SECTION 1 JAR–26

1–0–1 13.07.98

SECTION 1 – REQUIREMENTS

1 GENERAL

This Section contains the Requirements for compliance with JAR–26.

2 PRESENTATION

2.1 The requirements of JAR–26 are presented in two columns on loose pages, each page beingidentified by the date of issue or the Change number under which it is amended or reissued.

2.2 Sub-headings are in italic typeface.

2.3 Explanatory Notes not forming part of the requirements appear in smaller typeface.

2.4 New, amended and corrected text will be enclosed within heavy brackets until a subsequent‘Change’ is issued.

JAR–26 SECTION 1

13.07.98 1–0–2

INTENTIONALLY LEFT BLANK

SECTION 1 JAR–26

1–A–1 13.07.98

JAR 26.1 Applicability

(a) This JAR–26 prescribes specificadditional airworthiness requirements withwhich operators must ensure that compliance hasbeen established if operating in accordance withthe Part of JAR–OPS relevant to the particulartype of operation –

(1) Subpart B relates to CommercialAir Transportation (Aeroplanes);

(2) Subpart C relates to GeneralAviation (Aeroplanes);

(3) Subpart D relates to CommercialAir Transportation (Helicopters); and

(4) Subpart E relates to GeneralAviation (Helicopters).

(b) The requirements of JAR–26 areapplicable as follows –

(1) For Subpart B from 1 October1999, unless otherwise indicated;

(2) Reserved;

(3) Reserved;

(4) Reserved.

(c) Until the final implementation ofJAR–26, current national aviation requirementsapply.

JAR 26.2 Terminology

‘Airworthiness Exemption’: An exemption toan airworthiness requirement granted by aNational Authority in accordance with its TypeCertification Procedures. It is not meant toinclude those exemptions granted in accordancewith JAR–OPS 1.010 or 3.010.

‘Manufactured’: The date on which theinspection records show that an aircraft is first ina condition for safe flight. (See IEM No. 1 toJAR 26.2)

‘Maximum Certificated Passenger SeatingCapacity (MCPSC)’: The maximum number ofpassenger seats, excluding crew seats, approvedduring type certification of the aircraft, andspecified in the Type Certificate Data Sheet.(See IEM No. 2 to JAR 26.2)

‘Maximum Approved Passenger SeatingConfiguration (MAPSC)’: The maximumpassenger seating capacity of an individualaeroplane, excluding pilot seats or flight deckseats and cabin crew seats as applicable, used bythe operator, approved by the Authority andspecified in the Operations Manual.

‘Type Certificated (TC)’: Reference to whenan aircraft was type certificated means the dateof TC issuance, or equivalent, in the country oforigin (i.e. the State where the first TC wasissued).

JAR 26.3 Equivalent Safety Findings(ESF)(See IEM 26.3)

Equivalent Safety Findings included in theType Certification basis of an aircraft made andaccepted by the national Authority remain validregarding JAR–26 or equivalent requirements.

JAR 26.5 Airworthiness Exemptions(See IEM 26.5)

(a) Previously Granted AirworthinessExemptions: Airworthiness Exemptions granted,regarding JAR–26 or equivalent requirements, toan aircraft’s Type Certification Basis, C of Adocumentation or Operations approvaldocumentation prior to the implementation ofthis JAR–26 (as appropriate in each State), areto be notified to his Authority by the AOCholder who is adding an aircraft to his fleet,when that aircraft is being moved from one JAAregistry to another.

(b) Airworthiness Exemptions granted afterJAR–26 implementation: After the date ofJAR–26 implementation requests forAirworthiness Exemptions regarding JAR–26requirements, will be made in accordance withthe applicable JARs for certification oroperations. In the case of such jointly agreedairworthiness exemptions, there is no additionalreporting requirement to the NAA.

SUBPART A – GENERAL

JAR 26.2 (continued)

JAR–26 SECTION 1

13.07.98 1–A–2

INTENTIONALLY LEFT BLANK

SECTION 1 JAR–26

01.03.05 1–B–1 Amendment 1

EMERGENCY PROVISIONS

JAR 26.100 Location of emergency exits

(Text derived from: JAR 25.807(d)(7) at Chg. 13plus Amdt 93/1, 8/3/93)

Except for aeroplanes having an emergencyexit configuration installed and approved priorto 1 April 1999, an operator shall not operate alarge aeroplane having a MAPSC of more than19 with an emergency exit deactivated, whensuch a deactivation results in an emergency exitbeing more than 18.288 m (60 feet) from anyadjacent passenger emergency exit on the sameside of the same deck of the fuselage, asmeasured parallel to the aeroplane’s longitudinalaxis between the nearest exit edges.

JAR 26.105 Emergency exit access

(Text derived from: JAR 25.813(d) to (f) atChg. 8, 30/11/81)

An operator shall not operate a largeaeroplane that does not comply with thefollowing –

(a) Reserved

(b) If it is necessary to pass through apassageway between passenger compartments toreach any required emergency exit from any seatin the passenger cabin, the passageway must beunobstructed. However, curtains may be used ifthey allow free entry through the passageway.

(c) No door may be installed in anypartition between passenger compartments.

(d) If it is necessary to pass through adoorway separating the passenger cabin fromother areas to reach any required emergency exitfrom any passenger seat, the door must have ameans to latch it in the open position. Thelatching means must be able to withstand theloads imposed upon it when the door issubjected to the ultimate inertia forces, relativeto the surrounding structure, prescribed inJAR/FAR Part 25.561(b), or equivalent, at thechange/amendment level specified in therelevant Type Certificate Data Sheet, orequivalent document.

JAR 26.110 Emergency exit markings

(Text derived from: JAR 25.811(a) to (d), and(f)&(g), Chg. 8, 30/11/81, and JAR 25.811(e) atChg. 14, 27/5/94)

An operator shall not operate a largeaeroplane after 1 April 2001, that does notcomply with the following –

(a) Each passenger emergency exit, itsmeans of access, and its means of opening mustbe conspicuously marked.

(b) The identity and location of eachpassenger emergency exit must be recognisablefrom a distance equal to the width of the cabin.

(c) Means must be provided to assist theoccupants in locating the exits in conditions ofdense smoke.

(d) The location of each passengeremergency exit must be indicated by a signvisible to occupants approaching along the mainpassenger aisle (or aisles). There must be –

(1) A passenger emergency exitlocator sign above the aisle (or aisles) neareach passenger emergency exit, or at anotheroverhead location if it is more practicalbecause of low headroom, except that onesign may serve more than one exit if each exitcan be seen readily from the sign;

(2) A passenger emergency exitmarking sign next to each passengeremergency exit, except that one sign mayserve two such exits if they can both be seenreadily from the sign; and

(3) A sign on each bulkhead ordivider that prevents fore and aft vision alongthe passenger cabin to indicate emergencyexits beyond and obscured by the bulkhead ordivider, except that if this is not possible thesign may be placed at another appropriatelocation.

(e) The location of the operating handle andinstructions for opening exits from the inside ofthe aeroplane must be shown in the followingmanner –

(1) Each passenger emergency exitmust have, on or near the exit, a marking thatis readable from a distance of 762 mm(30 inches).

(2) Each passenger emergency exitoperating handle and the cover removalinstructions, if the handle is covered, must –

SUBPART B – COMMERCIAL AIR TRANSPORT (AEROPLANES)

JAR–26 SECTION 1

Amendment 1 1–B–2 01.05.03

(i) Be self-illuminated with aninitial brightness of at least 160 micro-lamberts (with the illumination level notdecreasing in service to below100 micro-lamberts); or

(ii) Be conspicuously locatedand well illuminated by the emergencylighting even in conditions of occupantcrowding at the exit.

(3) Reserved

(4) All Type II and larger passengeremergency exits with a locking mechanismreleased by motion of a handle, must bemarked by a red arrow with a shaft at least19 mm (0.75 inch) wide, adjacent to thehandle, that indicates the full extent anddirection of the unlocking motion required.The word OPEN must be horizontally situatedadjacent to the arrow head and must be in redcapital letters at least 25 mm (1 inch) high.The arrow and word OPEN must be locatedon a background which provides adequatecontrast. (See IEM 26.110(e)(4))

(f) Each emergency exit that is required tobe openable from the outside, and its means ofopening must be marked on the outside of theaeroplane. In addition, the following apply –

(1) The outside marking for eachpassenger emergency exit in the side of thefuselage must include one 50.80 mm (2 inch)coloured band outlining the exit.

