AIRCRAFT CONFORMITY JOB AID R1 0

0 2 /2 1 /0 2

OPERATOR:

CHDO:

LOCATION:

DATE (S):

PARTICIPANTS:

A. PURPOSE. The Aircraft Conformity job aid along with the SAI/EPI (1.1.1, 1.1.2, 1.2.6, 1.3.2, 3.1.2, 3.1.3) , TCDS, HBAT, HBAW, FSAT, FSAW and the AFM,
will serve as a guide for the conformity review of an aircraft. The job aid targets areas for evaluation to verify compliance with applicable portions of, but not
limited to, FAR Parts 21, 23, 25, 33, 91, & 121. This job aid is not all-inclusive, and it is the responsibility of the operator or the party applying for an Airworthiness
Certificate to ensure that all legal and technical requirements are properly met.

B. CANCELLATION. CSET Aircraft Conformity checklist, Revision 9 dated 1/10/02 is cancelled.

C. RELATED Federal Aviation Regulation (FAR) SECTIONS. FAR Parts 21, 23, 25, 33, 39, 43, 91, 121, CAR 4B

D. ABBREVIATIONS AND ACRONYMS.

AC Advisory Circular ICAO International Civil Aviation Organization

AMM Aircraft Maintenance Manual LOPA List of Passenger Accommodations
AWL Airworthiness Limitations MMEL Master Minimum Equipment List
CAR Civil Air Regulation MRB Maintenance Review Board
EPI Element Performance Inspection NAT North Atlantic
FCC Federal Communication Commission NOAA National Oceanic and Atmospheric Administration
FSAT Flight Standards Air Transportation Bulletin PL FAA Policy Letter
FSAW Flight Standards Airworthiness Bulletin RTCA Radio Technical Commission for Aeronautics
HBAT Hand Book Bulletin Air Transportation SAI Safety Attribute Inspection
HBAW Handbook Airworthiness SPPS Safety Program Analysis Systems
HBGA Hand Book Bulletin General Aviation TSO Technical Standard Order

1 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

1) LIST OF EFFECTIVE PAGES AND RECORD OF REVISIONS

LIST OF EFFECTIVE PAGES RECORD OF REVISIONS

EFFECTIVE PAGE EFFECTIVE REVISION

PAGE REVISION NUMBER
DATE NUMBER DATE DATE
NUMBER
1 2/21/02 33 2/21/02 ORIGINAL 09/12/00
2 2/21/02 34 2/21/02 Revision 1 10/12/00
3 2/21/02 Revision 2 11/04/00
4 2/21/02 Revision 3 12/07/00
5 2/21/02 Revision 4 12/28/00
6 2/21/02 Revision 5 01/06/01
7 2/21/02 Revision 6 01/14/01
8 2/21/02 Revision 7 05/20/01
9 2/21/02 Revision 8 08/11/01
10 2/21/02 Revision 9 01/10/02
11 2/21/02 Revision 10 02/21/02
12 2/21/02
13 2/21/02
14 2/21/02
15 2/21/02
16 2/21/02
17 2/21/02
18 2/21/02
19 2/21/02
20 2/21/02
21 2/21/02
22 2/21/02
23 2/21/02
24 2/21/02
25 2/21/02
26 2/21/02
27 2/21/02
28 2/21/02
29 2/21/02
30 2/21/02
31 2/21/02
32 2/21/02

2 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

TABLE OF CONTENTS

TITLE PAGE
SECTION
1 Purpose 1
1 List Of Effective Pages and Record of Revisions 2
1 Table of Contents 3
2 Aircraft Description 4
3 Documentation 6
4 Maintenance Program 7
5 General 10
6 Fuselage - Exterior - Avionics 10
7 Fuselage - Exterior - Maintenance 11
8 Fuselage – Exterior Powerplant - Maintenance 12
9 Fuselage - Interior - Avionics 12
10 Fuselage – Interior - Maintenance 14
11 Cockpit – Avionics / Operations 14
12 Cockpit - Maintenance / Operations 20
13 Cabin Interior Maintenance / Operations 21
14 Cabin Interior – Avionics / Operations 26
15 General Cargo Compartment requirements – Avionics And / Or Maintenance 27
16 Cargo Compartment Classes – Avionics And / Or Maintenance 29

3 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

2) AIRCRAFT DESCRIPTION
Date of
AIRCRAFT
Serial # Line or Fuselage # Manufacture Type Certificate Data Sheet Repair Map?
Make/Model/Series mm/dd/yy Yes or No
Last CAMP
Total Time (TT) Last Operator (Designator) Program Last “C” Check Last “D” Check
mm/dd/yy mm/dd/yy mm/dd/yy
Previous
Total Cycles (TC) Current Operator (Designator) Registration # Interior Configuration (# Pax) Availability of LOPA?
Yes or No
Current Registration #

Serial #
POWERPLANT TYPE
Serial # Position 1 Serial # Position 2 Position 3 Serial # Position 4 Type Certificate Data Sheet
Make/Model/Series
Total Time (TT) Total Time (TT) Total Time (TT) Total Time (TT)

Total Cycles
Total Cycles (TC) Total Cycles (TC) (TC) Total Cycles (TC)

Time Since
Overhaul
Time Since Overhaul (TSO) Time Since Overhaul (TSO) (TSO) Time Since Overhaul (TSO)

PROPELLERS Type Installed Type Installed Type Installed Type Installed Type Certificate Data Sheet
Make/Model/Series
Serial # Serial # Serial # Serial #

Total Time (TT) Total Time (TT) Total Time (TT) Total Time (TT)

Time Since
Overhaul
Time Since Overhaul (TSO) Time Since Overhaul (TSO) (TSO) Time Since Overhaul (TSO)

4 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

APU (TSO-C77A) Serial # Check A/C TCDS for Applicability?

Make/Model/Series Yes or No
Total Time (TT)

Total Cycles (TC)

Time Since Overhaul (TSO)

Serial # Main
LANDING GEAR TYPE
Serial # Nose Gear Serial # Main Gear LT Gear RT Serial # Gear (other) Serial # Gear (other)
Make/Model/Series
Total Time (TT) Total Time (TT) Total Time (TT) Total Time (TT) Total Time (TT)

Total Cycles
Total Cycles (TC) Total Cycles (TC) (TC) Total Cycles (TC) Total Cycles (TC)

Time Since
Overhaul
Time Since Overhaul (TSO) Time Since Overhaul (TSO) (TSO) Time Since Overhaul (TSO) Time Since Overhaul (TSO)

Max Landing
Max Taxi or Ramp Weight Max Takeoff Weight Weight Max Zero Fuel Weight Operator’s Empty Weight

AIRCRAFT WEIGHTS
Current Aircraft Equipment
Max Structural Weights Max Structural Weights (2) Last Weighing of Aircraft list?
Yes or No

5 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

3) DOCUMENTATION
SAI CERTIFICATES REQUIRED FAR FAR FAR 121 OTHER
21/23 25/33
a. 1.1.1 Aircraft Registration. Current or last. All aircraft bearing US registration markings must be properly registered. If 121.153(a) 47.3
None, FAA Form 8050-1, Application for Certificate of Registration must be completed. Record date of Issuance. (1) 91.203(a)
Issue Date:__________________________________________ AC 20-5G
b. 1.1.1 Airworthiness Certificate. Current or last. List Exemptions granted, if applicable. Or FAA Form 8130-6, 21.183(d) 121.153(a) 91.203(a)
Application for Certificate of Airworthiness, completed.
Listing of exemptions_____________________________________________________________________________:
c. 1.1.1 Export Airworthiness Certificate. If applicable. Any aircraft manufactured within the boundaries of the United 21.329 8130.2D
States and NOT certified in the US and then exported will have an Original export Certificate of Airworthiness. This AC 21.2H
certificate is essential to the certification process and can be obtained through the manufacturer or the FAA if not available
from the seller. The aircraft must comply with its’ TCDS as originally exported.
d. Certificate of Sanitary Construction
e. Aircraft Incident/Accident Records. Review history of incidents and/or accidents the aircraft may have been SPAS
involved in.
f. Type Certificate Data Sheet (TCDS) . Review applicability of TCDS. 21.21 www.airweb.faa.go
v
g. FCC Radio License. A FCC Aircraft Radio Station License is maintained by the operator to permit the operation of FCC
communication radios aboard their aircraft. This license is granted for a set number of aircraft and must be updated when
additional aircraft are added to the fleet.

h. SARSET Beacon Registration (Required for 406 MHZ ELT) Form OMB-0648-0295 is to be submitted NOAA.
i. 1.1.1 Export Certificate. Current and valid from country of current location. (If applicable) 21.183, 197
21.500
j. 1.1.3 Special Flight Authorization. If applicable. Special Flight Permit may be required to operate the aircraft prior to 21.197 FSAT 95-03
being placed on an operator’s ops spec. FSAW 95-02 and FSAT 95-03 (Extended): List of Minimum Instruments to Ferry FSAW 95-02
Large Turbojet Airplanes
k. 1.1.1 Identification of Aircraft & Related Products. Assure that the identification plate required by FAR Part 45.11 21.182(c) 45.11(a)(d)
is secured in such a manner that it will not likely be defaced or removed during normal service, and secured to the aircraft 21.607 45.13,
fuselage exterior. 45.15
Required Manuals On-Board
l. 2.1.4 Airplane Flight Manual (AFM): Check that the Aircraft has a current copy of the Manufacturer’s Airplane Flight 21.5 25.1581 thru 121.133 CAR4b.740
Manual (AFM) for the particular make, model and serial number. Confirm appropriate supplements. 23.1581 thru 25.1587 91.9
23.1589
m. 2.1.4 Airplane Operating Manual (AOM): Per 121.141(b) Certificate holder shall carry either the manual required by 121.141
121.133, if it contains the information required for the applicable flight manual and this information is clearly identified as
flight manual requirements, or an Approved AFM.
n. 2.1.4 Emergency Procedures Manual/Checklist. Cockpit Checklist / Emergency Procedures Manual. POIs shall 121.133 8400.10 Vol. 3
ensure aircraft checklists are limited to action items or verification items. The aircraft checklist should not contain elaboration 121.135 CH. 15
or explanation. POIs must ensure that the required actions and decisions for flight crews when performing a checklist are
thoroughly described in the operator's manual and training program.
o. 1.3.5 Minimum Equipment List. Check revision is current with MMEL. MEL items should correspond with aircraft 121.303(d) 91.213
2.1.4 equipment list. Check required (M)(O) procedures have been addressed. 121.627(b)
3.2.3 121.628
p. 1.3.17 Weight & Balance Manual. (Also Cargo Loading Manual if applicable) Review manual(s). 23.1583(c) 25.1583(c) 121.133 CAR4b.740
2.1.4 91.605

6 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

3) DOCUMENTATION (CONT’D)
SAI DESCRIPTION: FAR FAR FAR 121 OTHER
21/23 25/33
q. 2.1.4 Flight Attendant Manual (FAM): Check that the Aircraft has a current copy of the FAM (or its equivalent, i.e., In- 121.133 8400.10 Vol. 3
flight manual) 121.135 CH. 15, Sect. 6
121.137
121.139
r. 1.3.16 Other Manuals required by 121.133 and 121.135 Check that the Aircraft has a current copy of the De-Iceing, 121.133
1.3.18 Fueling manual, and any other manual required by the operators GOM/GMM 121.135
2.1.4 121.139

4) MAINTENANCE PROGRAMS
SAI DESCRIPTION: FAR FAR FAR 121 OTHER
21/23 25/33
a. 1.3.1 Maintenance Program. Each operator/applicant must have a maintenance program adequate to perform the work 21.181 121.367 91.409
and a separate inspection program adequate to perform required inspections. Minimum Standard The program should be 121.380 119.49
identified and be traceable to its minimum standard or baseline, i.e. Maintenance Review Board (MRB), Mfr. Approved 8300.10 Vol. 2
Program or recommended tasks and intervals, fleet average, etc. In the event that the program fails to meet an established CH. 64
standard such as the MRB all areas of deficiency should be identified. Identify any OC or CM systems, assemblies, or HBAW 98-03A
components that the operator performs specific tests upon to determine their acceptability: Identify test procedures and
equipment.

Maintenance Review Board reports contains the initial minimum maintenance/inspection requirements to be used in the
development of an approved continuous airworthiness maintenance program for the airframe, engines, systems and
components.
b. 1.3.1 Certification Maintenance Requirements. A CMR is a required periodic task, established during the design 23.1309 25.1309 AC 25.19
certification of the aircraft as an operating limitation of the type certificate. CMRs are a subject of the tasks identified during 23.1529 25.1529 AC 1309 1A
the type certification process. CMRs usually result from a formal, numerical analysis conducted to show compliance with
catastrophic and hazardous failure conditions.
c. 1.3.1 Turbine Engine Critical Rotating Hardware Enhanced Inspection Program. Operators certificated 121.380 Check AWL
under 14 CFR parts 121 and 135 with an approved continuous airworthiness maintenance program, in accordance with 121.709
paragraph (*) of the AD, must incorporate the inspection requirements of the AD AWL into their existing
maintenance/inspection programs. Principal Maintenance Inspector’s with certificate management responsibilities of these
operators must ensure that the operator’s program incorporate the inspections and procedures required by the applicable
AD. These inspections are contained in the airworthiness limitations section, time limitations section, or other listing as
appropriate with reference to the manual section containing the actual procedures, of the engine manufacturer’s ICA.
d. 1.1.1 Time Controlled Items. Documentation should exist for time-controlled items installed on the aircraft and/or engine, 121.380 91.409,
1.1.2 since the last required action. The Listing should include components identified by nomenclature, part number, and serial AC 121.1A
1.3.1 number. The records should state present status and time remaining. Substantiation of these records may be made by Applicable
1.3.2 reviewing documentation as applicable to the last overhaul, last maintenance activity or manufacture. If installation cannot MRBR
be verified through record research, a physical inspection to verify component identification will be necessary.
e. 1.3.1 VOR Equipment Checks for IFR Operations. No person may operate a civil aircraft under IFR using the VOR 91.171
1.3.2 system of radio navigation unless the VOR equipment of that aircraft; (1) Is maintained, checked, and inspected under an TSO-C40c
approved procedure, or (2) Has been operationally checked within the preceding 30 days, and was found to be within the TSO-C66c
limits of the permissible indicated bearing error set forth in paragraph (b) or (c) of this section. The aircraft VOR must be or
have been tested and/or maintained under an approved program. Example: (MPD / MRBR etc.).

