter 9, Section 1

Volume 6, Chapter 2, Sections 5 and 36

Volume 20, Chapter 8, Section 1

AC 120-77, Maintenance and Alteration Data

5

Cargo Barrier. Regardless whether the main cabin is used for cargo-only or as a combi, it must be equipped with a forward 9.0g barrier; either a solid bulkhead or net, in compliance with 14 CFR part 23, § 23.2270 and part 25, § 25.561.

a. Check the 9.0g barrier (net or bulkhead) for general condition, fraying, hardware integrity and airframe attachment, and conformity with approved data.

b. If the aircraft has been converted from a passenger configuration to a cargo-only or a combi through an STC, refer to AC 25-18 for details and verify the records for approved data. Perform the conformity review with this data.

c. Check for the presence of an FAA Parts Manufacturer Approval (FAA-PMA) tag, and TSO tag, if applicable.

d. Check all visible cables, wiring, hydraulic and fuel lines, and equipment for security and damage.

e. Check that each lamp is adequately shielded to prevent contact between lamp bulb and baggage or cargo.

f. Check that any heat source is adequately shielded and insulated to prevent igniting the baggage or cargo.

g. Check for approved hand-held fire extinguishers and if they are available for each class A and E compartment (main deck cargo).

h. Check that a separate approved smoke or fire detector system is installed to give warning to the pilot or Flight Engineer (FE) and is controllable from the flight deck.

i. Check if the installed equipment is in compliance with the current aircraft equipment list, including STC requirements.

j. Check the condition of the smoke curtain (if installed). If a smoke curtain was not installed, check the condition of the flight deck door seals.

k. Check for livestock-carrying freighters for FAA‑approved modification data.

l. Check for a means to prevent cargo or baggage from interfering with the functioning of the fire extinguishing system of the compartment (i.e., a top loading limit marking per the manufacturer’s or STC holder’s requirement).

m. Check the cargo door’s seals for condition.

n. Check the condition of the cargo bin or pallet loading system (if installed) such as rollers, tracks, pallet or bin clamps, or other securing devices for condition and operation.

o. Check if the emergency exit is more than 6 feet off the ground and that a means is provided for the crew and extra supernumeraries (if so equipped) to descend to the ground (e.g., inflatable slide or slide raft, cargo, etc.).

14 CFR part 21, § 21.31

§§ 135.25, 135.87, 135.177, 135.178, and 135.411

Part 135 appendix A

Volume 6, Chapter 2, Sections 4 and 5

AC 20-42, Hand Fire Extinguishers for Use in Aircraft

AC 20-88, Guidelines on the Marking of Aircraft Powerplant Instruments (Displays)

AC 20-168, Certification Guidance for Installation of Non-Essential, Non‑Required Aircraft Cabin Systems & Equipment (CS&E)

AC 25-16, Electrical Fault and Fire Prevention and Protection

AC 25-18

TSO-C121, Underwater Locating Devices (Acoustic) (Self-Powered)

10-9-2-7 through 10-9-2-29 RESERVED.