(2) Each outside marking includingthe band, must have colour contrast to bereadily distinguishable from the surroundingfuselage surface. The contrast must be suchthat if the reflectance of the darker colour is15% or less, the reflectance of the lightercolour must be at least 45%. ‘Reflectance’ isthe ratio of the luminous flux reflected by abody to the luminous flux it receives. Whenthe reflectance of the darker colour is greaterthan 15%, at least a 30% difference betweenits reflectance and the reflectance of thelighter colour must be provided.

(3) In the case of exits other thanthose in the side of the fuselage, such asventral or tail cone exits, the external meansof opening, including instructions ifapplicable, must be conspicuously marked inred, or bright chrome yellow if thebackground colour is such that red isinconspicuous. When the opening is locatedon only one side of the fuselage, aconspicuous marking to that effect must beprovided on the other side.

(g) Each sign required by sub-paragraph (d)of this paragraph may use the word ‘exit’ in itslegend in place of the term ‘emergency exit’.

FIRE PROTECTION

JAR 26.150 Compartment interiors(See IEM 26.150)

(Text derived from: JAR 25.853 and Appendix Fat Chg. 14, 27/5/94, JAR 25.853(e) at Chg. 13 plusAmdt 91/1, 12/4/91 and JAR 25.791 at Chg. 8,20/11/81)

For each compartment occupied by the crewor passengers the following apply –

(a) With respect to flammability, anoperator shall not operate a Large Aeroplanethat contains materials (including finishesapplied to the materials) that do not meet theapplicable test criteria prescribed in Appendix F,Part I of this JAR–26 or other approvedequivalent methods, unless the aeroplane wasType Certificated against an earlier standard inwhich case that earlier standard applies.However, upon any major replacement of anyindividual group of components as specified inAppendix F, Part I, sub-paragraph (a)(1)(i), suchas interior ceiling panels, wall panels, etc., thisindividual group of components must complywith Appendix F, Part I of this JAR–26.

(b) With respect to seat cushions, exceptthose on flight crew member seats, an operatorshall not operate a large aeroplane, TypeCertificated after 1 January 1958, that does notcomply with the fire protection requirements ofAppendix F, Part II.

(c) (1) With respect to heat release (otherthan for lavatory interiors or flight deck), forinterior ceiling and wall panels (other thanlighting lenses), partitions, and the outersurfaces of galleys, large cabinets andstowage compartments (other than underseatstowage compartments and compartments forstowing small items, such as magazines andmaps), an operator shall not operate a largeaeroplane, Manufactured on or after20 August 1988, but prior to 20 August 1990,and having a MAPSC of more than 19, thatdoes not comply with the heat release ratetesting provisions of Appendix F Part IV,except that the total heat release over the firsttwo minutes of sample exposure must notexceed 100 kilowatt-minutes per squaremetre, and the peak heat release rate must notexceed 100 kilowatts per square metre.

JAR 26.110(e)(2) (continued) JAR 26.110 (continued)

SECTION 1 JAR–26

01.03.05 1–B–3 Amendment 1

(2) With respect to heat release andsmoke density, (other than for lavatoryinteriors or flight deck) for interior ceilingand wall panels (other than lighting lenses),partitions, and the outer surfaces of galleys,large cabinets and stowage compartments(other than underseat stowage compartmentsand compartments for stowing small items,such as magazines and maps), an operatorshall not operate a large aeroplane, having aMAPSC of more than 19, Manufactured on orafter 20 August 1990, that does not complywith the heat release and smoke densityrequirements of Appendix F Parts IV & V.

(3) The Authority may authoriseexemption from the requirements of (c)(1)and (c)(2) of this paragraph for specificcomponents of the cabin interior which didnot meet applicable flammability and smokeemission requirements if the determinationwas made at the date of manufacture by theauthority of the country of manufacture andaccepted by the authority of the country ofimport, that special technical circumstances,existed that then made complianceimpractical. Such exemptions shall be limitedto those aeroplanes manufactured within1 year after the applicable date specified inthis paragraph and those airplanes in which aninterior was replaced within 1 year of thatdate.

(d) An operator shall not operate a largeaeroplane having a MAPSC of more than 19,Type Certificated after 1 January 1958 that, uponthe first substantially complete replacement of thecabin interior components, (i.e. interior ceilingand wall panels (other than lighting lenses),partitions, and the outer surfaces of galleys, largecabinets and stowage compartments (other thanunderseat stowage compartments andcompartments for stowing small items, such asmagazines and maps)), does not comply with theheat release and smoke density requirements ofAppendix F Parts IV & V.

(e) With respect to ashtrays and placards, ifsmoking is to be prohibited there must be aplacard so stating, and if smoking is to beallowed, an operator shall not operate a largeaeroplane after 1 April 2002, that does notcomply with the following –

(1) There must be an adequate numberof self-contained, removable ashtrays; and

(2) Where the crew compartment isseparated from the passenger compartment,there must be at least one sign (using eitherletters or symbols) notifying when smoking is

prohibited. It must, when illuminated, belegible to each person seated in the passengercabin under all probable conditions of cabinillumination, notifying all passengers whensmoking is prohibited. Signs which notifywhen smoking is prohibited must be installedso as to be operable from either pilot’s seat.

(f) With respect to disposal receptacles, anoperator shall not operate a large aeroplane after1 April 2002, that does not comply with thefollowing –

(1) Each disposal receptacle fortowels, paper or waste must be fully enclosedand constructed of materials adequate inresistance to fire such that any fire likely tooccur in it under normal use will becontained. The ability of the disposalreceptacle to contain those fires under allprobable conditions of wear, misalignment,and ventilation expected in service must havebeen demonstrated by test. A placardcontaining the legible words or symbologyindicating ‘No Cigarette Disposal’ must belocated on or near each disposal receptacledoor.

JAR 26.155 Flammability of cargocompartment liners(See IEM 26.155)

(Text derived from: JAR 25.855 & Appx F PartIII, at Chg. 13 plus Amdt 93/1, dated 8 March 1993)

(a) An operator shall not operate a largeaeroplane, Type Certificated after 1 January1958, with Class C or D compartment, asdefined in JAR 25.857 Amdt 93/1, 08/03/93,greater than 5.66 m3 (200 cubic feet) that haveceiling and sidewall liner panels which are notconstructed of : –

(1) Glass fibre reinforced resin, or

(2) Materials which meet the flamepenetration test requirements of Appendix FPart III, or other approved equivalentmethods, or

(3) Aluminium (only in the case ofaluminium liner installations approved priorto 1 July 1989).

(b) For compliance with this section, theterm ‘liner’ includes any design features, such asa joint or fastener which would affect thecapability of the liner to safely contain a fire.

JAR 26.150(c) (continued) JAR 26.150(e)(2) (continued)

JAR–26 SECTION 1

Amendment 1 1–B–4 01.05.03

JAR 26.160 Lavatory fire protection

(Text derived from: JAR 25.854, at Chg. 13 plusAmdt 93/1, dated 8 March 1993)

An operator shall not operate a largeaeroplane with an MAPSC of more than 19 after1 October 2000 that does not comply with thefollowing –

(a) Each lavatory must be equipped with asmoke detector system or equivalent thatprovides a warning light in the cockpit, orprovides a warning light or audible warning inthe passenger cabin that would be readilydetected by a cabin crew member; and

(b) Each lavatory must be equipped with abuilt-in fire extinguisher for each disposalreceptacle for towels, paper, or waste, locatedwithin the lavatory. The extinguisher must bedesigned to discharge automatically into eachdisposal receptacle upon occurrence of a fire inthat receptacle.

SYSTEMS AND EQUIPMENT

JAR 26.200 Landing gear aural warning

(Text derived from: FAR Part 121.289,Amendment 121-227)

An operator shall not operate a largeaeroplane that does not comply with thefollowing –

(a) Except for aeroplanes that comply withthe requirements of JAR 25.729, effective atAmdt 93/1, dated 08/03/93, or later, each largeaeroplane must have a landing gear auralwarning device that functions continuouslyunder the following conditions:

(1) For aeroplanes with an establishedapproach flap position, whenever the flaps areextended beyond the maximum certificatedapproach climb configuration position in theAeroplane Flight Manual and the landing gearis not fully extended and locked.