7 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

4) MAINTENANCE PROGRAMS (CONT’D)

SAI DESCRIPTION: FAR FAR FAR 121 OTHER
21/23 25/33
f. 1.3.1 HIRF/Lightning Protection Maintenance Program. These programs assure that lightning and HIRF 23.867 25.581 CAR4b.628
1.3.2 protection are maintained against electromagnetic hazards, caused by exposure to lightning and HIRF environments, and to 23.954 25.954 8300.10 Vol. 2
flight critical electrical/electronic systems installed on or within the aircraft. Equipment hazards addressed include those due 25.1316 CH. 63 & 237
to effects on equipment and associated wiring on or within the aircraft. This document applies to in-service aircraft, FSAW 97-16A
equipment, modifications of existing aircraft or equipment, and applications of existing (off the shelf) equipment. N8110.71
AC 20-53D
The program should include maintenance/inspection requirements for lightning and HIRF protection for applicable AC 20-115B
electric/electronic subsystems such as, but not limited to; power distribution and generating equipment, electronic and AC 20-136
electromechanical devices, systems that use data busses for critical functions, electronic engine and flight controls including MRBR
Full Authority Digital Engine Controls (FADEC), as well as associated interconnecting wiring or cables. FSAW 97-16A PL 2137, RTCA
(Extended) DO160 C/D &
DO178 A/B
g. 1.3.1 Pitot-Static System/Altimeter Tests and Inspection. Section 91.411, does not apply to an aircraft 23.1325(b) 25.1325(c) 43 app. E
1.3.2 maintained in accordance with a continuous airworthiness maintenance program as provided in part 121. AEG’s position is (2)(ii) (2)(ii) 91.401
that the carriers CAMP program normally exceeds the requirements 91.411. The carriers CAMP should still address how 91.411
they will test and inspect the pitot static/altimeter system.
h. 1.1.1 ATC Transponder Installation, Tests and Inspections. Includes altitude-reporting equipment. Verify 121.345(c) 43 app. F
strapping if registration change. 91.215(a)
91.413
8400.10, Vol.1
CH. 23,
TSO C112
(Mode S), TSO-
C74b
i. 1.1.2 Anticollision Lights. Verify Air Carrier Strobe Light Maintenance Program (if applicable). FSAW 98-01 (Extended): 23.1401 25.1401 121.323(b) CAR4b.637
1.3.1 Air Carrier Strobe Light Maintenance Programs. FSAW 98-01
AC 20-30B
TSO-C96a
j. 1.3.1 RVSM. Reduced Vertical Separation Minimum Airspace. Refer to FAR 91 –Appendix G for requirements. 121 app G. 91.706,
1.3.2 HBAT 97-14
5.1.9 HBAT 00-01
Additional Maintenance Requirements for Operational Approval of Operators Requesting RVSM Approval
AC 91-RVSM
Federal Aviation Administration (FAA) Memorandum 91-RVSM, entitled "Interim Guidance for Approval of Aircraft for
ICAO 9574
Reduced Vertical Separation Minimum (RVSM) Flight," dated March 14, 1994, relating to additional maintenance
MMEL GC-33
requirements pursuant to the operational approval of aircraft for flight in oceanic airspace where RVSM is applied.
NAT RVSM Doc-
Specifically, section 10, Continued Airworthiness (Maintenance Requirements), addresses additional maintenance
002
requirements for RVSM operational approval.
k. 1.3.1 Structural Inspection Requirements. The Structure Program defines the directed inspections for each 23.611 25.611 MRB and/or
1.3.2 Structural Significant Item (SSI) developed through evaluation of their fatigue, environmental and accidental damage AD’s (as
characteristics. A list of all SSIs and a list of SSIs having no scheduled maintenance task are given in Appendix 4 of the applicable)
MRB Report.
l. 1.3.1 Corrosion Prevention Control Program (CPCP)/Aging Aircraft. Required per applicable Airworthiness 23.609 25.609 8300.10 Vol. 3
1.3.2 Directive and/or MRB report. A Corrosion Prevention and Control Program should be established to maintain the aircraft's CH. 36,&
resistance to corrosion as a result of systematic (e.g. age related) deterioration through chemical and/or environmental 8300.10 app. 5,
interaction. Verify reporting activity. Verify that the Aging Aircraft/Corrosion Control program provides the necessary HBAW 94-05B,
guidance to evaluate and respond in a timely manner to structural fatigue and corrosion. HBAW 96-01,
MRB and/or
AD’s

8 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

4) MAINTENANCE PROGRAMS (CONT’D)

SAI DESCRIPTION: FAR FAR FAR 121 OTHER
21/23 25/33
m. 1.3.1 Damage Tolerance Rating Evaluations. A qualification standard for aircraft structure. An item is judged to be 23.573 25.571 121.370 MRB and/or
damage tolerant if it can sustain damage and the remaining, structure can withstand reasonable loads without structural AD’s (as
failure or excessive structural deformation until the damage is detected. Verify DTRs are incorporated in air carrier’s applicable)
maintenance program. AC 25.571-1 pg
4, par 3(p)
n. 1.3.1 Flight Data Recorder Maintenance Program. Does operator have a DFDR maintenance program (AC 20-41). 23.1459(c) 25.1459(c) 121.343 N8110.65
Review the most recent instrument calibration and the recording medium from which the calibration was derived, and the 121.344 AC 20-141
recorder correlation. Are the range and accuracy of the correlation within the limits specified in FAR 121 appendix. B & M. 121.344a 121 app. B & M
Does the operator have a program for accomplishing a Ping test each time the ULB is replaced?
o. 1.2.2 Major Repairs and Alterations. A complete and accurate listing of all major structural repairs including method of 121.379(b) 43.9(b)
1.3.9 repair and FAA approval must be furnished. Review records containing list of current major repairs and alterations to each 121.380 43 app. A & B
airframe, engine, or component. Documentation should be provided for each major repair/alteration that verifies that the 121.707 AC 140.6C
work has been done in accordance with technical data approved by the FAA. (i.e. STC, SRM, DER, or FAA field approval)
p. 1.2.2 Supplemental Type Certificates (STC). All incorporated STCs must be supported by documented approved 21.117 25.1529 121.379(b) 8110.69
1.3.9 data. Has the operator and/or the manufacturer of the STC, developed Instructions for Continued Airworthiness and are 21.463 121.380 HBAW 98-16
they incorporated into the carriers maintenance program? Does operators GMM have procedures for accomplishing this? 21.477 121.707
23.1529
q. 1.2.1 Airworthiness Directives (ADs). Confirm summary completed. Perform random sampling of Airframe, Engine, & 21.99 121.380 39.1
1.2.3 Appliance ADs and their compliance. If the AD was performed on a rotable component or assembly, serial numbers and 39.3
1.3.6 installation and removal dates shall be provided to ensure that the aircraft’s AD compliance list is still valid. The records 39.11
must include: (1) The ID of the particular airframe, engine, appliance, or component to which the AD applies. (2) The AD 91.417
number and if applicable, its revision number, revision date, or amendment number. (3) The date on which the required HBAW 98-02
action was last accomplished. (4) The total time-in-service, as expressed by the applicable standard, as required by the AD.
(5) The method of compliance, by reference to a specific action described in the AD, a specific description of the work
performed or a description of an AMOC with a copy of the FAA approval. AMOCs accepted must be transferable to the new
owner/operator, If not transferable compliance with all requirements of the AD must be established. (6) If the AD requires
recurring action, the interval to the next required action as expressed by the applicable standard. (7) If available, actual
completed work card for repetitive and terminated ADS. (8) CPCP compliance status of the aircraft must be reviewed, and
any AMOCs required to take credit for previous accomplishment must be applied for.
The following ADs are applicable to Transport Category Aircraft:
74-08-09 R2 LAVATORY FIRE PREVENTION
75-22-22 DOT-3HT-3000 COMPRESSED GAS CYLINDERS MANUFACTURED BY PRESSED STEEL TANK COMPANY
76-05-02 SIDE-FACING FLIGHT ATTENDANT SEAT
87-08-09 INFLATE TIRES WITH NITROGEN ONLY PLACARD/PROGRAM
r. 1.3.2 Temporary Repairs. All repairs performed on the aircraft, which have been identified as requiring recurring Applicable AMM
inspections shall be noted and their inspection requirements and intervals documented.
s. 1.2.1 Aircraft Maintenance/Overhaul Records. Perform a random sampling of records of the most recent repetitive 121.380 91.417
1.2.3 maintenance tasks, inspections, and overhaul teardowns performed on the aircraft, engine, and components as required by HBAW 98-02
the operator’s current inspection program. If the aircraft is not currently on a continuous airworthiness maintenance
program, records from the last approved operator’s inspection program are to be reviewed.
t. 1.3.2 Repair Assessment for Pressurized Fuselages. FAA approved repair assessment guidelines must be 121.370 91.410
incorporated into the air carriers maintenance program by May 25, 2001.

9 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

4) MAINTENANCE PROGRAMS (CONT’D)

SAI DESCRIPTION: FAR FAR FAR 121 OTHER
21/23 25/33
u. 1.3.1 Airplane Conformity Program. 121.135(b)
1.3.2 1. Does the operator have an aircraft conformity process documented within their manual system. (16), (17)
1.3.11
2. Does the operator's aircraft conformity process meet all applicable requirements of the CFR's and their Continued
Airworthiness Maintenance Program (CAMP)

3. Does the operator's aircraft conformity process include procedures for documenting discrepancies discovered during the
aircraft conformity process.

4. Does the aircraft conformity process include procedures for corrective action of those discrepancies.

5. Does the operator have a performance measurement within their CASS for the aircraft conformity requirements.

Should these questions be included w/in the job aid, the results will give us risk indicators as they relate to their CASS,
Maintenance Program and their Inspection Program. SAIs; 1.3.11, 1.3.1 and 1.3.2 respectively.

5) GENERAL
SAI DESCRIPTION: FAR FAR FAR 121 OTHER
21/23 25/33
a. 2.1.4 Performance Requirements The performance requirements of this Subpart, Sections 25.101 to 25.125, are 23.45 thru 25.101 thru 121.173 CAR 4b.100 to
applicable to all aircraft certificated under FAR 25 Sub. A. The performance requirements of CAR 4b, Subpart B, Sections 23.77 25.125 121.189 4b.125-1
4b.100 to 4b.125-1, are applicable to all aircraft certificated under CAR 4b. Each specific aircraft Performance and thru
Limitations for exiting aircraft configuration, modifications, improvements and engines installation, must be included in the 121.197
particular FAA approved Aircraft Flight Manual (AFM). 121 app. K
b. 1.1.1 Operating Noise Limits. Identify level of compliance with airframe and engine noise suppression requirements. List 21.183(e) 36
1.1.2 mfr. service bulletins, STCs, etc. Reference compliance with FAR 36, Stage I, II, III, or ICAO Annex 16, CH. 1, 2, 3. 91.801
Advisory Circular 36-3G, Estimated Airplane Noise Levels in A-Weighted Decibels. AC 36-3G
c. 1.1.1 Special Airworthiness Requirements – Subpart J of FAR 121: If airplane was type certificated under 121.211
Aero Bulletin 7A or the Civil Air Regulation in effect before November 1, 1946, assure that all special airworthiness 121.215
requirements listed in 121.215 through 121.283. thru
121.283
d. 1.1.1 Special Retroactive Requirements. The requirements included in 25.2(a)(1)&(b) are applicable to all aircraft 23.2 25.2(a)(1)
irrespective of reference regulation used for the certification and TCDS approval. 25.2(b)
e. Function and Installation. Each item of installed equipment must: a) Be of a kind and design appropriate to its 23.1301 25.1301
intended function; b) be labeled as to its identification, function, or operating limitations, or any applicable combination of
these factors; c) Be installed according to limitations specified for that equipment; and d) function properly when installed.

6) FUSELAGE – EXTERIOR - AVIONICS

SAI DESCRIPTION: FAR FAR FAR 121 OTHER
21/23 25/33
a. 1.1.2 Heated Pitot Tubes. An airspeed indicating system with heated Pitot Tube or equivalent means for preventing 23.1323(d) 25.1323(e) 121.323(e) HBAW 97-15
malfunctioning due to icing. 23.1326 25.1326 121.342
HBAW 97-15: Additional Procedures to the Air Carrier's Continuous Airworthiness Maintenance Program that Ensures
Covers are Removed From Pitot-Static Ports Following Cleaning and Maintenance

10 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

6) FUSELAGE – EXTERIOR – AVIONICS (CONT’D)

SAI DESCRIPTION: FAR FAR FAR 121 OTHER
21/23 25/33
b. 1.1.1 Static Pressure Systems. Two independent static pressure systems, vented to the outside atmospheric pressure so 23.1325 25.1325 121.313(e) CAR4b.612
1.1.2 that they will be least affected by airflow variation or moisture or other foreign matter, and installed so as to be airtight 121.323 43 app. E
except for the vent. When a means is provided for transferring an instrument from its primary operating system to an 91 app. A
alternate system, the means must include a positive positioning control and must be marked to indicate clearly which HBAW 97-15
system is being used. TSO-C2d.
c. 1.1.2 Landing Lights. Two landing lights, except that only one landing light is required for non-transport category aircraft 23.1383 25.1383 121.323(c) CAR4b.631
type certificated after December 31, 1964. Night Operations 91.205(c)
d. 1.1.2 Position Lights. System installation, Dihedral angles, Distribution & intensities. Night Operations 23.1385 thru 25.1385 thru 121.323(a) CAR4b.632 thru
23.1399 25.1399 4b.635
91.205(c)
PL 1104, 1106
TSO-C30c
e. 1.1.2 Anticollision Lights. Verify Air Carrier Strobe Light Maintenance Program (if applicable). FSAW 98-01 (Extended): 23.1401 25.1401 121.323(b) CAR4b.637
Air Carrier Strobe Light Maintenance Programs. FSAW 98-01
AC 20-30B
PL 1106,PL
1107
PL 1108 PL
1112
PL 1114 PL
1115
Preamble 23-11
TSO-C96a
f. 1.1.2 Antennas Security and indications of corrosion 8300.10 Vol. 3
CH. 1
g. 1.1.2 Placards. Verify mfg. required placards are installed. Refer to aircraft maintenance manual chapter 11 for data. All 23.1557 25.1557 CAR4b.730
placards required in either the approved AFM, the applicable operating rules, or the Certification Basis must be installed in 91.9(b), TCDS
the airplane. AFM Limits
AMM CH. 11

7) FUSELAGE – EXTERIOR – MAINTENANCE

SAI DESCRIPTION: FAR FAR FAR 121 OTHER
21/23 25/33
a. 1.3.1 Aircraft Inspection. Inspect the following zones for general condition, damage, corrosion, fluid leaks, security of 21.183 121.367 43 app. D
1.3.2 attachment, and corrosion prevention treatment application: Fuselage, wings, nacelles, pylons, stabilizers- 91.409
vertical/horizontal, & control surfaces. Examine joints, seams and skin for wrinkles, bulges, rivets, skin erosion, corrosion, AMM
oxidation, non-approved repairs and modifications, composite material panels for contamination and bonding, separation of
skin-bonding. Compare repair mapping with aircraft. Photograph exterior as necessary.
b. Identification of Aircraft. On aircraft manufactured before March 7, 1988, the identification plate required by 21.182 45.11(d)
paragraph (a) of this section may be secured at an accessible exterior or interior location near an entrance, if the model 45.23
designation and builder's serial number are also displayed on the aircraft fuselage exterior. The model designation and 119.9
builder's serial number must be legible to a person on the ground and must be located either adjacent to and aft of the
rearmost entrance door, or on the fuselage near the tail surfaces. The model designation and builder's serial number must
be displayed in such a manner that they are not likely to be defaced or removed during normal service.
c. 1.3.1 Aircraft Painting. Aircraft that have been painted must comply with the manufacturer’s painting procedures, and use 121.367 43.13(a) & (b)
1.3.2 the manufacturer’s recommended or equivalent materials. The aircraft must be weighed and balanced. The flight controls 43 app. A
1.3.17 may have to be Statically Balanced (painting an aircraft is considered preventative maintenance).
11 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

7) FUSELAGE – EXTERIOR – MAINTENANCE (CONT’D)

SAI DESCRIPTION: FAR FAR FAR 121 OTHER
21/23 25/33
d. Certificate Holder Name. The name of the certificate holder who is operating the aircraft, or the air carrier or 119.9
operating certificate number of the certificate holder who is operating the aircraft, must be legibly displayed on the aircraft
and clearly visible and readable from the outside of the aircraft to a person standing on the ground at any time except during
flight.
e. 1.1.1 Placards: All placards required in either the approved AFM, the applicable operating rules, or the Certification Basis 23.1557 25.1557 CAR4b.730
must be installed in the airplane. 91.9(b)
AFM Limits
AMM Chapter 11
f. 1.1.1 Fuel Tank Impact Resistant Access Doors. All fuel tank access covers must be designed to minimize 25.963(e) 121.316 AC 20-128
penetration and deformation by tire fragments, low energy engine debris, or other likely debris, unless the covers are AC 25.963-1
located in an area where service experience indicates a strike is not likely.
g. 1.1.1 Exterior Exit Markings. Each passenger emergency exit and the means of opening that exit from the outside must 21.183(f) 25.811 121.310(g) CAR4b.362
be marked on the outside of the airplane. Refer to 121.310(g) for requirements.
h. 1.3.1 Windows. Inspect for Delamination, scratches, crazing, and general visibility 21.183 25.775 121.367 8300.10 Vol. 3
1.3.2 23.775 CH. 1
i. 1.1.1 Emergency Exit Arrangement. Each emergency exit, including a flight crew emergency exit, must be a movable 21.183(f) 25.807 121.221 CAR 4b.362
door or hatch in the external walls of the fuselage, allowing unobstructed opening to the outside. Each emergency exit must 23.807 25.809
be operable from the inside and the outside except that sliding window emergency exits in the flight crew area need not be 23.813 25.813
operable from the outside if other approved exits are convenient and readily accessible to the flight crew area. The required 25.857
crew emergency exits are accessible under any cargo loading condition.
j. 1.1.1 Exterior Emergency Lighting and Escape Route. Refer to 121.310 & 25.810 for requirements. Check 23.812 25.810 121.310(h)
general condition of emergency floor path lighting system. 25.812
k. 1.3.1 Doors. (Entry, cargo, emergency, service, & access doors) Inspect for cleanliness, poor condition, loose/missing 21.183 25.783 121.367 CAR4b.356
1.3.2 equipment, deterioration breakage leakage, corrosion, proper installation, and other indications of defects. Pay particular 23.783 43.13
attention to doorjambs. Applicable AMM

8) FUSELAGE – EXTERIOR - POWERPLANT – MAINTENANCE

SAI DESCRIPTION: FAR FAR FAR 121 OTHER
21/23 25/33
a. 1.3.1 Engines, APU, Nacelles, and Compartments. Inspect for cleanliness, poor condition, loose/missing 21.183 121.367 43 app. D
1.3.2 equipment, deterioration breakage leakage, corrosion, proper installation, and other indications of defects. Pay particular Applicable
attention to excessive oil/fuel/ or hydraulic leaks, proper hardware installation. AMM/PMM
PL 818
b. 1.3.1 Engines, APU. Assure that current maintenance program contains instruction for maintaining continued airworthiness 21.183 33 app. A 121.367
1.3.2 of each engine and APU. This program should meet the minimum requirements of FAR 33, Appendix A
c. Airworthiness Standards Type Certificate and Changes to Type Certificate 33.1

d. 1.3.1 Engine: Instructions for Continued Airworthiness 33.4

1.3.2
e. Engine: Ratings and Operating Limitations 33.7
f. Engine: TCDS 21.41

12 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

9) FUSELAGE – INTERIOR - AVIONICS

SAI DESCRIPTION: FAR FAR FAR 121 OTHER
21/23 25/33
a. 1.3.1 Equipment Compartment Inspection. Perform inspection in electrical/electronics compartment(s). Inspect for 21.183 25.631 121.367 43 app. D
1.3.2 cleanliness, poor condition, loose/missing equipment, deterioration breakage leakage, corrosion, proper installation, and 25.869 AMM
other indications of defects. Pay particular attention to equipment installation lighting, and airplane wiring for the following: 25.903(d) TSO-C84
proper routing; marking; chaffing; location with respect to fluid lines, lavs and galley; drip loops; bend radius; coil, cap and 25.1301 AC-25-10
stow methods; proper slack, segregation and separation; clamping; and splicing. 25.1309(b) AC-25-16
25.1353(b) AC-43.13-1B
25.1529
b. 1.1.2 Batteries/Power Supplies. 23.1331 25.1331 CAR4b.625
23.1353 25.1353 PL 25.1301.746
c. 1.1.1 Cockpit Voice Recorder. No certificate holder may operate a large turbine engine powered airplane or a large 23.1457 25.1457 121.359 CAR4b.606
1.1.2 pressurized airplane with four reciprocating engines unless an approved cockpit voice recorder is installed in that airplane. 91.609
Verify Underwater Locator Beacon (ULB) shelf life. 8300.10 Vol. 2
CH. 1 & 237,
Vol. 3, CH. 142
Part Number:___________________________ Location:_______________________________
8300.56,
8430.58
ULB Due Date:_________________________ ULB Date of MFG.________________________ AC 21-10A
AC 43.13-2B
When was the ULB last Ping Tested/Inspected? PL 300
TSO-C121
TSO-C123a
d. 1.1.1 Digital Flight Data Recorder. Refer to 121.344 for required parameters. Note: The installation of enhanced 23.1459 25.1459 121.344 CAR4b.606
1.1.2 DFDR must be accomplished at the earliest time practicable, but no later than the next heavy maintenance check after 121.344(a) 91.609
August 18, 1999. HBAW 96-09: Self-Test of Teledyne Controls, (ARINC 563) Flight Data Recorder System, Central 121 app .M 8300.10 Vol. 3
Electronics Unit. Verify Underwater Locator Beacon (ULB) shelf life. 121 app. B CH. 142
HBAW 96-09
Part Number:____________________________ Location:______________________________
HBAW 97-13B
N8110.65
ULB Due Date:_______________________ ULB Date of MFG.___________________________ AC 20-141
TSO-C111
When was the ULB last Ping Tested/Inspected? TSO-C121
TSO-C124b
Digital Flight Data Recorder (Cont.) 23.1459 25.1459 121.344 91.609
1) Turbine-engine powered transport category airplanes operating under the provisions of 14 CFR 121.344(a) CAR4b.606
121 app. M 8300.10 Vol. 3
part 121
121 app. B CH. 146
a. Airplanes manufactured on or before October 11, 1991, that were not equipped with Flight Data
AC 20-141
Acquisition Units (FDAU) as of July 16, 1996. These airplanes must be upgraded from their current
HBAW 96-09
eleven (11) parameter recording capability to record eighteen (18) parameters. The retrofit must be
HBAW 97-13B
accomplished by the next heavy maintenance check after August 18, 1999, but no later than August 20,
N8110.65
2001.
TSO-C111
TSO-C121
b. Airplanes manufactured on or before October 11, 1991, that were equipped with FDAU as of July TSO-C124b
16, 1996. These airplanes must be upgraded to record 22 Parameters. The retrofit must be
accomplished by the next heavy maintenance check after August 18, 1999, but no later than August 20,
2001.

13 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

9) FUSELAGE – INTERIOR – AVIONICS (CONT’D)

SAI DESCRIPTION: FAR FAR FAR 121 OTHER
21/23 25/33
23.1459 25.1459 121.344 91.609
c. Airplanes manufactured on or before October 11, 1991, that were equipped with ARINC 717 121.344(a) CAR4b.606
DFDAU or equivalent as of July 16, 1996. These airplanes must be upgraded to record 22 121 app. M 8300.10 Vol. 3
parameters. The retrofit must be accomplished by August 20, 2001. 121 app. B CH. 146
AC 20-141
d. Airplanes manufactured after October 11, 1991, but before August 18, 2000. These airplanes must HBAW 96-09
be upgraded to record 34 parameters. The retrofit must be accomplished by August 20, 2001. HBAW 97-13B
N8110.65
e. Airplanes manufactured after August 18, 2000, but before August 20, 2002. The airplanes must be TSO-C111
equipped to record 57 parameters. TSO-C121
TSO-C124b
f. Airplanes manufactured after August 19, 2002. These airplanes must be equipped to record
88 parameters. The parameter specifications of part 121, appendix M, or part 125, appendix E, apply to
all parameters.

2) Turbine-engine powered airplanes having passenger seating of 10 to 19 seats operating under the
provisions of 14 CFR part 121
a. Airplanes (10 to 19 passengers) brought onto the U. S. register or foreign-registered airplanes
added to an operator's U. S. operations specifications after October 11, 1991, but manufactured
on or before August 18, 2000. In order to operate under part 121, these airplanes must be equipped
with a DFDR system recording 18 parameters by the next heavy maintenance check or equivalent after
August 18, 1999, but before August 20, 2001.

b. Airplanes (10 to 19 passengers) manufactured after August 18, 2000, but before August 20,
2002. These airplanes operated under part 121 must be equipped with a DFDRs that records 57
parameters.

c. Airplanes (10 to 19 passengers) manufactured after August 19, 2002. These airplanes must be
equipped with the 88-parameter system.

3) U.S. registered aircraft operated by a foreign carrier under part 129. These aircraft must have a
DFDR that records the parameters that would be required under part 121, 125, or 135 as applicable to
the aircraft.

10) FUSELAGE -- INTERIOR - MAINTENANCE

SAI DESCRIPTION: FAR FAR FAR 121 OTHER
21/23 25/33
a. 1.3.2 Aircraft Inspection. Inspect the following zones for general condition, damage, corrosion, fluid leaks, security of 21.183 121.367 43.13, 43 app. D
attachment, and corrosion prevention treatment application: Fwd & Rear pressure bulkhead (fore & aft), interior and under 91.409
floor areas. Fuselage, wings, nacelles, pylons, stabilizers-vertical/horizontal, & control surfaces. Examine joints, seams 8130.2D
and skin for wrinkles, bulges, rivets, skin erosion, corrosion, oxidation, non-approved repairs and modifications, composite 8300.10, Vol.3
material panels for contamination and bonding, separation of skin-bonding. Compare repair mapping with aircraft. CH. 2
Photograph exterior as necessary. AMM
b. 1.3.1 Repair Mapping. Obtain operator’s repair mapping for external/internal structural repairs. (Recommended) 121.370
1.3.2 121.380

14 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

11) COCKPIT – AVIONICS / OPERATIONS

SAI DESCRIPTION: FLIGHT AND NAVIGATIONAL EQUIPMENT FAR FAR FAR 121 OTHER
21/23 25/33
a. 1.1.1 Cockpit Inspection. Inspect for cleanliness, poor condition, loose/missing equipment, deterioration breakage 21.183 121.153 AMM
1.3.1 leakage, corrosion, proper installation, legibility of placards, and other indications of defects. Pay particular attention to
windshields, windows, paneling, flooring, controls, lighting, and wiring installations.
b. 1.1.1 Instrument Arrangement, Visibility & Lighting. Basic flying instruments must be installed in compliance with 23.1303 25.1303 121.303(b) CAR4b.611
FAR 25.1303 and grouped in compliance with FAR 25.1321(b). Instrument lights providing enough light to make each 23.1321(d) 25.1321(b) 121.323(d) 91.205
required instrument, switch, or similar instrument, easily readable and installed so that the direct rays are shielded from the 23.1381 25.1381 121.325(c)
flight crewmembers' 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. Night Operations See
Requirements at 121.323
c. 1.3.1 ELECTRONIC FLIGHT INSTRUMENT SYSTEM (EFIS) & ELECTRONIC CENTRALIZED 21.91 25.1309 8300.10 Vol. 2
1.3.2 21.111 25.1333 CH. 237
AIRCRAFT MONITORING (ECAM). Verify instructions for continued airworthiness. Verify installation approval 23.1309 FSAW 95-09B
(TC/STC)
23.1311 HBAW 91-13
AC 25.1309-1A
AC 25-11
PL 1050
PL 1065
PL 1698
RTCA DO178
A/B
RTCA DO 160C
TSO-C113
d. 1.1.2 Instrument Markings. Ranges/information correct for installed equipment. For imported aircraft, measurements are 23.1541 25.1541 CAR4b.731
in pounds, knots, and feet. 23.1543 25.1543 AC 20-69
e. 1.1.1 Instruments Using a Power Supply. For each instrument required by § 25.1303(b) that uses a power supply, 23.1331 25.1331 121.313(c) CAR4b.612(e)
the following apply: (1) Each instrument must have a visual means integral with, the instrument, to indicate when power
adequate to sustain proper instrument performance is not being supplied. The power must be measured at or near the point
where it enters the instruments. For electric instruments, the power is considered to be adequate when the voltage is within
approved limits. (2) Each instrument must, in the event of the failure of one power source, be supplied by another power
source. This may be accomplished automatically or by manual means. (3) If an instrument presenting navigation data
receives information from sources external to that instrument and loss of that information would render the presented data
unreliable, the instrument must incorporate a visual means to warn the crew that the presented data should not be relied
upon, when such loss of information occurs.
f. 1.1.2 Pitot Heat Indication Systems. The indication system must comply with the following requirements: (a) The 23.1326 25.1326 121.342 HBAW 97-15
indication provided must incorporate an amber light that is in clear view of a flight crewmember. (b) The indication provided
must be designed to alert the flight crew if either of the following conditions exist: (1) The Pitot heating system is switched
"off". (2) The Pitot heating system is switched "on" and any Pitot Tube heating element is inop.
g. 1.1.2 Airspeed Indicating System. With heated Pitot tube or equivalent means for preventing malfunctioning due to 23.1303(g) 25.1303(b) 121.303(c) CAR4b.612(a)(5)
icing. Check airspeed placard. Check AFM Operating limitations. Verify that each Airspeed indicator is calibrated in knots (1) (1) 121.305(a) TSO-C2d
and pertinent placards are expressed in knots. 23.1545 25.1545 121.323(e) TSO-C46a
23.1583 25.1583 121.325(a)

15 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

11) COCKPIT – AVIONICS / OPERATIONS (CONT’D)