(2) For aeroplanes without anestablished approach climb flap position,whenever the flaps are extended beyond theposition at which landing gear extension isnormally performed and the landing gear isnot fully extended and locked.

(b) The warning system required by sub-paragraph (a) of this paragraph –

(1) May not have a manual shut-offmeans readily available to the flight crewsuch that it could be operated instinctively,inadvertently or by habitual reflexive action;

(2) Must be in addition to the throttle-actuated device installed under theairworthiness type certification requirements;and

(3) May utilise any part of thethrottle-actuated system including the auralwarning device.

(c) The flap position sensing unit may beinstalled at any suitable place in the aeroplane.

[ JAR 26.260Security Considerations(See ACJ 26.260)

The applicability, as defined here-after,may be affected by and be changed inaccordance with national security programmesaddressing onboard security.

From 1 November 2003, all passengercarrying aeroplanes of a maximum certificatedtake-off mass in excess of 45 500 kg or with apassenger seating capacity greater than 60, andhaving a lockable door installed between thepilot compartment and the passengercompartment, shall meet the followingrequirements :

(a) Protection of flight deck. If a flight deckdoor is required by operating rules, the doorinstallation must be designed to:

(1) Resist forcible intrusion byunauthorized persons and be capable ofwithstanding impacts of 300 Joules (221.3foot-pounds) at the critical locations on thedoor, as well as a 1 113 Newton (250 pound)constant tensile load on the knob or handle(See ACJ 26.260(a)(1)), and

(2) Resist penetration by small armsfire and fragmentation devices by meeting thefollowing projectile definitions and projectilespeeds (See ACJ 26.260(a)(2).

(i) Demonstration Projectile #1.A 9 mm full metal jacket, round nose(FMJ RN) bullet with nominal mass of8·0 g (124 grain) and reference velocity436 m/s (1 430 ft/s)

(ii) Demonstration Projectile #2.A .44 Magnum, jacketed hollow point(JHP) bullet with nominal mass of15·6 g (240 grain) and referencevelocity 436 m/s (1 430 ft/s)]

[Amdt. 1, 01.05.03]

JAR 26.200(b) (continued)

SECTION 1 JAR–26

1–B–5 13.07.98

(a) Material test criteria

(1) Interior compartments occupiedby crew or passengers.

(i) Interior ceiling panels,interior wall panels, partitions, galleystructure, large cabinet walls, structuralflooring, and materials used in theconstruction of stowage compartments(other than underseat stowagecompartments and compartments forstowing small items such as magazinesand maps) must be self-extinguishingwhen tested vertically in accordancewith the applicable portions of Part I ofthis Appendix. The average burn lengthmay not exceed 152.40 mm (6 inches)and the average flame time afterremoval of the flame source may notexceed 15 seconds. Drippings from thetest specimen may not continue to flamefor more than an average of 3 secondsafter falling.

(ii) Floor covering, textiles(including draperies and upholstery),seat cushions, padding, decorative andnon-decorative coated fabrics, leather,trays and galley furnishings, electricalconduit, thermal and acousticalinsulation and insulation covering, airducting, joint and edge covering, linersof Class B and E cargo or baggagecompartments, floor panels of Class B,C, D, or E cargo or baggagecompartments, insulation blankets,cargo covers and transparencies,moulded and thermoformed parts, airducting joints, and trim strips(decorative and chafing), that areconstructed of materials not covered insub-paragraph (iv) below, must be self-extinguishing when tested vertically inaccordance with the applicable portionsof Part I of this Appendix or otherapproved equivalent means. Theaverage burn length may not exceed203·2 mm (8 inches), and the averageflame time after removal of the flamesource may not exceed 15 seconds.Drippings from the test specimen maynot continue to flame for more than anaverage of 5 seconds after falling.

(iii) Motion picture film must besafety film meeting the StandardSpecifications for Safety PhotographicFilm PHI.25 (available from theAmerican National Standards Institute,1430 Broadway, New York, NY 10018).If the film travels through ducts, theducts must meet the requirements ofsub-paragraph (ii) of this paragraph.

(iv) Clear plastic windows andsigns, parts constructed in whole or inpart of elastomeric materials, edgelighted instrument assemblies consistingof two or more instruments in a commonhousing, seat belts, shoulder harnesses,and cargo and baggage tiedownequipment, including containers, bins,pallets, etc, used in passenger or crewcompartments, may not have an averageburn rate greater than 63·5 mm(2·5 inches) per minute when testedhorizontally in accordance with theapplicable portions of this Appendix.

(v) Except for small parts (suchas knobs, handles, rollers, fasteners,clips, grommets, rub strips, pulleys, andsmall electrical parts) that would notcontribute significantly to thepropagation of a fire and for electricalwire and cable insulation, materials initems not specified in paragraphs(a)(1)(i),(ii),(iii), or (iv) of Part I of thisAppendix may not have a burn rategreater than 101.6 mm (4 inches) perminute when tested horizontally inaccordance with the applicable portionsof this Appendix.

(2) Cargo and baggage compartmentsnot occupied by crew or passengers.

(i) Thermal and acousticinsulation (including coverings) used ineach cargo and baggage compartmentmust be constructed of materials that meetthe requirements set forth in sub-paragraph(a)(1)(ii) of Part I of this Appendix.

(ii) A cargo or baggagecompartment defined in JAR 25.857 asClass B or E must have a linerconstructed of materials that meet therequirements of sub-paragraph (a)(1)(ii)of Part I of this Appendix and separated

Appendix FPart l — Test Criteria and Procedures for Showing Compliance with JAR 25.853, or 25.855.

Text derived from JAR–25 Appx F, Part I at Chg 14, plus Amendment 93/1, dated 08/03/93

JAR–26 SECTION 1

13.07.98 1–B–6

from the aeroplane structure (except forattachments). In addition, such linersmust be subjected to the 45 degreeangle test as specificed in sub-paragraph(b) (6) of Part I of this Appendix. Theflame may not penetrate (pass through)the material during application of theflame or subsequent to its removal. Theaverage flame time after removal of theflame source may not exceed15 seconds, and the average glow timemay not exceed 10 seconds.

(iii) A cargo or baggagecompartment defined in JAR 25.857 asClass B, C, D, or E must have floorpanels constructed of materials whichmeet the requirements of sub-paragraph(a)(1)(ii) of Part I of this Appendix andwhich are separated from the aeroplanestructure (except for attachments). Suchpanels must be subjected to the 45degree angle test as specified in sub-paragraph (b) (6) of Part I of thisAppendix. The flame may not penetrate(pass through) the material duringapplication of the flame or subsequentto its removal. The average flame timeafter removal of the flame source maynot exceed 15 seconds, and the averageglow time may not exceed 10 seconds.

(iv) Insulation blankets andcovers used to protect cargo must beconstructed of materials that meet therequirements of sub-paragraph (a)(1)(ii)of Part I of this Appendix. Tiedownequipment (including containers, bins,and pallets) used in each cargo andbaggage compartment must beconstructed of materials that meet therequirements of sub-paragraph (a)(1)(v)of Part I of this Appendix.

(3) Electrical system components.Insulation on electrical wire or cable installedin any area of the fuselage must be self-extinguishing when subjected to the 60 degreetest as specified in sub-paragraph (b) (7) ofPart I of this Appendix. The average burnlength may not exceed 76·2 mm (3 inches)and the average flame time after removal ofthe flame source may not exceed 30 seconds.Drippings from the test specimen may notcontinue to flame for more than an average of3 seconds after falling.

(b) Test Procedures –

(1) Conditioning. Specimens must beconditioned to 70 ± 5°F (21·11 ± 3°C), and at50% ± 5% relative humidity until moistureequilibrium is reached or for 24 hours. Eachspecimen must remain in the conditioningenvironment until it is subjected to the flame.

(2) Specimen configuration. Exceptfor small parts and electrical wire and cableinsulation, materials must be tested either as asection cut from a fabricated part as installedin the aeroplane or as a specimen simulating acut section, such as a specimen cut from a flatsheet of the material or a model of thefabricated part. The specimen may be cutfrom any location in a fabricated part;however, fabricated units, such as sandwichpanels, may not be separated for test. Exceptas noted below, the specimen thickness mustbe no thicker than the minimum thickness tobe qualified for use in the aeroplane. Testspecimens of thick foam parts, such as seatcushions, must be 12·7 mm (½-inch) inthickness. Test specimens of materials thatmust meet the requirements of sub-paragraph(a)(1)(v) of Part I of this Appendix must beno more than 3·175 mm (1/8-inch) inthickness. Electrical wire and cable specimensmust be the same size as used in theaeroplane. In the case of fabrics, both thewarp and fill direction of the weave must betested to determine the most criticalflammability condition. Specimens must bemounted in a metal frame so that the two longedges and the upper edge are held securelyduring the vertical test prescribed in sub-paragraph (4) of this paragraph and the twolong edges and the edge away from the flameare held securely during the horizontal testprescribed in sub-paragraph (5) of thisparagraph. The exposed area of the specimenmust be at least 50·8 mm (2 inches) wide and304·8 mm (12 inches) long, unless the actualsize used in the aeroplane is smaller. Theedge to which the burner flame is appliedmust not consist of the finished or protectededge of the specimen but must berepresentative of the actual cross-section ofthe material or part as installed in theaeroplane. The specimen must be mounted ina metal frame so that all four edges are heldsecurely and the exposed area of the specimenis at least 203·2 mm by 203·2 mm (8 inchesby 8 inches) during the 45° test prescribed insub-paragraph (6) of this paragraph.

Appendix F (Part I) (continued)

SECTION 1 JAR–26

1–B–7 13.07.98

(3) Apparatus. Except as provided insub-paragraph (7) of this paragraph, testsmust be conducted in a draught-free cabinetin accordance with Federal Test MethodStandard 191 Model 5903 (revised Method5902) for the vertical test, or Method 5906for horizontal test (available from the GeneralServices Administration, Business ServiceCentre, Region 3, Seventh & D Streets SW.,Washington, DC 20407, USA). Specimenswhich are too large for the cabinet must betested in similar draught-free conditions.

(4) Vertical test. A minimum of threespecimens must be tested and resultsaveraged. For fabrics, the direction of weavecorresponding to the most criticalflammability conditions must be parallel tothe longest dimension. Each specimen mustbe supported vertically. The specimen mustbe exposed to a Bunsen or Tirril burner with anominal 9·525 mm (3/8-inch) I.D. tubeadjusted to give a flame of 38·1 mm(1½ inches) in height. The minimum flametemperature measured by a calibratedthermocouple pyrometer in the centre of theflame must be 843·33 °C (1550 °F). Thelower edge of the specimen must be19·05 mm (¾-inch) above the top edge of theburner. The flame must be applied to thecentre line of the lower edge of the specimen.For materials covered by sub-paragraph(a)(1)(i) of Part I of this Appendix, the flamemust be applied for 60 seconds and thenremoved. For materials covered by sub-paragraph (a)(1)(ii) of Part I of thisAppendix, the flame must be applied for12 seconds and then removed. Flame time,burn length, and flaming time of drippings, ifany, may be recorded. The burn lengthdetermined in accordance with sub-paragraph(7) of this paragraph must be measured to thenearest 2·54 mm (tenth of an inch).

(5) Horizontal test. A minimum ofthree specimens must be tested and the resultsaveraged. Each specimen must be supportedhorizontally. The exposed surface, wheninstalled in the aircraft, must be face down forthe test. The specimen must be exposed to aBunsen or Tirrill burner with a nominal9·525 mm (3/8-inch) I.D. tube adjusted to givea flame of 38·1 mm (1½ inches) in height.The minimum flame temperature measured bya calibrated thermocouple pyrometer in thecentre of the flame must be 843·33°C(1550°F). The specimen must be positioned

so that the edge being tested is centred19·05 mm (¾-inch) above the top of theburner. The flame must be applied for15 seconds and then removed. A minimum of254 mm (10 inches) of specimen must be usedfor timing purposes, approximately 38·1 mm(1½ inches) must burn before the burningfront reaches the timing zone, and the averageburn rate must be recorded.

(6) Forty-five degree test. A minimumof three specimens must be tested and theresults averaged. The specimens must besupported at an angle of 45° to a horizontalsurface. The exposed surface when installedin the aircraft must be face down for the test.The specimens must be exposed to a Bunsenor Tirrill burner with a nominal 9·525 mm(3/8-inch) I.D. tube adjusted to give a flame of38·1 mm (1½ inches) in height. The minimumflame temperature measured by a calibratedthermocouple pyrometer in the centre of theflame must be 843·33°C (1550°F). Suitableprecautions must be taken to avoid draughts.The flame must be applied for 30 secondswith one-third contacting the material at thecentre of the specimen and then removed.Flame time, glow time, and whether the flamepenetrates (passes through) the specimen mustbe recorded.

(7) Sixty degree test. A minimum ofthree specimens of each wire specification(make and size) must be tested. The specimenof wire or cable (including insulation) mustbe placed at an angle of 60° with thehorizontal in the cabinet specified in sub-paragraph (3) of this paragraph with thecabinet door open during the test, or must beplaced within a chamber approximately609·6 mm (2 feet) high by 304·8 mm by304·8 mm (1 foot by 1 foot), open at the topand at one vertical side (front), and whichallows sufficient flow of air for completecombustion, but which is free from draughts.The specimen must be parallel to andapproximately 152·4 mm (6 inches) from thefront of the chamber. The lower end of thespecimen must be held rigidly clamped. Theupper end of the specimen must pass over apulley or rod and must have an appropriateweight attached to it so that the specimen isheld tautly throughout the flammability test.The test specimen span between lower clampand upper pulley or rod must be 609·6 mm(24 inches) and must be marked 203·2 mm(8 inches) from the lower end to indicate the

Appendix F (Part I) (continued)Appendix F (Part I) (continued)

JAR–26 SECTION 1

13.07.98 1–B–8

central point for flame application. A flamefrom a Bunsen or Tirrill burner must beapplied for 30 seconds at the test mark. Theburner must be mounted underneath the testmark on the specimen, perpendicular to thespecimen and at an angle of 30° to thevertical plane of the specimen. The burnermust have a nominal bore of 9·525 mm(3/8-inch) and be adjusted to provide a76·2 mm (3-inch) high flame with an innercone approximately one-third of the flameheight. The minimum temperature of thehottest portion of the flame, as measured witha calibrated thermocouple pyrometer, may notbe less than 954·44°C (1750°F). The burnermust be positioned so that the hottest portionof the flame is applied to the test mark on thewire. Flame time, burn length, and flamingtime of drippings, if any, must be recorded.The burn length determined in accordancewith sub-paragraph (8) of this paragraph mustbe measured to the nearest 2·54 mm (tenth ofan inch). Breaking of the wire specimens isnot considered a failure.

(8) Burn length. Burn length is thedistance from the original edge to the farthestevidence of damage to the test specimen dueto flame impingement, including areas ofpartial or complete consumption, charring, orembrittlement, but not including areas sooted,stained, warped, or discoloured, nor areaswhere material has shrunk or melted awayfrom the heat source.

INTENTIONALLY LEFT BLANK

Appendix F (Part I) (continued)

SECTION 1 JAR–26

1–B–9 13.07.98

(a) Criteria for Acceptance. Each seatcushion must meet the following criteria:

(1) At least three sets of seat bottomand seat back cushion specimens must betested.

(2) If the cushion is constructed witha fire blocking material, the fire blockingmaterial must completely enclose the cushionfoam core material.

(3) Each specimen tested must befabricated using the principal components(i.e. foam core, flotation material, fireblocking material, if used, and dresscovering) and assembly processes(representative seams and closures) intendedfor use in the production articles. If adifferent material combination is used for theback cushion than for the bottom cushion,both material combinations must be tested ascomplete specimen sets, each set consisting ofa back cushion specimen and a bottomcushion specimen. If a cushion, includingouter dress covering, is demonstrated to meetthe requirements of this Appendix using theoil burner test, the dress covering of thatcushion may be replaced with a similar dresscovering provided the burn length of thereplacement covering, as determined by thetest specified in JAR 25.853(b), does notexceed the corresponding burn length of thedress covering used on the cushion subjectedto the oil burner test.