SAI DESCRIPTION: FLIGHT AND NAVIGATIONAL EQUIPMENT (CONT’D) FAR FAR FAR 121 OTHER
21/23 25/33
h. 1.1.2 Sensitive Altimeter. Check AFM Operating limitations. FSAW 97-02: Modification of Technical Standard Order (TSO) 23.1303(g) 25.1303(b) 121.305(b) 43 app. E
Altimeters. (Although 91.411 is not applicable to 121 operations, requirements should be contained in the maintenance (2) (2) 121.323(f) 91.217
program) 121.325(b) 91.411
FSAW 97-02
AC 43-6A
TSO-C10b
TSO-C88a
i. 1.1.2 Sweep-Second Hand Clock. A clock displaying hours, minutes, and seconds with a sweep-second pointer or 251303(a)(2) 121.305(c) 91.205(d)(6)
digital presentation. AC 20-94
j. 1.1.2 Free air (OAT) Temperature Indicator. Or an air temperature indicator, which provides indications that are 23.1303(d) 25.1303(a) 121.305(d) TSO-C43b
convertible to free air temperature. (1)
k. 1.1.2 Gyroscopic Bank and Pitch Indicator. Artificial horizon. In addition to two gyroscopic bank and pitch indicators 23.1303(b) 25.1303(b) 121.305(e) 91.205(d)(8)
for use at the pilot stations. FSAW 95-09B : Electronic Horizontal Situation Indicator (EHSI) Approvals (5) (5) (k) FSAW 95-09B
TSO-C4c
l. 1.1.2 Standby Horizon Additional Attitude Instrument. A third such instrument is installed in accordance with 23.1303(g) 25.1303(b) 121.305(j), TSO-C4c
121.305(k), and: (1) Is powered from a source independent of the electrical generating system; (2) Continues reliable (3) (4)
operation for a minimum of 30 minutes after total failure of the electrical generating system; (3) Operates independently of
any other attitude indicating system; (4) Is operative without selection (automatic) after total failure of the electrical
generating system; (5) Is located on the instrument panel in a position acceptable to the Administrator that will make it
plainly visible to and usable by each pilot at his or her station; and (6) Is appropriately lighted during all phases of operation.
m. 1.1.2 Gyroscopic Rate of Turn Indicator. Combined with an integral slip/skid indicator (turn and bank indicator) 25.1303(b) 121.305(f) 91.205(d)(3)
except that only a slip/skid indicator is required when a third attitude instrument system usable through flight attitudes of (4) TSO-C3e
360° of pitch and roll is installed.
n. 1.1.2 Gyroscopic Direction Indicator. Directional gyro or equivalent. 25.1303(b) 121.305(g) 91.205(d)(9)
(6) TSO-C5e,
TSO-C6d,
TSO-C7d
o. 1.1.2 Magnetic Compass. The magnetic compass must be calibrated to reflect the maximum deviation, and illuminated for 23.1303(c) 25.1303(a) 121.305(h) CAR 4b.612-3
night operations 23.1327 (3) 91.205(b)(3)
23.1547 25.1327 TSO-C7d
25.1547
p. 1.1.2 Vertical Speed Indicator. Rate of climb indicator. 25.1303(b) 121.305(i) TSO-C8d
(3)
q. 1.1.2 Speed Warning Device. Is required for turbine engine powered airplanes and for airplanes with VMO/MMO greater 23.1303(e) 25.1303(c) 91.603
than 0.8 VDF/MDF or 0.8 VD/MD. The speed warning device must give effective aural warning (differing distinctively from (1) TSO-C101
aural warnings used for other purposes) to the pilots, whenever the speed exceeds VMO plus 6 knots or MMO + 0.01. The
upper limit of the production tolerance for the warning device may not exceed the prescribed warning speed.
r. 1.1.2 Machmeter. Is Required At Each Pilot Station For Airplanes With Compressibility Limitations Not Otherwise Indicated To 25.1303(c) TSO-C95
The Pilot By The Airspeed Indicating System Required Under 25.1303(b)(1). (2)

16 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

11) COCKPIT – AVIONICS / OPERATIONS (CONT’D)

SAI DESCRIPTION: FLIGHT AND NAVIGATIONAL EQUIPMENT (CONT’D) FAR FAR FAR 121 OTHER
21/23 25/33
s. 1.1.2 Automatic Pilot System. Refer to 25.1329 for requirements. Aircraft Flight Manual must show minimum altitude 23.1329 25.1329 121.579 CAR4b.612-4
for use of autopilot. If CAT II or CAT III, aircraft autopilot can be used for lower altitudes when approved by Ops Specs. HBAW95-07
AC 25-11
AC 25.1329-1A
TSO-C9c
DESCRIPTION: POWERPLANT INSTRUMENTS
t. 1.1.1 Instrument Markings. For each required Powerplant and auxiliary power unit instrument, as appropriate to the type 23.1521 25.1521 AC 20-69
1.1.2 of instrument - 23.1541 25.1543 AC 20-88A
(a) Each maximum and, if applicable, minimum safe operating limit must be marked with a red radial or a red line; 23.1543 25.1541
(b) Each normal operating range must be marked with a green arc or green line, not extending beyond the maximum and 23.1549 25.1549
minimum safe limits; 23.1583 25.1583
(c) Each takeoff and precautionary range must be marked with a yellow arc or a yellow line; and
(d) Each engine, auxiliary power unit, or propeller speed range that is restricted because of excessive vibration stresses
must be
marked with red arcs or red lines. Check AFM Operating limitations and TCDS for approved appliances.
u. 1.1.2 Exhaust Gas Temperature Indicator. FAR 23/25 for Turbine Engine Powered Airplanes 23.1305(c) 25.1305(c) TSO-C43b
(1) (1)
v. 1.1.2 Fuel Pressure Indicator. FAR 25 for all airplanes. FAR 23 for Turbine Engine Powered Airplanes 23.1305(c) 25.1305(a) 121.307(c) CAR4.b.613(f)
(3) (1) TSO-C47
25.1337(f)
w. 1.1.2 Fuel Pressure Warning. Or a master warning means for all engines with provision for isolating the individual 23.1305(c) 25.1305(a) 121.307(k) CAR4b.
(3) (1)
warning means from the master warning means. FAR 25 for all airplanes. FAR 23 for Turbine Engine Powered
Airplanes
x. 1.1.2 Fuel Flowmeter Indicator. For each engine. FAR 23/25 for Turbine Engine-Powered Airplane 23.1305((c) 25.1305(c) 121.307(d) CAR4b.613(c)
(2) (2) TSO-C44b
23.1337(c) 25.1337(c)
y. 1.1.2 Fuel Quantity Indicator. For each fuel tank. FAR 23/25 1337(b)(1) MUST be calibrated to read Zero during level 23.1305(a) 25.1305(a) 121.307(e) CAR4b.613(b)
flight when the quantity of fuel remaining is equal to the unusable fuel supply determined under 23.959(a) / 25.959. (1) (2) 91.205((b)(9)
23.1337(b) 25.1337(b)
z. 1.1.2 Engine Pressure Ratio Indicator FAR 23/25 Turbojet Engine Powered Airplanes 23.1305(d) 25.1305(d)
(1) (1)
aa. 1.1.2 Oil Quantity Indicator. For each oil tank. 23.1305(a)(4) For all Airplanes, An Oil Quantity Indicating Device for each 23.1305(a) 25.1305(a) 121.307(h) CAR4b.613(d)
oil tank which meets the requirements of 23.1337(d). (4) (3)
23.1551 25.1337(d)
25.1551
bb. 1.1.2 Oil Pressure Indicator. For each independent pressure oil system of each engine. 23.1305(a) 25.1305(a) 121.307(g) CAR4b.604(k)
(2) (4) 91.205(b)(7)
TSO-C47
cc. 1.1.2 Oil Pressure Warning. Or a master warning means for all engines with provision for isolating the individual warning 23.1305(c) 25.1305(a) CAR4b.604(l)
means from the master warning means. 23.1305(c)(6) for Turbine Engine-Powered airplanes (6) (5)
dd. 1.1.2 Oil Temperature Indicator. For each engine. 23.1305(a) 25.1305(a) 121.307(i) 91.205(b)(7)
(3) (6) CAR4b.604(l)
TSO-C43b
ee. 1.1.2 Fire Warning Indicators. 23.1305(a)(5) is for those airplanes required to comply with 23.1203 fire detection 23.1305(a) 25.1305(a) CAR4b.485
system. (5) (7)
ff. 1.1.2 Augmentation Liquid Quantity Indicator. Appropriate for the manner in which the liquid is to be used in 25.1305(a)
operation) for each tank. (8)

17 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

11) COCKPIT – AVIONICS /OPERATIONS (CONT’D)

SAI DESCRIPTION: POWERPLANT INSTRUMENTS (CONT’D) FAR FAR FAR 121 OTHER
21/23 25/33
gg. 1.1.2 N1, N2, N3 Tachometer. To indicate the speed of the rotors with established limiting speeds for each engine. 23.1305(c) 25.1305(c) 121.307(j) CAR4b.604(o)
(5) (3) 91.205(b)(4)
TSO-C49b
hh. 1.1.2 Engine starter Indication. 25.1305(c)
(4)
ii. 1.1.2 Powerplant Ice Protection System Indicator. To indicate the functioning of the system for each engine. 23.1305(c) 25.1305(c)
(7) (5)
jj. 1.1.2 Fuel Strainer or Filter Indicator. To indicate the occurrence of contamination of the strainer or filter before it 23.997 25.997 AD 96-07-09
reaches the capacity established in accordance with 25.997. 23.1305(c) 25.1305(c)
(8) (6)
kk. 1.1.2 Oil Strainer or Filter Warning. If it has no bypass, to warn the pilot of the occurrence of contamination of the 23.1019 25.1019
strainer or filter screen before it reaches the capacity established in accordance with 25.1019(a)(2). 23.1305(c)9 25.1305(c)
(7)
ll. 1.1.2 Fuel Heat Indication. Indicate the proper functioning of any heater used to prevent ice clogging of fuel system 23.1305(c) 25.1305(c)
components. (10) (8)
mm 1.1.2 Thrust Indicator. Or a parameter that is directly related to thrust, to the pilot. The indication must be based on the 23.1305(d) 25.1305(d) CAR4b.604(q)
direct measurement of thrust or of parameters that are directly related to thrust. The indicator must indicate a change in (1) (1)
thrust resulting from any engine malfunction, damage, or deterioration. 23.1305(d)(1) for Turbojet/Turbofan engine
powered airplanes
25.1305(d)(1) for Turbojet engine powered airplanes.
nn. 1.1.2 Thrust Reverser Position Indication. Means to indicate to the flight crew when the thrust-reversing device is in 23.1305(d) 25.1305(d) CAR4b.604(t)
the reverse thrust position, for each engine using a thrust reversing device. 23.1305(d)(2) for Turbojet/Turbofan engine (2) (2)
powered airplanes. 25.1305(d)(2) for Turbojet engine powered airplanes.
oo. 1.1.2 Vibration Indicator. To indicate rotor system unbalance 25.1305(d)
(3)
pp. 1.1.2 Torque Indicator. For each engine. (Turbo-propeller powered airplanes) 23.1305(e) 25.1305(e) CAR4b.603®
(1) (1)
qq. 1.1.2 Propeller Blade Angle Position Indication. To indicate to the flight crew when the blade angle is below the 23.1305(e) 25.1305(e) 121.307(l) CAR4b.603(s)
flight low pitch position, for each propeller. (Turbo-propeller powered airplanes) (2) (2)
rr. 1.1.2 Thrust or Power Augmentation. To indicate the proper functioning of that system to the flight crew. (Turbo- 23.1305(f) 25.1305(f)
propeller powered airplanes) (If equipped)
RADIO EQUIPMENT:
ss. 1.1.2 Radio Equipment. 25.1307(d) 121.345 CAR4b.650
Two systems for two-way radio communications, with controls for each accessible from each pilot station, designed and 8300.10 Vol. 2
installed so that failure of one system will not preclude operation of the other system. The use of a common antenna system CH. 237
is acceptable if adequate reliability is shown. AC 25.10
TSO-C31d
Two systems for radio navigation, with controls for each accessible from each pilot station, designed and installed so that 25.1307(e) TSO-C32d
failure of one system will not preclude operation of the other system. The use of a common antenna system is acceptable if TSO-C37d
adequate reliability is shown. TSO-C38d
TSO-C40c
TSO-C41d
TSO-C50c
TSO-C57a
TSO-C58a
tt. 1.1.2 Radio Equipment for operations under VFR over routes navigated by pilotage. 121.347 CAR4b.605
91.205(d)

18 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

11) COCKPIT – AVIONICS / OPERATIONS (CONT’D)

SAI DESCRIPTION: RADIO EQUIPMENT (CONT’D) FAR FAR FAR 121 OTHER
21/23 25/33
uu. 1.1.2 Radio Equipment for operations under VFR over routes not navigated by pilotage or for 25.1307(e) 121.349 CAR4b.605
91.205(e)
operations under IFR or over the top. Marker beacon (1), ILS receiver (1), LFRR (1) or ADF receiver (1) (as TSO-C58a,
applicable) if VOR receivers (2), DME (1). Mics (2), & headsets (2) or headsets (2), & speaker (1).
vv. 1.1.2 Radio and Navigation Equipment for extended overwater operations and for certain other 25.1307 121.351 CAR4b.605
91.511
operations. Marker beacon (1), ILS receiver (1), LFRR (1) or ADF receiver (1) (as applicable) if VOR receivers (2), AC 121-13
DME (1). Mics (2), & headsets (2) or headsets (2), & speaker (1). PLUS LRNS (2) when VOR or ADF is unusable. 1 LRNS
may be used if approved.
ww. 1.1.2 Flight Management Systems (FMS). Verify database is current. 8300.10 Vol. 2
CH. 1 & CH. 237
AC 20-129
AC 20-130A
AC 25-15
RTCA DO178A
&B
TSO-C115A
xx. 1.1.2 Equipment for operations on which specialized means of navigation is used. Refer to 121.355 25.1307 121.355
for requirements. 121 Appendix G Operations in Reduced Vertical Separation Minimum (RVSM) Airspace. 121 app. G
yy. 1.1.2 Traffic Alert and Collision Avoidance System. In addition, the appropriate manuals required by 121.131 shall 23.1301 25.1301 121.356 91.221
contain the following information on the TCAS II System or TCAS I System, as appropriate, as required by this section: (1) 8300.10 Vol. 2
Appropriate procedures for (i) The operation of the equipment; and (ii) Proper flight crew action with respect to the CH. 237
equipment. AC 120-55a
AC 20-131A
TCAS ANTENNA. The active Mode S transponder shall have a top and bottom Omni-directional antenna. The TCAS II shall TSO-C119b
have a top directional antenna and a bottom Omni-directional or directional antenna.
(A) Directional antennas. For an aircraft installation, the TCAS II directional antenna should be located on the top
forward fuselage as close to the centerline as possible. If more than one directional antenna is provided, locate the second
antenna in a similar manner on the lower fuselage. The TCAS II antennas should be mounted on the aircraft with at least
20-db isolation from other L band frequency antennas. Since the antenna diameter may be large, some structural
considerations may be necessary and a centerline offset resulting in an angular offset of up to 5 degrees is acceptable. The
maximum height of the directional antenna is expected to be approximately 1 inch, and therefore is not considered
susceptible to icing effects in the general area of the proposed installation. Otherwise, anti-icing provisions should be
considered. Section 3 of Volume I of RTCA document DO-185 provides antenna selection and performance criteria. For
propeller driven aircraft, the location and performance of the directional antenna must be investigated for minimum blockage
and to ensure that the propellers do not interfere with system operation.
(B) Omni-directional antennas. The TCAS II antennas should be mounted on the aircraft with at least 20-db isolation
from other L band frequency antennas. The Mode S transponder antennas shall be mounted at locations chosen for
adequate isolation and signal coverage. These antennas may be standard ATCRBS transponder antennas.
(C) Structural analysis. A structural analysis of the antenna installations showing compliance with the applicable FAR
should be submitted to the FAA. This includes the structural provisions for a beam steering unit (if installed) if it is not
mounted in a standard avionics rack.
zz. 1.1.2 ATC Transponder 121.345(c) 91.215
91.413
aaa. 1.1.2 Airborne Weather Radar Equipment. No person may operate any transport category airplane (except C-46 121.357 AC 43-14
type airplanes) unless approved airborne weather radar equipment has been installed in the airplane. TSO-C63c
RTCA DO-173
TSO-C133