(4) For at least two-thirds of the totalnumber of specimen sets tested, the burnlength from the burner must not reach the sideof the cushion opposite the burner. The burnlength must not exceed 431.8 mm (17 inches).Burn length is the perpendicular distancefrom the inside edge of the seat frame closestto the burner to the farthest evidence ofdamage to the test specimen due to flameimpingement, including areas of partial orcomplete consumption, charring, orembrittlement, but not including areas sooted,stained, warped, or discoloured, or areaswhere material has shrunk or melted awayfrom the heat source.

(5) The average percentage weightloss must not exceed 10 percent. Also, at leasttwo-thirds of the total number of specimensets tested must not exceed 10 percent weight

loss. All droppings falling from the cushionsand mounting stand are to be discarded beforethe after-test weight is determined. Thepercentage weight loss for a specimen set isthe weight of the specimen set before testingless the weight of the specimen set aftertesting expressed as the percentage of theweight before testing.

(b) Test Conditions. Vertical air velocityshould average 0.127 m/s ± 0.05 m/s (25 fpm± 10 fpm) at the top of the back seat cushion.Horizontal air velocity should be below 0.05 m/s(10 fpm) just above the bottom seat cushion. Airvelocities should be measured with theventilation hood operating and the burner motoroff.

(c) Test Specimens

(1) For each test, one set of cushionspecimens representing a seat bottom and seatback cushion must be used.

(2) The seat bottom cushion specimenmust be 457 ± 3 mm (18 ± 0·125 inches) wideby 508 ± 3 mm (20 ± 0·125 inches) deep by102 ± 3 mm (4 ± 0·125 inches) thick,exclusive of fabric closures and seam overlap.

(3) The seat back cushion specimenmust be 432 ± 3 mm (18 ± 0·125 inches) wideby 635 ± 3 mm (25 ± 0·125 inches) high by51 ± 3 mm (2 ± 0·125 inches) thick, exclusiveof fabric closures and seam overlap.

(4) The specimens must beconditioned at 21 ± 2ºC (70 ± 5ºF) 55%± 10% relative humidity for at least 24 hoursbefore testing.

(d) Test Apparatus. The arrangement of thetest apparatus is shown in Figure 1 through 5and must include the components described inthis paragraph. Minor details of the apparatusmay vary, depending on the model burner used.

(1) Specimen Mounting Stand. Themounting stand for the test specimens consistof steel angles, as shown in Figure 1. Thelength of the mounting stand legs is 305 ±3 mm (12 ± 0·125 inches). The mountingstand must be used for mounting the testspecimen seat bottom and seat back, as shownin Figure 2. The mounting stand should alsoinclude a suitable drip pan lined withaluminium foil, dull side up.

Appendix F (continued)Part II — Flammability of Seat Cushions

Text derived from: JAR–25 Appendix F, Part II at Chg 12, plus Amendment 86/1, 16/6/86, and reissued byChg 13 15/10/89

JAR–26 SECTION 1

13.07.98 1–B–10

(2) Test Burner. The burner to beused in testing must –

(i) Be a modified gun type;

(ii) Have an 80-degree sprayangle nozzle nominally rated for2·25 US gallons/hour at 100 psi;

(iii) Have a 305 mm (12-inch)burner cone installed at the end of thedraft tube, with an opening 152 mm(6 inches) high and 208 mm (11 inches)wide, as shown in Figure 3; and

(iv) Have a burner fuel pressureregulator that is adjusted to deliver anominal 2·0 US gallon/hour of # 2Grade kerosene or equivalent requiredfor the test.

(3) Calorimeter

(i) The calorimeter to be usedin testing must be a 0–17·0 Watts/cm2

(0–15·0 BTU per ft2 sec) calorimeter,accurate ± 3%, mounted in a 152 by305 mm (6 inch by 12 inch) by 19 mm(0·75 inch) thick calcium silicateinsulating board which is attached to asteel angle bracket for placement in thetest stand during burner calibration, asshown in Figure 4.

(ii) Because crumbling of theinsulating board with service can resultin misalignment of the calorimeter, thecalorimeter must be monitored and themounting shimmed, as necessary, toensure that the calorimeter face is flushwith the exposed plane of the insulatingboard in a plane parallel to the exit ofthe test burner cone.

(4) Thermocouples. The seventhermo-couples to be used for testing must be0·0625 to 0·125 inch metal sheathed, ceramicpacked, type K, grounded thermocouples witha nominal 22 to 30 American wire gauge(AWG)-size conductor (0·643 mm (0·0253inches) to 0·254 mm (0·010 inches) diameter).The seven thermocouples must be attached toa steel angle bracket to form a thermocouplerake for placement in the test stand duringburner calibration as shown in Figure 5.

(5) Apparatus Arrangement. The testburner must be mounted on a suitable stand toposition the exit of the burner cone a distanceof 102 ± 3 mm (4 ± 0·125 inches) from oneside of the specimen mounting stand. The

burner stand should have the capability ofallowing the burner to be swung from thespecimen mounting stand during warmupperiods.

(6) Data Recording. A recordingpotentiometer or other suitable calibratedinstrument with an appropriate range must beused to measure and record the outputs of thecalorimeter and the thermocouples.

(7) Weight Scale. Weighing Device –A device must be used that with properprocedures may determine the before andafter test weights of each set of seat cushionspecimens within 9 grams (0·02 pound). Acontinuous weighing system is preferred.

(8) Timing Device. A stopwatch orother device (calibrated to ± 1 second) mustbe used to measure the time of application ofthe burner flame and self-extinguishing timeor test duration.

(e) Preparation of Apparatus. Beforecalibration, all equipment must be turned on andthe burner fuel must be adjusted as specified insub-paragraph (d)(2).

(f) Calibration. To ensure the properthermal output of the burner, the following testmust be made:

(1) Place the calorimeter on the teststand as shown in Figure 4 at a distance of102 ± 3 mm (4 ± 0·125 inches) from the exitof the burner cone.

(2) Turn on the burner, allow it to runfor 2 minutes for warmup, and adjust theburner air intake damper to produce a readingof 11·9 ± 0·6 Watts/cm2 (10·5 ± 0·5 BTU perft2 sec) on the calorimeter to ensure steadystate conditions have been achieved. Turn offthe burner.

(3) Replace the calorimeter with thethermocouple rake (Figure 5).

(4) Turn on the burner and ensure thatthe thermocouples are reading 1038 ± 38ºC(1900 ± 100ºF) to ensure steady stateconditions have been achieved.

(5) If the calorimeter andthermocouples do not read within range,repeat steps in sub-paragraphs 1 to 4 andadjust the burner air intake damper until theproper readings are obtained. Thethermocouple rake and the calorimeter shouldbe used frequently to maintain and record

Appendix F (Part II) (continued)

SECTION 1 JAR–26

1–B–11 13.07.98

calibrated test parameters. Until the specificapparatus has demonstrated consistency, eachtest should be calibrated. After consistencyhas been confirmed, several tests may beconducted with the pre-test calibration beforeand a calibration check after the series.

(g) Test Procedures. The flammability ofeach set of specimens must be tested as follows:

(1) Record the weight of each set ofseat bottom and seat back cushion specimensto be tested to the nearest 9 grams(0·02 pound).

(2) Mount the seat bottom and seatback cushion test specimens on the test standas shown in Figure 2, securing the seat backcushion specimen to the test stand at the top.

(3) Swing the burner into position andensure that the distance from the exit of theburner cone to the side of the seat bottomcushion specimen is 102 ± 3 mm (4 ± 0·125inches).

(4) Swing the burner away from thetest position. Turn on the burner and allow itto run for 2 minutes to provide adequatewarmup of the burner cone and flamestabilization.

(5) To begin the test, swing the burnerinto the test position and simultaneously startthe timing device.

(6) Expose the seat bottom cushionspecimen to the burner for 2 minutes and thenturn off the burner. Immediately swing theburner away from the test position. Terminatetest 7 minutes after initiating cushionexposure to the flame by use of a gaseousextinguishing agent (i.e. Halon or CO2).

(7) Determine the weight of theremains of the seat cushion specimen set left

on the mounting stand to the nearest 9 grams(0·02 pound) excluding all droppings.

(h) Test Report. With respect to allspecimen sets tested for a particular seat cushionfor which testing of compliance is performed,the following information must be recorded:

(1) An identification and descriptionof the specimens being tested.

(2) The number of specimen setstested.

(3) The initial weight and residualweight of each set, the calculated percentageweight loss of each set, and the calculatedaverage percentage weight loss for the totalnumber of sets tested.

(4) The burn length for each settested.

INTENTIONALLY LEFT BLANK

Appendix F (Part II) (continued)

JAR–26 SECTION 1

13.07.98 1–B–12

FIGURE 1

Appendix F (Part II) (continued)

SECTION 1 JAR–26

1–B–13 13.07.98

FIGURE 2

Appendix F (Part II) (continued)

JAR–26 SECTION 1

13.07.98 1–B–14

FIGURE 3

Appendix F (Part II) (continued)

SECTION 1 JAR–26

1–B–15 13.07.98

FIGURE 4

Appendix F (Part II) (continued)

JAR–26 SECTION 1

13.07.98 1–B–16

FIGURE 5

Appendix F (Part II) (continued)

SECTION 1 JAR–26

1–B–17 13.07.98

(a) Criteria for Acceptance

(1) At least three specimens of cargocompartment sidewall or ceiling liner panelsmust be tested.

(2) Each specimen tested mustsimulate the cargo compartment sidewall orceiling liner panel, including any designfeatures, such as joints, lamp assemblies, etc.,the failure of which would affect thecapability of the liner to safely contain a fire.

(3) There must be no flamepenetration of any specimen within 5 minutesafter application of the flame source, and thepeak temperature measured at 4 inches abovethe upper surface of the horizontal test samplemust not exceed 222.22ºC (400ºF).

(b) Summary of Method. This methodprovides a laboratory test procedure formeasuring the capability of cargo compartmentlining materials to resist flame penetrationwithin a 2 US gallons/hour # 2 Grade keroseneor equivalent burner fire source. Ceiling andsidewall liner panels may be tested individuallyprovided a baffle is used to simulate the missingpanel. Any specimen that passes the test as aceiling liner panel may be used as a sidewallliner panel.

(c) Test Specimens

(1) The specimen to be tested mustmeasure 406 ± 3 mm (16 ± 0·125 inches) by610 ± 3 mm (24 ± 0·125 inches).

(2) The specimens must beconditioned at 21ºC ± 2ºC (70ºF ± 5ºF) and55% ± 5% humidity for at least 24 hoursbefore testing.

(d) Test Apparatus. The arrangement of thetest apparatus, which is shown in Figure 3 ofPart II and Figures 1 through 3 of this Part ofAppendix F, must include the componentsdescribed in this paragraph. Minor details of theapparatus may vary, depending on the model ofthe burner used.

(1) Specimen Mounting Stand. Themounting stand for the test specimens consistsof steel angles as shown in Figure 1.

(2) Test Burner. The burner to beused in testing must –

(i) Be a modified gun type.

(ii) Use a suitable nozzle andmaintain fuel pressure to yield a 2 USgallons/hour fuel flow. For example: an80 degree nozzle nominally rated at2·25 US gallons/hour and operated at85 pounds per square inch (PSI) gaugeto deliver 2·03 US gallons/hour.

(iii) Have a 305 mm (12 inch)burner extension installed at the end ofthe draft tube with an opening 152 mm(6 inches) high and 280 mm (11 inches)wide as shown in Figure 3 of Part II ofthis Appendix.

(iv) Have a burner fuel pressureregulator that is adjusted to deliver anominal 2·0 US gallons/hour of # 2Grade kerosene or equivalent.

(3) Calorimeter

(i) The calorimeter to be usedin testing must be a total heat flux FoilType Gardon Gauge of an appropriaterange, approximately 0–17·0 Watts/cm2

(0 to 15·0 BTU per ft2 sec). Thecalorimeter must be mounted in a 152by 305 mm (6 inch by 12 inch) by19 mm (0·75 inch) thick insulatingblock which is attached to a steel anglebracket for placement in the test standduring burner calibration as shown inFigure 2 of this Part of this Appendix.

(ii) The insulating block must bemonitored for deterioration and themounting shimmed as necessary toensure that the calorimeter face isparallel to the exit plane of the testburner cone.

(4) Thermocouples. The seventhermocouples to be used for testing must be0·0625 of an inch ceramic sheathed, type K,grounded thermocouples with a nominal30 American wire gauge (AWG)-sizeconductor (0·254 mm (0·010 inches)diameter). The seven thermocouples must beattached to a steel angle bracket to form athermocouple rake for placement in the standduring burner calibration as shown in Figure3 of this Part of this Appendix.

(5) Apparatus Arrangement. The testburner must be mounted on a suitable stand toposition the exit of the burner cone a distanceof 203.2 mm (8 inches) from the ceiling liner

Appendix F (continued)Part III – Test Method to Determine Flame Penetration Resistance of Cargo Compartment Liners

Text derived from: JAR–25 Appendix F, Part III at Chg 12, plus Amdt 86/2 5/10.86, and reissued by Chg 13

JAR–26 SECTION 1

13.07.98 1–B–18

panel and 50.8 mm (2 inches) from thesidewall liner panel. The burner stand shouldhave the capability of allowing the burner tobe swung away from the test specimen duringwarm-up periods.

(6) Instrumentation. A recordingpotentiometer or other suitable instrumentwith an appropriate range must be used tomeasure and record the outputs of thecalorimeter and the thermocouples.

(7) Timing Device. A stopwatch orother device must be used to measure the timeof flame application and the time of flamepenetration, if it occurs.

(e) Preparation of Apparatus. Beforecalibration, all equipment must be turned on andallowed to stabilize, and the burner fuel flowmust be adjusted as specified in sub-paragraph(d)(2).

(f) Calibration. To ensure the properthermal output of the burner the following testmust be made:

(1) Remove the burner extension fromthe end of the draft tube. Turn on the blowerportion of the burner without turning the fuelor igniters on. Measure the air velocity usinga hot wire anemometer in the centre of thedraft tube across the face of the opening.Adjust the damper such that the air velocity isin the range of 7.97 to 9.14 m/s (1550 to1800 fpm). If tabs are being used at the exitof the draft tube, they must be removed priorto this measurement. Reinstall the draft tubeextension cone.

(2) Place the calorimeter on the teststand as shown in Figure 2 at a distance of203 mm (8 inches) from the exit of the burnercone to simulate the position of the horizontaltest specimen.

(3) Turn on the burner, allow it to runfor 2 minutes for warm-up, and adjust thedamper to produce a calorimeter reading of9·1 ± 0·6 Watts/cm2 (8·0 ± 0·5 BTU per ft2

sec).

(4) Replace the calorimeter with thethermocouple rake (see Figure 3).

(5) Turn on the burner and ensure thateach of the seven thermocouples reads 927ºC± 38ºC (1700ºF ± 100ºF) to ensure steadystate conditions have been achieved. If thetemperature is out of this range, repeat steps 2through 5 until proper readings are obtained.

(6) Turn off the burner and removethe thermocouple rake.

(7) Repeat (f)(1) to ensure that theburner is in the correct range.

(g) Test Procedure

(1) Mount a thermocouple of the sametype as that used for calibration at a distanceof 101 mm (4 inches) above the horizontal(ceiling) test specimen. The thermocoupleshould be centred over the burner cone.

(2) Mount the test specimen on thetest stand shown in Figure 1 in either thehorizontal or vertical position. Mount theinsulating material in the other position.

(3) Position the burner so that flameswill not impinge on the specimen, turn theburner on, and allow it to run for 2 minutes.Rotate the burner to apply the flame to thespecimen and simultaneously start the timingdevice.

(4) Expose the test specimen to theflame for 5 minutes and then turn off theburner. The test may be terminated earlier ifflame penetration is observed.

(5) When testing ceiling liner panels,record the peak temperature measured101.6 mm (4 inches) above the sample.

(6) Record the time at which flamepenetration occurs if applicable.

(h) Test Report. The test report mustinclude the following:

(1) A complete description of thematerials tested including type, manufacturer,thickness, and other appropriate data.