19 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

11) COCKPIT – AVIONICS / OPERATIONS (CONT’D)

SAI DESCRIPTION: RADIO EQUIPMENT (CONT’D) FAR FAR FAR 121 OTHER
21/23 25/33
bbb. 1.1.2 Low Altitude Windshear System Equipment. Refer to 121.358 for applicability. 121.358 8430.54
8430.59
HBAW 91-12
AC 00-54
AC 25-12
AC 120-41
AC 120-50
TSO-C117a
ccc. 1.1.2 Ground Proximity Warning / Glide Slope Deviation Alerting System. No person may operate a 121.360 8300.10 Vol. 2
turbine-powered airplane unless it is equipped with a ground proximity warning system that meets the performance and CH. 237
environmental standards of TSO-C92 or incorporates TSO-approved ground proximity warning equipment. Verify that AFM RTCA DO-161A
has info required. TSO-C92c
ddd. 1.1.2 Altitude Alerting System or Device. Refer to 91.219 for requirements. 91.219
eee. 1.1.2 Radio Altimeter. Refer to equipment requirements for lower landing minimum operations. TSO-C87
fff. 1.1.2 Global Positioning System GPS 8110.60
8300.10 Vol. 2
CH. 237
FSAW 94-32(A)
AC 20-130A
AC 20-138
TSO-C115B
TSO-C129
ggg. 1.1.2 Terrain Awareness and Warning System. Required for all airplanes mfg. After March 29, 2002. TAWS meet 121.354 TSO C151
TSO C151. Airplanes mfg. On or before March 29, 2002: May not operate after March 29, 2005 unless equipped with
TAWS TSO C151.
hhh. 1.1.2 Take Off Warning System. 121.293 requires Part 23 normal and commuter category airplanes to have takeoff 25.703 121.293 AC 25.703-1
warning systems that meet the requirements of 25.703. The system does not have to cover any device for which it is
demonstrated that takeoff with the device in the most adverse position would not create a hazardous condition.
25.703 requires and aural warning during the initial portion of the takeoff roll that the airplane is in a configuration that would
not allow a safe takeoff.
iii. 1.1.2 Landing Gear Aural Warning Device. 121.189 requires a wing activated aural means to warn that the landing 23.729(f) 25.729(e) 121.289(a) CAR4b.334(e)(2)
gear is not extended and locked for landing. This section does not apply to transport category airplanes that are required to 25.1309(c)
comply with 25.729(e) as part of type certification. 25.729(e) requires a warning to serve the same purpose as 121.189, but
does not require the warning to be activated by wing flap position. 23.729(f) requires a landing gear warning system, but
does not require the warning to be aural. This section currently requires such warning means to be both throttle and flap
position activated
jjj. 1.1.2 Aural speed Warning Device. A speed-warning device is required for turbine engine powered airplanes and for 23.1303(e) 25.1303(c) CAR4b.603(k)
airplanes with VMO/MMO greater than 0.8 VDF/MDF or 0.8 VD/MD. The speed warning device must give effective aural (1) 91.603
warning (differing distinctively from aural warnings used for other purposes) to the pilots, whenever the speed exceeds VMO
plus 6 knots or MMO + 0.01. The upper limit of the production tolerance for the warning device may not exceed the
prescribed warning speed.
kkk. 1.1.2 North Atlantic Minimum Navigation Performance Specifications (NAT/MNPS). Refer to FAR 91 - 91.703
Appendix C for requirements. Advisory Circulars 91-49, General Aviation Procedures for Flight in North Atlantic Minimum 91.705
Navigation Performance Specifications Airspace, as amended, and AC 120-33, Operational Approval of Airborne Long 91 Appendix C
Range Navigation Systems for Flight Within the North Atlantic Minimum Navigation Performance Specifications Airspace. HBAW 95-10
AC 120-33

20 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

11) COCKPIT – AVIONICS / OPERATIONS (CONT’D)

SAI DESCRIPTION: RADIO EQUIPMENT (CONT’D) FAR FAR FAR 121 OTHER
21/23 25/33
lll. 1.1.2 BRNAVRNP-10 Required Navigation Performance 10 Capability. 121 app. G 8400.10 Vol. 3
RNP-10 requires that each individual aircraft must be determined to be qualified, and appropriate FAA offices must approve CH. 1
the individual operator before the operator conducts flight in RNP-10 airspace. HBAT 98-16A
Refer to FAA Order 8400.12 for aircraft/equipment requirements. HBAT 98-15
HBAW 98-06
HBAW 98-07A
AC 90-96
ICAO 9613-
AN/937

12) COCKPIT – MAINTENANCE/OPERATIONS

SAI DESCRIPTION: FAR FAR FAR 121 OTHER
21/23 25/33
a. 1.1.2 Windows. Inspect for Delamination, scratches, crazing, and general visibility 21.183 25.775 121.367 8300.10 Vol. 3
23.775 CH. 1
b. 1.1.2 Cockpit Interiors/Fire Resistance. Look on back of cushions to identify if the seats have been blocked. It should 23.853 25.853(a) 121.215 CAR 4B.381
state that the cushion meets the requirements of 25.853(c). Review documentation of flame testing. Ac 25.853-1 - 23.855 25.855 121.312, AC 25-10
Flammability Requirements For Aircraft Seat Cushions, FSAT 96-11 - Flammability Of Airline Blankets. 23.1359 25 app. F AC 25.853-1
23 app. F

c. 1.1.1 Emergency Exit Arrangement. Each emergency exit, including a flight crew emergency exit, must be a movable 23.807 25.809 121.221 CAR 4b.362
door or hatch in the external walls of the fuselage, allowing unobstructed opening to the outside. Each emergency exit must 25.857
be operable from the inside and the outside except that sliding window emergency exits in the flight crew area need not be
operable from the outside if other approved exits are convenient and readily accessible to the flight crew area. The required
crew emergency exits are accessible under any cargo loading condition.
d. 1.1.1 Emergency Equipment. Each item of emergency and flotation equipment: (1) Must be inspected regularly in 121.309 CAR4b.646
1.1.2 accordance with inspection periods established in the operations specifications to ensure its condition for continued
1.3.2 serviceability and immediate readiness to perform its intended emergency purposes; (2) Must be readily accessible to the
crew and, with regard to equipment located in the passenger compartment, to passengers; (3) Must be clearly identified and
clearly marked to indicate its method of operation; and (4) When carried in a compartment or container, must be carried in a
compartment or container marked as to contents and the compartment or container, or the item itself, must be marked as to
date of last inspection.
e. 1.1.2 Medical Kit (if located on flightdeck.) Refer to requirements located at Section 4. Cabin-Maintenance of this job aid. 121.309(d) 91.513
121 app. A 8300.10 Vol. 3
CH. 1, AC 25-17
f. 1.1.2 Hand Fire Extinguishers for Flight Crew. At least one hand fire extinguisher must be conveniently located on 23.851 25.851 121.309(c) CAR4b.380
the flight deck for use by the flight crew. The type and quantity of extinguishing agent must be suitable for the kinds of fires 91.513
likely to occur in the compartment where the extinguisher is intended to be used and, for passenger compartments, must be AC 20-42C
designed to minimize the hazard of toxic gas concentrations. Check for Fire extinguisher security, pressure, hydrostatic test
dates, and seal.
g. 1.1.2 Protective Breathing Equipment (PBE). If there is a class A, B, or E cargo compartment, protective breathing 25.1439 121.337 CAR4b.380
equipment must be installed for the use of appropriate crewmembers. In addition, protective-breathing equipment must be 8300.10 Vol. 3
installed in each isolated separate compartment in the airplane, including upper and lower lobe galleys, in which CH. 1
crewmember occupancy is permitted during flight for the maximum number of crewmembers expected to be in the area HBAT 98-29
during any operation. Refer to 25.1439 for requirements. AC 25-9a
HBAT 98-29: Smoke Goggles and Oxygen Masks (PBE) AC 25-18
TSO-C99

21 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

12) COCKPIT – MAINTENANCE/OPERATIONS (CONT’D)

SAI DESCRIPTION: FAR FAR FAR 121 OTHER
21/23 25/33
h. 1.1.1 Oxygen Equipment and Supply. Aircraft must be equipped with Oxygen equipment per 25.1441 to 25.1453. 23.1441 thru 25.1441 thru 121.309, CAR4b.651
Oxygen/Fire extinguishers pressure vessels inspections must comply with 49 CFR 173.34, DOT, or US Coast Guard 23.1453 25.1453 121.329, 91.211
requirements. Crewmember Demand Oxygen Masks TSO-C78, Crewmember Protective Breathing Equipment TSO- 121.333, CFR 49
C116, Oxygen Mask Assembly Continuous Flow, Passenger (For Air Carrier Aircraft) TSO-C64a, Oxygen Regulators, 121.574
Demand TSO-C89 Protective Breathing Equipment TSO-C99. Check all portable and fixed oxygen bottles and fire bottles
for hydrostatic test dates.
i. 1.1.2 Seats, Berths, Safety Belts, and Harnesses. Each seat at a flight deck station must have a restraint system 23.785 25.785(g) 121.311(f) CAR4b.358
consisting of a combined safety belt and shoulder harness with a single point release that permits the flight deck occupant, 25.853 CAR4b.381
when seated with the restraint system fastened, to perform all of the occupant's necessary flight deck functions. There must 91.521
be a means to secure each combined restraint system when not in use to prevent interference with the operation of the AC 21-25A
airplane and with rapid egress in an emergency. AC 25.562-1A
Aircraft Seats and Berths (Type I Transport, 6g Forward Load) TSO-C25a, Aircraft Seats and Berths TSO-C39b, Safety TSO-22g
Belts TSO-C22g, Torso Restraint Systems TSO-C 114. TSO-39b
Ac 21-25a - Approval Of Modified Seating Systems Initially Approved Under A Technical Standard Order TSO-C 114
Ac 25-17 - Transport Airplane Cabin Interiors Crashworthiness Handbook TSO-C25a
Ac 25.562-1a - Dynamic Evaluation Of Seat Restraint Systems & Occupant Protection On Transport ,
j. 3.1.3 Approved Cockpit Check Procedures Checklist. 23.1585 25.1585 121.315 CAR4b.470
k. 1.1.2 Observer Seat. Verify installation of cockpit observer seat and all required peripheral equipment. 25.785(l) 121.581 CAR4b.358
3.1.3 25.853
l. 1.1.1 Placards. Verify mfg. required placards are installed. Refer to aircraft maintenance manual chapter 11 for data. All 23.1557 25.1557 CAR4b.730
1.3.1 placards required in either the approved AFM, the applicable operating rules, or the Certification Basis must be installed in AMM CH. 11
the airplane.
m. 1.1.1 Windshield Wiper. Or equivalent for each pilot station. 121.313(b) 91 app. A
1.1.2 AC 25-17

13) CABIN INTERIOR – MAINTENANCE / OPERATIONS

SAI DESCRIPTION: FAR FAR FAR 121 OTHER
21/23 25/33
a. 1.1.1 Compartment Interiors/Fire Resistance 23.853 25.785 121.215 CAR 4B.381
Review documentation of flame testing. 23 app. F 25.853 121.312 AC 25-10
AC 25-10 - Guidance For Installation Of Miscellaneous, Non-required Electrical Equipment 25 app. F AC 25-17
AC 25-17 - TRANSPORT AIRPLANE CABIN INTERIORS CRASHWORTHINESS HANDBOOK AC 25.853-1
AC 25.853-1 - FLAMMABILITY REQUIREMENTS FOR AIRCRAFT SEAT CUSHIONS.
b. 3.1.2 Passenger Safety Information Briefing Cards. Perform random sample and assure proper distribution. 121.571(b) AC 121-24A
c. 1.1.1 Lavatory Placard. Sign or placard stating, “Federal Law provides for a penalty of up to $2,000 for tampering with the 121.317(e)
1.1.2 smoke detector installed in this lavatory."
d. 1.1.1 Floor Surfaces. The floor surface of all areas, which are likely to become wet in service, must have slip resistant 25.793
properties.

22 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

13) CABIN INTERIOR – MAINTENANCE /OPERATIONS (CONT’D)

SAI DESCRIPTION: FAR FAR FAR 121 OTHER
21/23 25/33
e. 1.1.1 Ashtrays. If smoking is to be allowed in any other compartment occupied by the crew or passengers, an adequate 23.853(c)(1) 25.853(f) 121.215(d) CAR 4b.381(c)
number of self-contained, removable ashtrays must be provided for all seated occupants. Lavatories must have self- 23.853(d)(2) 25.853(g)
contained, removable ashtrays located conspicuously on or near the entry side of each lavatory door, except that one
ashtray may serve more than one lavatory door if the ashtray can be seen readily from the cabin side of each lavatory
served. Each receptacle used for the disposal of flammable waste material must be fully enclosed, constructed of at least
fire resistant materials, and must 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.
f. 1.1.1 Waste Receptacle. Each receptacle used for the disposal of flammable waste material must be fully enclosed, 23.853(d)(1) 25.853(h) 121.215(e), CAR 4b.381(d)
1.1.2 constructed of at least fire resistant materials, and must contain fires likely to occur in it under normal use. The capability of 25.854 121.308 AD 74-08-09
the receptacle to contain those fires under all probable conditions of wear, misalignment, and ventilation expected in service SFAR41.7
must be demonstrated by test. AD 74-08-09 R2 requires operators inclusive of B737 aircraft to inspect all lavatory paper AC 25-17
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. AC 25-17 - TRANSPORT AIRPLANE CABIN INTERIORS CRASHWORTHINESS
HANDBOOK
g. 1.1.2 Pilot Compartment Doors. A lockable door installed between the pilot compartment and the passenger 25.772 121.217 CAR 4b.356
compartment: (a) The emergency exit configuration must be designed so that neither crewmembers nor passengers need 121.219 AC 25-17
use that door in order to reach the emergency exits provided for them; and (b) Means must be provided to enable flight 121.313(f)
crewmembers to directly enter the passenger compartment from the pilot compartment if the cockpit door becomes jammed.
In any case where internal doors are equipped with louvers or other ventilating means, there must be a means convenient
to the crew for closing the flow of air through the door when necessary.
h. 1.1.1 Ventilation. Each passenger or crew compartment must be suitably ventilated. Carbon monoxide concentration may 23.831 25.831 121.219 SFAR 41.4
not be more than one part in 20,000 parts of air, and fuel fumes may not be present. In any case where partitions between
compartments have louvers or other means allowing 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.
i. 1.1.2 Carriage of Cargo in Passenger Compartments. Refer to FAR 121.285 for requirements. 23.855 25.855 121.285 CAR4b.359
121.583 91.525
121.589
j. 1.1.1 Cabin Load Capability. The structure must be designed to give each occupant every reasonable chance of escaping 23.561 25.561 121.285 CAR4b.260
serious injury in a minor crash landing when the occupant experiences the following ultimate inertia forces acting separately 91.525
relative to the surrounding structure. : (i) Upward, 3.0 g. (ii) Forward, 9.0 g. (iii) Sideward, 3.0 g on the airframe; and 4.0 g
on the seats and their attachments. . (iv) Downward, 6.0 g. (v) Rearward, 1.5 g. For equipment/ cargo in the passenger
compartments and any other large masses, these items must be positioned so that if they break loose they will be unlikely
to: (i) Cause direct injury to occupants. ; (ii) Penetrate fuel tanks or lines or cause fire or explosion hazard by damage to
adjacent systems. Or (iii) Nullify any of the escape facilities provided for use after an emergency landing. When such
positioning is not practical (e.g. fuselage mounted engines or auxiliary power units) each such item of mass shall be
restrained under all loads up to those specified previously. The local attachments for these items should be designed to
withstand 1.33 times the specified loads if these items are subject to severe wear and tear through frequent removal (e.g.
quick-change interior items).
k. 1.3.2 Galleys/Service Centers. Inspect the following: Trash bin lids for fit, Storage compartment restraints, Stationary cart 21.183 121.367
tie-downs, Lower lobe equipment/restraints, Lift operation, Galley supplies stowage.

23 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

13) CABIN INTERIOR – MAINTENANCE /OPERATIONS (CONT’D)

SAI DESCRIPTION: FAR FAR FAR 121 OTHER
21/23 25/33
l. 1.1.1 Stowage Compartments. Check for weight restriction placards and the doors for proper latching, when applicable. 23.561 25.561 121.589 CAR4b.359
Each compartment for the stowage of cargo, baggage, carry-on articles, and equipment (such as life rafts), and any other 23.787 25.787 121.285
stowage compartment must be designed for its placarded maximum weight of contents and for the critical load distribution 23.1557 25.1557
at the appropriate maximum load factors corresponding to the specified flight and ground load conditions, and to the
emergency landing conditions of § 25.561(b). 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 loads specified in paragraph (a) of this section. For stowage
compartments in the passenger and crew cabin, if the means used is a latched door, the design must take into
consideration the wear and deterioration expected in service.
m. 1.1.1 Retention of Items of Mass in Passenger and Crew Compartments and Galleys. Means must be 23.787(a)(2) 25.789 121.589 CAR4b.359
provided to prevent each item of mass (that is part of the airplane type design) in a passenger or crew compartment or 91.523
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).
n. 1.3.2 Emergency Equipment. Each item of emergency and flotation equipment: (1) Must be inspected regularly in 121.309
accordance with inspection periods established in the operations specifications to ensure its condition for continued
serviceability and immediate readiness to perform its intended emergency purposes; (2) Must be readily accessible to the
crew and, with regard to equipment located in the passenger compartment, to passengers; (3) Must be clearly identified and
clearly marked to indicate its method of operation; and (4) When carried in a compartment or container, must be carried in a
compartment or container marked as to contents and the compartment or container, or the item itself, must be marked as to
date of last inspection.
o. 1.1.2 Hand Fire Extinguishers for Passenger Compartment. Refer to 121.309 for requirements. The type and 23.851 25.851 121.309 CAR4b.381
quantity of extinguishing agent must be suitable for the kinds of fires likely to occur in the compartment where the 91.513
extinguisher is intended to be used and, for passenger compartments, must be designed to minimize the hazard of toxic gas AC 25-17
concentrations. At least two of the required hand fire extinguisher installed in passenger-carrying airplanes must contain AC 20-42C
Halon 1211 (bromochlorofluoromethane) or equivalent as the extinguishing agent. At least one hand fire extinguisher in the NFPA 10
passenger compartment must contain Halon 1211 or equivalent. Check for Fire extinguisher security, pressure, hydrostatic
test dates, and seal.
p. 1.1.2 Hand Fire Extinguishers for Cargo Compartment. At least one hand fire extinguisher must be conveniently 25.851 121.309 CAR4b.384
located for use in each class E cargo compartment that is accessible to crewmembers during flight. The type and quantity of 91.513
extinguishing agent must be suitable for the kinds of fires likely to occur in the compartment where the extinguisher is AC 25-17
intended to be used and, for passenger compartments, must be designed to minimize the hazard of toxic gas AC 20-42C
concentrations. Check for Fire extinguisher security, pressure, hydrostatic test dates, and seal NFPA 10
q. 1.1.2 Hand Fire Extinguishers for Galley Compartment. At least one hand fire extinguisher must be conveniently 25.851 121.309 CAR4b.381
located for use in each galley located in a compartment other than a passenger, cargo, or crew compartment. The type and 91.513
quantity of extinguishing agent must be suitable for the kinds of fires likely to occur in the compartment where the AC 25-17
extinguisher is intended to be used and, for passenger compartments, must be designed to minimize the hazard of toxic gas AC 20-42C
concentrations. . Check for Fire extinguisher security, pressure, hydrostatic test dates, and seal. NFPA 10
r. 1.1.2 First Aid and Emergency Medical Equipment and Protective Gloves. Approved first aid kits, and in ` 121.309 91.513
airplanes for which a flight attendant is required, an emergency medical kit. 2 Pairs of protective latex gloves, or equivalent 121 app. A 8300.10 Vol. 3
non-permeable gloves, equal in number to the number of first aid kits on board the aircraft. These gloves must be CH. 1
distributed as evenly as practicable throughout the cabin of the aircraft. AC 25-17
s. 1.1.2 Emergency Evacuation. Each crew and passenger area must have emergency means to allow rapid evacuation in 23.803 25.803 121.291 CAR4b.362
crash landings, with landing gear extended or retracted. For aircraft with a service compartment located below the main 25.819 121.570 8300.10 Vol. 2
deck which may be occupied during taxi or flight but not during take off and landing the following apply: Refer to 25.819 for 25 app. J 121 app. D CH. 77 & 85,
Lower deck service compartments (including galleys) requirements. Check Slide containers to ensure containers are Vol. 3 CH. 1
properly marked for content. Check pressure of slide inflation bottle, if visible. PL 279 Exit Row Seating Approval Inst PL 279

24 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

13) CABIN INTERIOR – MAINTENANCE /OPERATIONS (CONT’D)

SAI DESCRIPTION: FAR FAR FAR 121 OTHER
21/23 25/33
t. 1.1.1 Means for Emergency Evacuation. Each passenger carrying landplane emergency exit (other than over the 25.810 121.310 CAR4b.362
wing) that is more than 6 feet from the ground with the airplane on the ground and the landing gear extended, must have an TSO-C69b
approved means to assist the occupants in descending to the ground.
u. 1.1.2 Interior Emergency Exit Marking. Emergency Exit Access. For each Type III Exit, regardless of the passenger 23.811 25.811 121.310(b) CAR4b.362
capacity of the airplane in which it is installed, there must be placards that “if the exit is a removable hatch, state the 25.813(3)(iii) AC 45-2A, 25-
WEIGHT of the hatch and indicate an appropriate location to place the hatch after removal. 17
Refer to 121.310(b) for additional requirements.
v. 1.1.2 Emergency Exit Operating Handles. Refer to 121.310(e) for requirements. 23.811 25.811 121.310(e) CAR4b.362
w. 1.1.2 Emergency Exit Access. Access to emergency exits must be provided. Refer to 121.310(f) for requirements. In 23.813 25.813 121.310(f) CAR4b.362
addition, Except as provided by § 121.627and except for an airplane used in operations under this part on October 16, 121.310(m)
1987, and having an emergency exit configuration installed and authorized for operation prior to October 16, 1987, for an
airplane that is required to have more than one passenger emergency exit for each side of the fuselage, no passenger
emergency exit shall be more than 60 feet from any adjacent passenger emergency exit on the same side of the same deck
of the fuselage, as measured parallel to the airplane's longitudinal axis between the nearest exit edges.
x. 1.1.2 Floor-level Exits. Each floor-level door or exit in the side of the fuselage (other than those leading into a cargo or 25.807 121.310(i) CAR4b.362
baggage compartment that is not accessible from the passenger cabin) that is 44 or more inches high and 20 or more 25.813 AC 25-17
inches wide, but not wider than 46 inches, each passenger ventral exit (except the ventral exits on M-404 and CV-240 25 app. J
airplanes), and each tail cone exit, must meet the requirements of this section for floor-level emergency exits.
y. 1.1.2 Additional Emergency Exits. Approved emergency exits in the Pax compartments that are in excess of the 25.807 121.310(j) CAR4b.362
minimum number of required emergency exits must meet all of the applicable provisions of 121.310(f)(1), (2), &(3) and must 25.813 AC 25-17
be readily accessible. 25 app. J
z. 1.1.2 Ventral Exit and Tailcone Exit. Must be: (1) Designed and constructed so that it cannot be opened during flight; 25.807 121.310(k) CAR4b.362
and (2) Marked with a placard readable from a distance of 30 inches and installed at a conspicuous location near the means AC 25-17
of opening the exit, stating that the exit has been designed and constructed so that it cannot be opened during flight.
DESCRIPTION: Emergency Equipment For Extended Overwater Operations / Uninhabited
Terrain Areas
aa. 1.1.2 The required life rafts, life preservers, and survival type emergency locator transmitter (ELT) must be easily accessible in 121.339
the event of a ditching without appreciable time for preparatory procedures. This equipment must be installed in 121.352
conspicuously marked and approved locations.
bb. 1.1.2 Life Preserver. Equipped with an approved survivor locator light, for each occupant of the airplane. Check inspection 23.1415 25.801 121.339 CAR 4b.645
date of randomly selected vests. 25.1411 121.340 91.205, 91.509
25.1415 HBAW 91-14
AC 120-47
TSO-C13F,
C72c
cc. 1.1.2 Life Rafts. Enough life rafts (each equipped with an approved survivor locator light) of a rated capacity and buoyancy to 23.1415 25.801 121.339 CAR4b.645
accommodate the occupants of the airplane. Unless excess rafts of enough capacity are provided, the buoyancy and 25.1411 TSO-C70a
seating capacity of the rafts must accommodate all occupants of the airplane in the event of a loss of one raft of the largest 25.1415
rated capacity. 25 app. J
dd. 1.1.2 Pyrotechnic Signaling Device. At least one for each life raft. Uninhabited Terrain Areas 121.339 CAR4b.645
91.509
AC 120-47
TSO-C85
ee. 1.1.2 Survival Kit. Appropriately equipped for the route to be flown must be attached to each required life raft. Uninhabited 121.339 91.509
Terrain Areas 121.353 AC 120-47

25 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

13) CABIN INTERIOR – MAINTENANCE /OPERATIONS (CONT’D)

SAI DESCRIPTION: FAR FAR FAR 121 OTHER
21/23 25/33
ff. 1.1.2 Protective Breathing Equipment. If there is a class A, B, or E cargo compartment, protective breathing 25.1439 121.309 CAR4b.380
equipment must be installed for the use of appropriate crewmembers. In addition, protective-breathing equipment must be 121.329 CAR4b.651
installed in each isolated separate compartment in the airplane, including upper and lower lobe galleys, in which 121.337 HBAT 98-29
crewmember occupancy is permitted during flight for the maximum number of crewmembers expected to be in the area AC 25-9a
during any operation. Refer to 25.1439 for requirements. AC 25-17
AC 25-18
TSO-C99
gg. 1.1.2 Oxygen Equipment and Supply. Aircraft must be equipped with Oxygen equipment per 25.1441 to 25.1453. 23.1441 thru 25.1441 thru 121.309 CAR4b.651
Oxygen/Fire extinguishers pressure vessels inspections must comply with 49 CFR 173.34, DOT, or US Coast Guard 23.1453 25.1453 121.329 91.211
requirements. Crewmember Demand Oxygen Masks TSO-C78, Crewmember Protective Breathing Equipment TSO-C116, 121.333 91.405
Oxygen Mask Assembly Continuous Flow, Passenger (For Air Carrier Aircraft) TSO-C64a, Oxygen Regulators, Demand 121.574 CFR 49
TSO-C89 Protective Breathing Equipment TSO-C99. Check all portable and fixed oxygen bottles and fire bottles for
hydrostatic test dates. Check for proper pressure and security.
hh. 1.1.2 Compartment Interiors/Fire Resistance. Look on back of cushions to identify if the seats have been fire- 23.853 25.853 121.215 CAR4b.381
blocked. It should state that the cushion meets the requirements of 25.853(c). Review documentation of flame testing. 23 app. F 25 app. F 121.312 AC 25-10
Includes material for wall & ceiling. AC 25-10 - GUIDANCE FOR INSTALLATION OF MISCELLANEOUS, NON- AC 25-17
REQUIRED ELECTRICAL EQUIPMENT. AC 25.853-1 - FLAMMABILITY REQUIREMENTS FOR AIRCRAFT SEAT AC 25-25A
CUSHIONS. AC 25-853-1
TSO-39b
ii. 1.1.2 Passenger Seats, Berths, Safety Belts, and Harnesses. Refer to 25.785 for requirements. Check that 23.785 25.785(g) 121.311 CAR4b.358
seats adjacent to emergency exits do not block exit path, seats are secure in seat track (random sample), seat breakover 23.853 25.853 CAR4b.381
pressure is in accordance with operator's maintenance program (random Sample), "Fasten Seat Belt During Flight" placards CAR4b.643
are in view from all seats, seat belts have metal-to-metal latches and are in good general condition (random sample). 91.107
Aircraft Seats and Berths (Type I Transport, 6g Forward Load) TSO-C25a, Aircraft Seats and Berths TSO-C39b, Safety 91.521
Belts TSO-C22g, Torso Restraint Systems TSO-C 114. FSAW 95-03
Ac 21-25a - Approval Of Modified Seating Systems Initially Approved Under A Technical Standard Order AC 25-17
Ac 25-17 - Transport Airplane Cabin Interiors Crashworthiness Handbook AC 21-25A
Ac 25.562-1a - Dynamic Evaluation Of Seat Restraint Systems & Occupant Protection On Transport , FSAW 95-03 AC 25.562-1A
(Extended) Seat Back Break-Over AC 25.853-1
TSO-C22g
TSO-C25a
TSO-C39b
TSO-C114
jj. 1.1.2 Cabin Attendant Seats, Berths, Safety Belts, and Harnesses. Refer to 25.785 for requirements. Pull the 25.785 121.311(f) CAR4b.358
jump seat down to ensure seat retracts (those in-path of exits) Inspect seat belts for Technical Standard Order marking, 25.853 CAR4b.381
metal-to-metal latching and general condition. CAR4b.643
Aircraft Seats and Berths (Type I Transport, 6g Forward Load) TSO-C25a, Aircraft Seats and Berths TSO-C39b, Safety 91.107
Belts TSO-C22g, Torso Restraint Systems TSO-C 114. 91.521
AC 21-25A - APPROVAL OF MODIFIED SEATING SYSTEMS INITIALLY APPROVED UNDER A TECHNICAL AC 25-17
STANDARD ORDER AC 21-25A
AC 25-17 - TRANSPORT AIRPLANE CABIN INTERIORS CRASHWORTHINESS HANDBOOK AC 25.562-1A
AC 25.562-1A - DYNAMIC EVALUATION OF SEAT RESTRAINT SYSTEMS & OCCUPANT PROTECTION ON AC 25.853-1
TRANSPORT AIRPLANES TSO-C22g
TSO-C25a
TSO-C39b
TSO-C 114