(2) Observations of the behaviour ofthe test specimens during flame exposure suchas delamination, resin ignition, smoke, etc.,including the time of such occurrence.

(3) The time at which flamepenetration occurs, if applicable, for each ofthree specimens tested.

(4) Panel orientation (ceiling orsidewall).

Appendix F (Part III) (continued)

SECTION 1 JAR–26

1–B–19 13.07.98

FIGURE 1 – TEST APPARATUS FOR HORIZONTAL AND VERTICAL MOUNTING

Appendix F (Part III) (continued)Appendix F (Part III) (continued)Appendix F (Part III) (continued)

JAR–26 SECTION 1

13.07.98 1–B–20

FIGURE 2 – CALORIMETER BRACKET

Appendix F (Part III) (continued)

SECTION 1 JAR–26

1–B–21 13.07.98

FIGURE 3 – THERMOCOUPLE RAKE BRACKET

JAR–26 SECTION 1

13.07.98 1–B–22

(a) Summary of Method

(1) The specimen to be tested isinjected into an environmental chamberthrough which a constant flow of air passes.The specimen’s exposure is determined by aradiant heat source adjusted to produce thedesired total heat flux on the specimen of3·5 Watts/cm2, using a calibrated calorimeter.The specimen is tested so that the exposedsurface is vertical. Combustion is initiated bypiloted ignition. The combustion productsleaving the chamber are monitored in order tocalculate the release rate of heat.

(b) Apparatus. The Ohio State University(OSU) rate of heat release apparatus asdescribed below, is used. This is a modifiedversion of the rate of heat release apparatusstandardised by the American Society of Testingand Materials (ASTM), ASTM E-906.

(1) This apparatus is shown inFigure 1. All exterior surfaces of theapparatus, except the holding chamber, shallbe insulated with 25 mm (1 inch) thick, lowdensity, high-temperature, fibreglass boardinsulation. A gasketed door through which thesample injection rod slides forms an airtightclosure on the specimen hold chamber.

(2) Thermopile. The temperaturedifference between the air entering theenvironmental chamber and that leaving ismonitored by a thermopile having five hotand five cold, 24 gauge Chromel-Alumeljunctions. The hot junctions are spaced acrossthe top of the exhaust stack 10 mm(0.39 inch) below the top of the chimney. Onethermocouple is located in the geometriccentre, with the other four located 30 mm(1.17 inch) from the centre along the diagonaltoward each of the corners (Figure 5). Thecold junctions are located in the pan belowthe lower air distribution plate (see sub-paragraph (b)(4)). Thermopile hot junctionsmust be cleared of soot deposits as needed tomaintain the calibrated sensitivity.

(3) Radiation Source. A radiant heatsource for generating a flux up to 100 kW/m2,using four silicon carbide elements, Type LL,50·8 cm (20 inches) long by 15·8 mm(0·625 inch) O.D., nominal resistance1·4 ohms, is shown in Figures 2A and 2B.

The silicon carbide elements are mounted inthe stainless steel panel box by inserting themthrough 15·9 mm holes in 0·8 mm thickceramic fibre board. Location of the holes inthe pads and stainless steel cover plates areshown in Figure 2B. The diamond shapedmask of 19 gauge stainless steel is added toprovide uniform heat flux over the areaoccupied by the 150 by 150 mm verticalsample.

(4) Air Distribution System. The airentering the environmental chamber isdistributed by a 6·3 mm thick aluminium platehaving eight, No. 4 drill holes, 51 mm fromsides on 102 mm centres, mounted at the baseof the environmental chamber. A second plateof 18 gauge steel having 120, evenly spaced,No. 28 drill holes is mounted 150 mm abovethe aluminium plate. A well-regulated airsupply is required. The air supply manifold atthe base of the pyramidal section has 48,evenly spaced, No. 26 drill holes located10 mm from the inner edge of the manifold sothat 0·03 m3/second of air flows between thepyramidal sections and 0·01 m3/second flowsthrough the environmental chamber whentotal air flow to apparatus is controlled at0·04 m3/second.

(5) Exhaust Stack. An exhaust stack,133 mm by 70 mm in cross section, and254 mm long, fabricated from 28 gaugestainless steel, is mounted on the outlet of thepyramidal section. A 25 mm by 76 mm plateof 31 gauge stainless steel is centred insidethe stack, perpendicular to the air flow,75 mm above the base of the stack.

(6) Specimen Holders. The 150 mm x150 mm specimen is tested in a verticalorientation. The holder (Figure 3) is providedwith a specimen holder frame, which touchesthe specimen (which is wrapped withaluminium foil as required by sub-paragraph(d)(3)) along only the 6 mm perimeter, and a“V” shaped spring to hold the assemblytogether. A detachable 12 mm x 12 mm x150 mm drip pan and two 0·020 inch stainlesssteel wires (as shown in Figure 3) should beused for testing of materials prone to meltingand dripping. The positioning of the springand frame may be changed to accommodatedifferent specimen thicknesses by inserting

Appendix F (continued)Part IV – Test Method to Determine the Heat Release Rate From Cabin Materials Exposed to

Radiant Heat(See ACJ Appendix F, Part IV)

Text derived from: JAR–25 Appendix F, Part IV at Chg 13, 05/10/89

SECTION 1 JAR–26

1–B–23 13.07.98

the retaining rod in different holes on thespecimen holder.

Since the radiation shield described inASTM E-906 is not used, a guide pin is addedto the injection mechanism. This fits into aslotted metal plate on the injectionmechanism outside of the holding chamberand can be used to provide accuratepositioning of the specimen face afterinjection. The front surface of the specimenshall be 100 mm from the closed radiationdoors after injection.

The specimen holder clips onto themounted bracket (Figure 3). The mountingbracket is attached to the injection rod bythree screws which pass through a wide areawasher welded onto a 0·5 inch nut. The end ofthe injection rod is threaded to screw into thenut and a 0·020 inch thick wide area washer isheld between two 0·5 inch nuts which areadjusted to tightly cover the hole in theradiation doors through which the injectionrod or calibration calorimeter pass.

(7) Calorimeter. A total-flux typecalorimeter must be mounted in the centre ofa 0·5 inch Kaowool “M” board inserted in thesample holder must be used to measure thetotal heat flux. The calorimeter must have aview angle of 180º and be calibrated forincident flux. The calorimeter calibrationmust be acceptable to the Authority.

(8) Pilot-Flame Positions. Pilotignition of the specimen must beaccomplished by simultaneously exposing thespecimen to a lower pilot burner and an upperpilot burner, as described in sub-paragraphs(b)(8)(i) and (b)(8)(ii), respectively. The pilotburners must remain lighted for the entire5-minute duration of the test.

(i) Lower Pilot Burner. Thepilot-flame tubing must be 6·3 mmO.D., 0·8 mm wall, stainless steeltubing. A mixture of 120cm3/min. ofmethane and 850 cm3/min. of air mustbe fed to the lower pilot flame burner.The normal position of the end of thepilot burner tubing is 10 mm from andperpendicular to the exposed verticalsurface of the specimen. The centrelineat the outlet of the burner tubing mustintersect the vertical centreline of thesample at a point 5 mm above the lowerexposed edge of the specimen.

(ii) Upper Pilot Burner. Thepilot burner must be a straight length of6·3 mm O.D., 0·8 mm wall, stainlesssteel tubing 360 mm long. One end ofthe tubing shall be closed, and three No.40 drill holes shall be drilled into thetubing, 60 mm apart, for gas ports, allradiating in the same direction. The firsthole must be 5 mm from the closed endof the tubing. The tube is inserted intothe environmental chamber through a6·6 mm hole drilled 10 mm above theupper edge of the window frame. Thetube is supported and positioned by anadjustable “Z” shaped support mountedoutside the environmental chamber,above the viewing window. The tube ispositioned above and 20 mm behind theexposed upper edge of the specimen.The middle hold must be in the verticalplane perpendicular to the exposedsurface of the specimen which passesthrough its vertical centreline and mustbe pointed toward the radiation source.The gas supplied to the burner must bemethane adjusted to produce flamelengths of 25 mm.