26 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

13) CABIN INTERIOR – MAINTENANCE /OPERATIONS (CONT’D)

SAI DESCRIPTION: FAR FAR FAR 121 OTHER
21/23 25/33
kk. 1.1.1 Materials for Compartment Interiors. Refer to 25.853 for requirements. 23.853 25.853 121.215 CAR 4b.381
23 app. F 25 App. F 121.221 AC 25.853-1
121.312
121.314
ll. 1.1.1 Maximum Number of Seats Abreast. On airplanes having only one passenger aisle, no more than three seats 25.817
abreast may be placed on each side of the aisle in any one row.
mm. 1.1.1 Width of Aisle. Refer to 25.815 for requirements. 23.815 25.815
nn. 1.1.2 Cabin Ozone Concentration. Refer to 25.832 for requirements. 25.832 AC 120-38
oo. 1.1.2 Smoking/No Smoking Signs. If smoking is to be prohibited there must be at least one placard so stating that is 23.853(c) 25.791 121.317 CAR4b.644
legible to each person seated in the cabin. If smoking is to be allowed, and if the crew compartment is separated from the AC 25-17
passenger compartment, there must be at least one sign notifying when smoking is prohibited. Signs that notify when
smoking is prohibited must be operable by a member of the flight crew and, when illuminated, must be legible under all
probable conditions of cabin illumination to each person seated in the cabin. In addition, A placard must be located on or
adjacent to the door of each receptacle used for the disposal of flammable waste materials to indicate that use of the
receptacle for disposal of cigarettes, etc., is prohibited. Lavatories must have "No Smoking" or "No Smoking in Lavatory"
placards conspicuously located on or adjacent to each side of the entry door. Symbols that clearly express the intent of the
sign or placard may be used in lieu of letters.
pp. 1.1.2 Fasten Seat Belt Signs. Signs that notify when seat belts should be fastened and that are installed to comply with 23.791 25.791 121.317 CAR4b.644
the operating rules of this chapter must be operable by a member of the flight crew and, when illuminated, must be legible AC 25-17
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.
qq. 1.1.2 Door & Key. Between the passenger and pilot compartments, with a locking means to prevent passengers from 25.772 121.313(f) CAR4b.356
opening it without the pilot's permission. The key must be readily available for each crewmember. A means for the crew, in 121.313(g)
an emergency to unlock each door that leads to a compartment that is normally accessible to passengers and that can be 121.313(i)
locked by passengers.
rr. 1.1.2 Door placard. On each door that is the means of access to a required passenger emergency exit, to indicate that it 25.809 121.313(h) CAR4b.356
must be open during takeoff and landing
ss. 1.1.2 Placards. Verify mfg. required placards are installed. Refer to aircraft maintenance manual chapter 11 for data. All 23.1557 25.1557 CAR4b.738
placards required in either the approved AFM, the applicable operating rules, or the Certification Basis must be installed in AMM CH. 11
the airplane.

14) CABIN INTERIOR – AVIONICS /OPERATIONS

SAI DESCRIPTION: FAR FAR FAR 121 OTHER
21/23 25/33
a. 1.1.1 Entertainment Systems 23.1301 25.1301 PL 1725
RTCA/DO-160
b. 1.1.2 Lavatory Fire Protection. Each lavatory in the airplane is equipped with a smoke detector system or equivalent that 25.854 121.308 CAR 4b.381
provides a warning light in the cockpit or provides a warning light or audio warning in the passenger cabin which would be AD’s
readily detected by a flight attendant, taking into consideration the positioning of flight attendants throughout the passenger
compartment during various phases of flight. Each lavatory in the airplane is equipped with a built-in fire extinguisher for
each disposal receptacle for towels, paper, or waste located within the lavatory. The built-in fire extinguisher must be
designed to discharge automatically into each disposal receptacle upon occurrence of a fire in the receptacle.
EMERGENCY EQUIPMENT:
c. 1.1.2 Megaphones. Refer to 121.309 for requirements. A restraining means must be provided that is capable of restraining 25.1421 121.309 91.513,
the megaphone when it is subjected to the ultimate inertia. Check for Megaphone(s) security and general condition. AC 25-17

27 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

14) CABIN INTERIOR – AVIONICS /OPERATIONS

SAI DESCRIPTION: EMERGENCY EQUIPMENT (CONT’D) FAR FAR FAR 121 OTHER
21/23 25/33
d. 1.1.2 Lighting for Interior Emergency Exit Markings. Refer to 121.310(c) for requirements. 23.812 25.812 121.310(c)
e. 1.1.2 Emergency Light Operation. Refer to 121.310(d) for requirements. 23.812 25.812 121.310(d)
f. 1.1.2 Exterior Emergency lighting and Escape Route. Refer to 121.310 & 25.810 for requirements. Check 25.810 121.310(h)
general condition of emergency floor path lighting system.
g. 1.1.2 Portable lights. No person may operate a passenger-carrying airplane unless it is equipped with flashlight stowage 121.310(l) 8300.10, Vol. 3
provisions accessible from each flight attendant seat. Check condition of Flight attendant flashlight holder CH. 1
h. 1.1.2 Public Address System. No person may operate an airplane with a seating capacity of more than 19 passengers 21.305 25.819 121.318 AC 25-17
unless it is equipped with a public address system. System must be accessible for immediate use from each of two flight 25.1423
crewmember stations in the pilot compartment. Each required floor level passenger emergency exit that has an adjacent
flight attendant seat must have a microphone that is readily accessible to the seated flight attendant. Refer to 25.1423 for
requirements. Aircraft mfg. after 11/27/90 must meet 25.1423.
i. 1.1.2 Crewmember Interphone System. No person may operate an airplane with a seating capacity of more than 19 25.789 121.319 AC 25-17
passengers unless the airplane is equipped with a crewmember interphone system that: Refer to 121.319 for requirements 25.1423
j. 1.1.2 Emergency Equipment For Extended Overwater Operations / Uninhabited Terrain Areas The 121.339
required life rafts, life preservers, and survival type emergency locator transmitter must be easily accessible in the event of a
ditching without appreciable time for preparatory procedures. This equipment must be installed in conspicuously marked
and approved locations.
k. 1.1.2 Survival Type Emergency locator Transmitter. Batteries used in this transmitter must be replaced (or 25.1415(d) 121.339 91.207
recharged, if the battery is rechargeable) when the transmitter has been in use for more than 1 cumulative hour, or when 50 121.353 AC 25-17
percent of their useful life (or for rechargeable batteries, 50 percent of their useful life of charge) has expired, as established TSO-C91a,
by the transmitter manufacturer under its approval. The new expiration date for replacing (or recharging) the battery must be TSO-C126
legibly marked on the outside of the transmitter. The battery useful life (or useful life of charge) requirements of this
paragraph do not apply to batteries (such as water activated batteries) that are essentially unaffected during probable
storage intervals.
MISCELLANEOUS EQUIPMENT:
l. 1.1.2 Protective Fuses. If protective fuses are installed on an airplane, the number of spare fuses approved for that 23.1357 25.1357 121.313(a) 91.205, AC 25-
airplane and appropriately described in the certificate holder's manual. 16, 25.1357-1
m. 1.1.2 Power Supply. Refer to requirements of 25.1309, 25.1331, 25.1351(a) and (b)(1) through (4), 25.1353, 25.1355, and 23.1309 25.1309, 121.313(c) AC 20-136
23.1331 25.1331, AC 25.1309-1A
25.1431(b).
23.1351(a) 25.1351(a)
23.1351(b) 25.1351(b)
(1) thru (b)(4) (1) thru( b)(4)
23.1353, 25.1353,
23.1365 25.1355
23.1431(b) 25.1431(b)

28 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

15) GENERAL CARGO COMPARTMENT REQUIREMENTS – AVIONICS AND / OR MAINTENANCE

SAI DESCRIPTION: FAR FAR FAR 121 OTHER
21/23 25/33
a. 1.3.1 Compartment Inspection. 21.183 121.367 43 app. D
1.3.2 Perform inspection in electrical/electronics compartment(s). Inspect for cleanliness, poor condition, loose/missing 23.787 121.221(a) 8300.10 Vol. 3
equipment, deterioration breakage leakage, corrosion, proper installation, and other indications of defects. 23.855 (1) thru CH. 1
(a)(4) HBAT 97-12A
Pay particular attention to cargo and container handling systems, lighting, smoke detectors & fire extinguishers (if HBAW 97-12A
applicable), paneling, cargo pit tape installation/adhesion, leaking and corrosion including that which may normally be AC 25-18
concealed by compartment liners and paneling. AD 93-07-15
AMM
Ensure an Airworthiness Directive search for particular Make and Model aircraft is accomplished. (I.e. Cargo doors, weight
restrictions, etc.)

Ensure any relief given in the operator’s MEL is based on the MMEL or other approved data (i.e. STC or TC)

Ensure CAMP includes all aspects of the Cargo installation.

b. 1.3.1 Placards. Verify mfg. required placards are installed. Refer to aircraft maintenance manual chapter 11 for data. All 23.1557 25.1557 CAR4b.738
placards required in either the approved AFM, the applicable operating rules, or the Certification Basis must be installed in AMM CH. 11
the airplane.
c. 1.1.1 In any case where internal doors are equipped with louvers, or other ventilating means, there must be a means convenient 121.217
to the crew for closing the flow of air when necessary.
d. 1.1.1 Each passenger or crew compartment must be suitable ventilated. Ref. FAR 25.831 or CAR 4b.371, as applicable. 25.831 121.219 4b.371
e. 1.1.1 Each compartment occupied by flight crew or passengers must be covered with at least flash, fire, or flame resistant 25.853(a) to 4b.381(a) to
material, as prescribed for the area, by the applicable regulation. FAR 25, crew/passengers compartments must be lined 25.853 (h) 4b.381 (f)
with materials tested in compliance with FAR 25, Subpart F, Part IV V, or I as applicable to the compartment
area/component. CAR 4b aircraft must meet CAR 4b.381 requirements.
Note: Lining of the compartments depends on the certification basis of the aircraft, for example the B-747 main deck class
"E" compartment is not completely lined.
f. 1.1.2 Each compartment must be designed so that, when used for storing cargo or baggage, it meets the requirements of this 25.857 4b.382(c)
paragraph. The compartment must meet one of the class requirements of FAR 25.857 or CAR 4b.382(c) and CAR 4b.383(a) to
4b.383(a) to (e). 4b.383(e).
g. 1.1.1 Wires, cables, fluid lines, and equipment. Radios (including CVR & DFDR installations forward of the rear bulkhead), or 25.855(e) to 4b.382(a) to
accessories, whose damage, failure and/or sources of heat could affect the safety of flight, can not be exposed. They must 25.855(i) 4b.382(d)
be protected, insulated and shielded. Cargo compartments must met specified individual fire detection and protection
requirements of this section. NOTE: FAA Inspector should read specific requirements for each class compartment.
h. 1.1.2 Required crew emergency exists must be accessible under all cargo loading conditions. Cockpit flight crews emergency 25.809(a) & 4b.383(e)(5)
exits can not be located within the "E" compartment. For aircraft which cockpit emergency side windows and/or top hatch (b) 4b.362(a)
can not be opened from outside, the nearest suitable most forward main cabin exit is considered as a required flight crew 25.857(e)(5)
emergency exit.
i. 1.1.1 Major alterations of aircraft modified to cargo freighters, including palletized restrain systems, cargo doors, etc., must be 21.113
documented in compliance with FAA approved data (TCDS, STC and TSO C-90). Only TSO/PMA parts (FAR 21.303) may
be utilized for the modification. The modifications must be reflected in the aircraft FAA approved AFM.
Note: The weight and balance supplement will contain the modification information. Also, intermix of restraint components
must be addressed if the operator intends to utilize other OEM parts. This is a major alteration.
j. 1.1.1 All aircraft must be equipped with passengers and crew baggage/cargo compartments, bins and galleys capable of retaining 25.789(a)
items of mass (Ref FAR 25.2). and (b)

29 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

15) GENERAL CARGO COMPARTMENT REQUIREMENTS – AVIONICS AND / OR MAINTENANCE (CONT’D)

SAI DESCRIPTION: FAR FAR FAR 121 OTHER
21/23 25/33
k. 1.1.1 Aircraft compartments occupied by passengers or crewmembers ("A" or B"), must be properly ventilated. An outside air 25.831(a) to 121.578 4b.371(a) to
supply of no less than 0.55 pounds per minute (10 qubic feet per minute), must be maintained in all areas occupied by 25.831(g), 4b.371(e)
passengers or flight crew. Pressurized aircraft must be able to maintain an 8,000 feet cabin pressure altitude. The 25.841 &
compartments must be free of noxious gases or fumes or other dangerous air contamination. 25.832

"E" cargo compartments are sealed vessels within the pressurized vessel; flow of air in "E" compartment is controlled by
flight crew using the "E" compartment air flow control valve and closing the 9G bulkhead sealed door. Ozone concentration
must also meet the requirements of FAR 25.853 and 121.578.
l. 1.1.1 Aircraft's existing cargo restrain system installation, (restrain system, pallets and nets), must be properly certificated, (FAR TSO C90 OR
21.303), identified (FARs 21.607 or FAR 45.11/45.13), comply with manufacturer's specifications and have a maintenance STC
program in compliance with FAR 25.1529.