(c) Calibration of Equipment

(1) Heat Release Rate. A burner asshown in Figure 4 must be placed over theend of the lower pilot flame tubing using agas-tight connection. The flow of gas to thepilot flame must be at least 99% methane andmust be accurately metered. Prior to usage,the wet test meter is properly levelled andfilled with distilled water to the tip of theinternal pointer while no gas is flowing.Ambient temperature and pressure of thewater, are based on the internal wet test metertemperature. A baseline flow rate ofapproximately 1 litre/min. is set and increasedto higher preset flows of 4, 6, 8, 6 and 4litres/min. The rate is determined by using astopwatch to time a complete revolution ofthe wet test meter for both the baseline andhigher flow, with the flow returned tobaseline before changing to the next higherflow. The thermopile baseline voltage ismeasured. The gas flow to the burner must beincreased to the higher preset flow andallowed to burn for 2·0 minutes, and thethermopile voltage must be measured. Thesequence is repeated until all five values havebeen determined. The average of the fivevalues must be used as the calibration factor.

Appendix F (Part IV) (continued)

JAR–26 SECTION 1

13.07.98 1–B–24

The procedure must be repeated if the percentrelative standard deviation is greater than 5%.Calculations are shown in paragraph (f).

(2) Flux Uniformity. Uniformity offlux over the specimen must be checkedperiodically and after each heating elementchange to determine if it is within acceptablelimits of ± 5%.

(d) Sample Preparation

(1) The standard size for verticallymounted specimens is 150 x 150 mm withthicknesses up to 45 mm.

(2) Conditioning. Specimens must beconditioned as described in Part I of thisAppendix.

(3) Mounting. Only one surface of aspecimen will be exposed during a test. Asingle layer of 0·025 mm aluminium foil iswrapped tightly on all unexposed sides.

(e) Procedure

(1) The power supply to the radiantpanel is set to produce a radiant flux of3·5 Watts/cm2. The flux is measured at thepoint which the centre of the specimensurface will occupy when positioned for test.The radiant flux is measured after the air flowthrough the equipment is adjusted to thedesired rate. The sample should be tested inits end use thickness.

(2) The pilot flames are lighted andtheir position, as described in sub-paragraph(b)(8), is checked.

(3) The air flow to the equipment isset at 0·04 ± 0·001 m3/s at atmosphericpressure. Proper air flow may be set andmonitored by either: (1) An orifice meterdesigned to produce a pressure drop of atleast 200 mm of the manometric fluid, or by(2) a rotometer (variable orifice meter) with ascale capable of being read to ± 0·0004 m3/s.The stop on the vertical specimen holder rodis adjusted so that the exposed surface of thespecimen is positioned 100 mm from theentrance when injected into the environmentalchamber.

(4) The specimen is placed in the holdchamber with the radiation doors closed. Theairtight outer door is secured, and therecording devices are started. The specimenmust be retained in the hold chamber for60 seconds ± 10 seconds, before injection.

The thermopile “zero” value is determinedduring the last 20 seconds of the hold period.

(5) When the specimen is to beinjected, the radiation doors are opened, thespecimen is injected into the environmentalchamber, and the radiation doors are closedbehind the specimen.

(6) Reserved.

(7) Injection of the specimen andclosure of the inner door marks time zero. Acontinuous record of the thermopile outputwith at least one data point per second mustbe made during the time the specimen is inthe environmental chamber.

(8) The test duration time is fiveminutes.

(9) A minimum of three specimensmust be tested.

(f) Calculations

(1) The calibration factor is calculatedas follows:

K x (210 8 22) l

x 273

x

x x WATT.min

01433 x

h = −−

⋅ −

−⋅ ⋅

( )

( )

F F

V V

kca

mole T

P P moleCH STP

kcal

kW

W

a

v

1 0

1 0

760

4

22 41 1000

F0 = Flow of methane at baseline (1pm)F1 = Higher preset flow of methane (1pm)V0 = Thermopile voltage at baseline (mv)V1 = Thermopile voltage at higher flow (mv)Ta = Ambient temperature (K)P = Ambient pressure (mm Hg)Pv = Water vapour pressure (mm Hg)

(2) Heat release rates may becalculated from the reading of the thermopileoutput voltage at any instant of time as:

HRR = V V

02323 m Km b

2 h−

⋅×

HRR = Heat Release Rate kW/m2

Vm = Measured thermopile voltage (mv)Vb = Baseline voltage (mv)Kh = Calibration Factor (kW/mv)

(3) The integral of the heat releaserate is the total heat release as a function oftime and is calculated by multiplying the rateby the data sampling frequency in minutesand summing the time from zero to twominutes.

Appendix F (Part IV) (continued)

SECTION 1 JAR–26

1–B–25 13.07.98

(g) Criteria. The total positive heatrelease over the first two minutes of exposure foreach of the three or more samples tested must beaveraged, and the peak heat release rate for eachof the samples must be averaged. The averagetotal heat release must not exceed 65 kilowatt-minutes per square metre, and the average peakheat release rate must not exceed 65 kilowattsper square metre.

(h) Report. The test report must include thefollowing for each specimen tested:

(1) Description of the specimen.

(2) Radiant heat flux to the specimen,expressed in Watts/cm2.

(3) Data giving release rates of heat(in kW/m2) as a function of time, eithergraphically or tabulated at intervals no greaterthan 10 seconds. The calibration factor mustbe recorded.

(4) If melting, sagging, delaminating,or other behaviour that affects the exposedsurface area or the mode of burning occurs,these behaviours must be reported, togetherwith the time at which such behaviours wereobserved.

(5) The peak heat release and the2 minute integrated heat release rate must bereported.

INTENTIONALLY LEFT BLANK

Appendix F (Part IV) (continued)

JAR–26 SECTION 1

13.07.98 1–B–26

FIGURE 1 – RELEASE RATE APPARATUS

Appendix F (Part IV) (continued)Appendix F (Part IV) (continued)Appendix F (Part IV) (continued)

SECTION 1 JAR–26

1–B–27 13.07.98

FIGURE 2A – “GLOBAR” RADIANT PANEL

Appendix F (Part IV) (continued)Appendix F (Part IV) (continued)

JAR–26 SECTION 1

13.07.98 1–B–28

(Unless denoted otherwise, all dimensions are in millimeters.)

FIGURE 2B – “GLOBAR” RADIANT PANEL

Appendix F (Part IV) (continued)

SECTION 1 JAR–26

1–B–29 13.07.98

FIGURE 3

Appendix F (Part IV) (continued)

JAR–26 SECTION 1

13.07.98 1–B–30

FIGURE 4

Appendix F (Part IV) (continued)

SECTION 1 JAR–26

1–B–31 13.07.98

FIGURE 5 – THERMOCOUPLE POSITION

Appendix F (Part IV) (continued)

JAR–26 SECTION 1

13.07.98 1–B–32

(a) Summary of Method. The specimensmust be constructed, conditioned, and tested inthe flaming mode in accordance with AmericanSociety of Testing and Materials (ASTM)Standard Test Method ASTM F814-83.

(b) Acceptance Criteria The specificoptical smoke density (DS) which is obtained byaveraging the reading obtained after 4 minuteswith each of the three specimens, shall notexceed 200.

INTENTIONALLY LEFT BLANK INTENTIONALLY LEFT BLANK

Appendix F (continued)Part V – Test Method to Determine the Smoke Emission Characteristics of Cabin Materials

Text derived from: JAR–25 Appendix F, Part V at Chg 13, 05/10/89

SECTION 1 JAR–26

1–C–1 13.07.98

INTENTIONALLY LEFT BLANK

SUBPART C – GENERAL AVIATION (AEROPLANES)[Reserved]

JAR–26 SECTION 1

13.07.98 1–C–2

INTENTIONALLY LEFT BLANK

SECTION 1 JAR–26

1–D–1 13.07.98

INTENTIONALLY LEFT BLANK

SUBPART D – COMMERCIAL AIR TRANSPORTATION (HELICOPTERS)[Reserved]

JAR–26 SECTION 1

13.07.98 1–D–2

INTENTIONALLY LEFT BLANK

SECTION 1 JAR–26

1–E–1 13.07.98

INTENTIONALLY LEFT BLANK

SUBPART E – GENERAL AVIATION (HELICOPTERS)[Reserved]

JAR–26 SECTION 1

13.07.98 1–E–2

INTENTIONALLY LEFT BLANK