Note: The authorized ULD's for a particular aircraft configuration should be noted in the operator’s manuals. Also, non-
certified ULD's are allowed on certain aircraft however, a maintenance program must be shown that prevents these ULD's
from becoming a hazard to the aircraft.
m. 1.1.1 FAR 25.787(c) requires that if cargo compartment lamps are installed, each lamp must be installed so as to prevent contact 25.787(c)
between the lamp bulb and cargo (protective covering). In addition to illuminating the cargo compartment during ground
handling and maintenance operations, the ceiling lights in commercial airplane cargo compartments are part of an important
safety system. These light assemblies are a component of the cargo lining and are designed to contribute to the smoke- and
Fire-containment requirements of various aviation regulatory agencies. However, if a light lens assembly is damaged,
missing, or modified, the bulb could become a fire ignition source. In addition, if the light lens were missing on some Newer
commercial airplane models, the cargo compartment would no longer meet its certification requirements for fire
containment.
n. 1.1.2 Main cabin utilized for cargo only must be equipped with a 9g barrier in compliance with this section. The floor, ceiling, 25.561(b)(3) 4b.260(a)
walls and rear bulkhead as well as all other compartment components must also meet all of their airworthiness requirements
listed in this section. If classified as a class "E", the compartment must meet all the applicable FAR 25 or CAR 4b
requirements of an "E" compartment.
Note: A class "E" compartment may have a restraint system that is certified to the 9g loading requirement and therefore a
barrier of net is not required. This also requires type 1 ULD’s

16) CARGO COMPARTMENT CLASSES – AVIONICS AND / OR MAINTENANCE

SAI DESCRIPTION: FAR FAR FAR 121 OTHER
21/23 25/33
a. 1.1.1 Class- A -Cargo Compartments. Compartment in which fire therein would be readily discernible to a member of 25.851(a) 121.221(b) CAR 4b.381(f)
1.1.2 the crew while at his station. 25.853 121.221(b) CAR 4b.383(a)
25.855 (1) 91.525
1. All parts of a Class “A” compartment (Main cargo Cabin) can be entered and occupied during flight, by a member of 25.857(a) 121.221(b) HBAT 97-12A
the crew. 25 app. F (2) HBAW 97-12A
121.223 AC 25-17
2. There must be a hand fire extinguisher available for each Class A compartment. 121.309 8110.27A
AC 21-17
3. The compartment must also meet the requirements of FAR 25.853 or CAR 4b.381. AC 25-18

30 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

16) CARGO COMPARTMENT CLASSES – AVIONICS AND / OR MAINTENANCE (CONT’D)

SAI DESCRIPTION: FAR FAR FAR 121 OTHER
21/23 25/33
b. 1.1.1 Class- B -Cargo Compartments (Small main cabin compartments). Cargo and baggage 25.787 121.221(c) CAR 4b.381(f)
1.1.2 compartments are classified in the "B" category if enough access is provided while in flight to enable a member of the crew 25.851(a)(3) 121.221(c) CAR 4b.382(c)
to effectively reach all of the compartment and its contents with a hand fire extinguisher. 25.855(b) (1) CAR 4b.383(b)
25.857(b) 121.221(c) CAR
1. It must have a separate approved smoke or fire detector system to give warning at the pilot or flight engineer station. 25 app. F (2) 4b.383(b)(2)
121.221(c) CAR
2. There must be a hand fire extinguisher available for class “B” compartments. (3) 4b.383(b)(3)
121.223 CAR
3. It must be constructed with flame resistant materials and lined with at least fire resistant material, except that 4b.383(b)(4)
additional service lining of flame resistant material may be used. 91.525
HBAT 97-12A
4. If cargo compartment lamps are installed, each lamp must be installed so as to prevent contact between lamp bulb and HBAW 97-12A
cargo. AC 25-17
8110.27A
Compartments located immediately behind the cockpit, (separated by a wall and door), and accessible to the flight AC 21-17
crew/dead heads in flight. If equipped with jump seat installations, and/or galley, potty, life raft, technical library, and/or AC 25-18
where "required emergency exits are located, for aircraft with cockpit windows that can not be open from the outside",
and/or where the "E" compartment Air Flow Shut Off Valve Control Handle is located, are classified as Class "B"
compartments. The compartment must be located forward of the 9G barrier, it must be properly ventilated, protected by the
9G barrier or 9G net/smoke curtain combination against noxious fumes or smoke. Above described "B" compartment can
not be classified as part of the class "E" compartment.
c. 1.1.1 Class- C -Cargo Compartments Cargo and baggage compartments are classified in the "C" category if they do 25.787 121.221(d) CAR 4b3.81(f)
1.1.2 not conform to the requirements for the "A", "B", "D", or "E" categories. Each Class C compartment must comply with the 25.855(b) 121.223 CAR 4b.382(c)
following:: 25.855(c) 121.314 CAR 4b.383(c)
25.855(d) 121 app. L 4b.383(c)(1)(I)
1. I t must have a separate approved smoke or fire detector system to give warning at the pilot or flight engineer station. 25.857(c) 4b.383(C)(1)(ii)
25.857(c)(1) 4b.383(c)(2)
2. It must have an approved built-in fire extinguishing system controlled from the pilot or flight engineer station. 25.857(c)(2) 4b.383(c)(3)
25.857((c)(3) 4b.383(c)(4)
3. It must be designed to exclude hazardous quantities of smoke, flames, or extinguishing agents from entering into any 25.857(c)(4 ) 91.525
compartment occupied by the crew or passengers. HBAW 97-12A
HBAT 97-12A
4. It must be ventilated and draft controlled, so when the fire extinguishing agent is discharged, it can control any fire TSO-C1
that may start in the compartment. 8110.27A
AC 21-17
5. It must be lined with fire resistant material, except that additional service lining of flame resistant material may be used. AC 25-18
(Aircraft certificated under FAR 25, "C" compartment)

6. It must be constructed with flame resistant materials and lined with at least fire-resistant material.
(Aircraft certificated under CAR 4b, "C" compartment)

7. If cargo compartment lamps are installed, each lamp must be installed so as to prevent contact between lamp bulb and
cargo.

AC 25-17 – TRANSPORT AIRPLANE CABIN INTERIORS CRASHWORTHINESS HANDBOOK

31 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

16) CARGO COMPARTMENT CLASSES – AVIONICS AND / OR MAINTENANCE (CONT’D)

SAI DESCRIPTION: FAR FAR 25 FAR 121 OTHER
21/23
d. 1.1.1 Class- D -Cargo Compartments. Note: As of March 19, 2001 all class "D" compartments need to 25.855(d) 121.221(e) CAR 4b.382(c)
1.1.2 25.855(h)(2) 121.221(e) CAR4b.383(d)
be converted to C or E compartments! Cargo and baggage compartments are classified in the "D" category if they 25.855(h)(3) (2). CAR
are so designed and constructed that a fire occurring therein will be completely confined without endangering the safety of
121.221(e) 4b.383(d)(1)
the airplane or the occupants. Each Class D compartment must comply with the following:
(3) CAR
121.221(e) 4b.383(d)(2)
1. It must have a means to exclude hazardous quantities of smoke, flames, or noxious gases from entering any
(4) CAR
compartment occupied by the crew or passengers.
121.223 4b.383(d)(3)
121.314 91.525
2. It must be ventilated and draft controlled, so when the fire extinguishing agent is discharged, it can control any fire that
121 app. L HBAT 97-12A
may start in the compartment
HBAW 97-12A
AC 25-17
3. It must be completely lined with fire resistant material. Consideration must be given to the effect of heat within the
AC 25-18
compartment on adjacent critical parts of the airplane. (Aircraft certificated under FAR 25, "D" compartment)
8110.27A
4. Compartments must be constructed with flame resistant materials and completely lined with fire resistant materials
(Aircraft certificated under CAR 4b, "D" compartment)

5. Main cabin utilized for cargo only must be equipped with a 9g barrier in compliance with this section. The floor, ceiling,
walls and rear bulkhead as well as all other compartment components must also meet all of their airworthiness
requirements listed in this section.

NOTE: Class D cargo compartments must be converted or retrofitted to meet the standards of Class C or, for all-cargo
operations, Class E compartments. Such conversions applicable for transport category airplanes type-certificated after
January 1, 1958, must be accomplished on or before March 19, 2001.
e. 1.1.1 Class- E -Cargo Compartments.. The Class “E” compartment is designed only to be used for 25.787 121.219 CAR 4b.381(f)
1.1.2 25.855(b) to 121.221(f) CAR 4b.382(c)
the carriage of cargo. Flight crew/s have no access to "E" compartment while in flight. Seat installation is not
25.855(h) 121.223 CAR 4b.383(e)
authorized in "E" compartments. Each Class E compartment must comply with the following::
25.857(e) 121.314 CAR
25.857(e)(2) 121 app. L 4b.383(e)(1)
1. Main Cabin must be constructed with flame resistant materials and completely lined with fire resistant material. 25.857(e)(3) CAR
Note: This depends on the certification basis of the TC or STC. Some aircraft do not have the Class “E” compartment 25.857(e)(4) 4b.383(e)(2)
fully lined. CAR
4b.383(e)(3)
2. It must have a separate system of an approved type smoke or fire detector to give warning at the pilot or flight engineer CAR
station. The compartment immediately behind the pilot does not meet this requirement. FAR 25.858, FAR 121.221(f)(2) 4b.383(e)(4)
and CAR 4b.382(e)(2). 91.525
HBAW 97-12A
3. It must have a means to shut off the ventilating airflow to or within the compartment and the controls for that means HBAT 97-12A
must be accessible to the flight crew in the crew compartment. TSO-C1
8110.27A
4. It must have a means to exclude hazardous quantities of smoke, flames, or noxious gases from entering the flight AC 21-17
crew compartment. The "E" Compartment air shut off valve handle can not be located within the "E" compartment. AC 25-18

5. If instead of a solid 9g metal barrier, a 9g net is used, the 9G Net must include a smoke curtain installation forward of
the barrier.

6. The compartment must be completely sealed, including the forward 9G barrier or net.

32 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

16) CARGO COMPARTMENT CLASSES – AVIONICS AND / OR MAINTENANCE (CONT’D)

SAI DESCRIPTION: FAR FAR 25 FAR 121 OTHER
21/23
Class- E -Cargo Compartments (Cont’d)
Note: MEL considerations: If the smoke barrier is damaged the cockpit door must be functional and able to prevent smoke
from entering the cockpit.

7. Required crew emergency exits must be accessible under all cargo loading conditions.

8. If cargo compartment lamps are installed, each lamp must be installed so as to prevent contact between lamp bulb and
cargo.

AC 25-17 - TRANSPORT AIRPLANE CABIN INTERIORS CRASHWORTHINESS HANDBOOK

AC 25-18 - TRANSPORT CATEGORY AIRPLANES MODIFIED FOR CARGO SERVICE
f. 1.1.1 Cargo compartments must be tested as per FAR 25, Appendix F, Part III, FAR 121.221(f)(3) & (4) – Test Method To 25.855(b) 121.221(a) CAR 4b.359
Determine Flame Penetration Resistance. Each compartment occupied by the crew or passengers, (including the (3) CAR.4b.382(c)
compartment immediately behind the cockpit), need to be tested only to FAR 25, Appendix F, Part I or II, and need to meet 121.221
only that requirement. Cargo compartments must meet FAR 25.855(a) through (c) and FAR 121.215(a) through (e). (f)(1)
Note: This depends on the certification basis of the TC or STC 121.287
121.312(a)
(1) & (c)
g. 1.1.1 The cargo compartment may not contain exposed controls, wiring, lines, equipment, radios, or accessories, whose damage 25.855(e)(1) 121.221(a) CAR 4B.382(a)
or failure would affect the aircraft safe operation, unless the items are protected (Shielded), so it cannot be damaged by the 25.855(e)(2) (1)
movement of cargo, and their breakage or failure will not create a fire hazard.

DFDR and/or CVRs, attached to the forward side of the Rear Pressure Bulkhead, must be protected as required under FAR
25.855(e)&((g), 121.211(a)&(b), and 121.221(a)(1).
h. 1.1.1 There must be means to prevent cargo or baggage in the compartment, from interfering with the functioning of the fire 25.855(f) 121.221(a) CAR4b.382(b)
protective feature of the compartment. (2)
i. 1.1.1 Sources of heat within the compartment must be shielded and insulated to prevent igniting the cargo or baggage. 25.855(g) 121.221(a) CAR 4b.382(d)
(4) and
(f)(4)
j. 1.1.1 Class- E -Cargo Compartments (Cont’d) The required crew emergency exits must be accessible under any 25.857((e)(5) CAR 4b382(e)(5)
1.1.2 loading conditions. On airplanes that have two cockpit windows that cannot be opened from outside, the most forward left 8110.27A
main external passenger door is considered a required emergency exit.
Note: Emergency exit markings vary from aircraft to aircraft depending again on the requirements of the TC or STC. Some
aircraft have the cockpit windows as the required emergency exit and therefore are not required to have the L-1 door
marked as an emergency exit)
k. 1.1.1 FAR 25 and CAR 4B, Regardless of airplane configuration (Passengers or “E” compartment), the entire pressure vessel 25.831(a) 121.219 4b.370 to 4b.375
must be properly ventilated to provide each occupant with an airflow containing at least 0.55 pounds r and/or 10 cubic feet
per minute of outside fresh air. Regardless of altitude the entire pressure vessel must be maintained at no more than 8,000
feet pressure altitude. The airflow to the compartment immediately behind the cockpit can not be shut off.
The required ventilating airflow also applies to “E” compartment, except that the flow of air to or within, the compartment
must be controlled and shut off in case of fire, smoke or noxious fumes emanate from it.

33 of 34
 AIRCRAFT CONFORMITY JOB AID R1 0
0 2 /2 1 /0 2

16) CARGO COMPARTMENT CLASSES – AVIONICS AND / OR MAINTENANCE (CONT’D)

SAI DESCRIPTION: FAR FAR 25 FAR 121 OTHER
21/23
l. 1.1.1 Large transport airplane main cabin to be approved as an “E” compartment 21.303 25.1519 121.707 CAR 4b.740(c),
1.1.2 21.607 25.1529 CAR 4b.740-1(b)
Major alterations of passenger aircraft main passenger cabin modified to “E” type cargo compartment freighters, 25.1581(a) CAR 4b,740(
including installed palletized restrain system, cargo door/s, etc. must be performed in compliance with FAA approved (1) to (3) b)(1) TCDS,
data and properly documented. 25.1583(c) STC, PMA TSO
C-90
TSO/PMA parts must be utilized for the modification. The modifications must be reflected (included), in the aircraft FAA
approved Aircraft Flight Manual (AFM), WT&BAL Report, Equipment List, Loading Schedule and in the aircraft’s FAA
approved inspection program, as follows:

1. - Supplemental Type Certificate (STC) design data for the Conversion to “E” compartment installation, description of
system, provisions for ventilation and control of air flow, normal and abnormal operational instructions, requirements and
limitations for cargo door, 9G Bulkhead, floors modified to higher load bearing capability, cargo pallets restraint system,
pallets and cargo nets must be included in the FAA Airplane Flight Manual (AFM).

2. - Installation and description of each component, plus identification and physical location in aircraft, and cargo restrain
system and limitations, must be included in Aircraft FAA approved Weight and Balance Report and Equipment List;
Loading instructions, identifying all “E” compartment stations maximum loading capacity must also be included in
WT&BAL Loading Schedule

3. - An inspection/maintenance program for converted “E” compartment installation, including STC designed data, cargo
door, 9G Bulkhead, floors modified to higher load bearing capability, cargo pallets restrain system, pallets and cargo nets
must be included in Aircraft FAA approved CAMP.

Reference: CAR 4b are not included because they are almost identical to FAR 25. FAR 21.31, 21.93, 21.97, 21.113,
21.303, 21.305, 21.502, 21.607, 25 Subpart D, 25.601 to 25.613, 25.803, 25.609(b), 25.831 to 25.833, 25.841 and 25.843,
25.1529, 121.370, TCDS and Manufacturer’s SRM and maintenance manuals.

34 of 34