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14 CFR Ch. I (1–1–02 Edition)Pt. 21, SFAR No. 88

(4) There must be means to allow the crewto check, in flight, the function of each firedetector electric circuit.

(5) Wiring and other components of eachfire detector system in an engine compart-ment must be at least fire resistant.

(b) Fire extinguishing systems. (1) Except forcombustor, turbine, and tail pipe sections ofturbine engine installations that containlines or components carrying flammablefluids or gases for which it is shown that afire originating in these sections can be con-trolled, there must be a fire extinguishersystem serving each engine compartment.

(2) The fire extinguishing system, thequantity of the extinguishing agent, the rateof discharge, and the discharge distributionmust be adequate to extinguish fires. An in-dividual ‘‘one shot’’ system may be used.

(3) The fire-extinguishing system for a na-celle must be able to simultaneously protecteach compartment of the nacelle for whichprotection is provided.

12. Fire extinguishing agents. Comply with§ 25.1197 of this chapter in effect on Sep-tember 26, 1978.

13. Extinguishing agent containers. Complywith § 25.1199 of this chapter in effect on Sep-tember 26, 1978.

14. Fire extinguishing system materials. Com-ply with § 25.1201 of this chapter in effect onSeptember 26, 1978.

15. Expiration. This Special Federal Avia-tion Regulation terminates on September 13,1983, unless sooner rescinded or superseded.

[Doc. No. 18315, 44 FR 53729, Sept. 17, 1979; 45FR 25047, Apr. 14, 1980; 45 FR 80973, Dec. 8,1980, as amended by Doc. No. 21716, 47 FR35153, Aug. 12, 1982]

SPECIAL FEDERAL AVIATION REGULATIONNO. 88—FUEL TANK SYSTEM FAULTTOLERANCE EVALUATION REQUIRE-MENTS

1. Applicability. This SFAR applies to theholders of type certificates, and supple-mental type certificates that may affect theairplane fuel tank system, for turbine-pow-ered transport category airplanes, providedthe type certificate was issued after January1, 1958, and the airplane has either a max-imum type certificated passenger capacity of30 or more, or a maximum type certificatedpayload capacity of 7,500 pounds or more.This SFAR also applies to applicants fortype certificates, amendments to a type cer-tificate, and supplemental type certificatesaffecting the fuel tank systems for those air-planes identified above, if the applicationwas filed before June 6, 2001, the effectivedate of this SFAR, and the certificate wasnot issued before June 6, 2001.

2. Compliance: No later than December 6,2002, or within 18 months after the issuanceof a certificate for which application was

filed before June 6, 2001, whichever is later,each type certificate holder, or supplementaltype certificate holder of a modification af-fecting the airplane fuel tank system, mustaccomplish the following:

(a) Conduct a safety review of the airplanefuel tank system to determine that the de-sign meets the requirements of §§ 25.901 and25.981(a) and (b) of this chapter. If the cur-rent design does not meet these require-ments, develop all design changes to the fueltank system that are necessary to meetthese requirements. The FAA (Aircraft Cer-tification Office (ACO), or office of theTransport Airplane Directorate, having cog-nizance over the type certificate for the af-fected airplane) may grant an extension ofthe 18-month compliance time for develop-ment of design changes if:

(1) The safety review is completed withinthe compliance time;

(2) Necessary design changes are identifiedwithin the compliance time; and

(3) Additional time can be justified, basedon the holder’s demonstrated aggressivenessin performing the safety review, the com-plexity of the necessary design changes, theavailability of interim actions to provide anacceptable level of safety, and the resultinglevel of safety.

(b) Develop all maintenance and inspectioninstructions necessary to maintain the de-sign features required to preclude the exist-ence or development of an ignition sourcewithin the fuel tank system of the airplane.

(c) Submit a report for approval to theFAA Aircraft Certification Office (ACO), oroffice of the Transport Airplane Directorate,having cognizance over the type certificatefor the affected airplane, that:

(1) Provides substantiation that the air-plane fuel tank system design, including allnecessary design changes, meets the require-ments of §§ 25.901 and 25.981(a) and (b) of thischapter; and

(2) Contains all maintenance and inspec-tion instructions necessary to maintain thedesign features required to preclude the ex-istence or development of an ignition sourcewithin the fuel tank system throughout theoperational life of the airplane.

[Doc. No. 1999–6411, 66 FR 23129, May 7, 2001]

Subpart A—General

§ 21.1 Applicability.

(a) This part prescribes—(1) Procedural requirements for the

issue of type certificates and changesto those certificates; the issue of pro-duction certificates; the issue of air-worthiness certificates; and the issueof export airworthiness approvals.

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Federal Aviation Administration, DOT § 21.3

(2) Rules governing the holders ofany certificate specified in paragraph(a)(1) of this section; and

(3) Procedural requirements for theapproval of certain materials, parts,processes, and appliances.

(b) For the purposes of this part, theword ‘‘product’’ means an aircraft, air-craft engine, or propeller. In addition,for the purposes of Subpart L only, itincludes components and parts of air-craft, of aircraft engines, and of propel-lers; also parts, materials, and appli-ances, approved under the TechnicalStandard Order system.

[Doc. No. 5085, 29 FR 14563, Oct. 24, 1964, asamended by Amdt. 21–2, 30 FR 8465, July 2,1965; Amdt. 21–6, 30 FR 11379, Sept. 8, 1965]

§ 21.2 Falsification of applications, re-ports, or records.

(a) No person shall make or cause tobe made—

(1) Any fraudulent or intentionallyfalse statement on any application fora certificate or approval under thispart;

(2) Any fraudulent or intentionallyfalse entry in any record or report thatis required to be kept, made, or used toshow compliance with any requirementfor the issuance or the exercise of theprivileges of any certificate or ap-proval issued under this part;

(3) Any reproduction for a fraudulentpurpose of any certificate or approvalissued under this part.

(4) Any alteration of any certificateor approval issued under this part.

(b) The commission by any person ofan act prohibited under paragraph (a)of this section is a basis for suspendingor revoking any certificate or approvalissued under this part and held by thatperson.

[Doc. No. 23345, 57 FR 41367, Sept. 9, 1992]

§ 21.3 Reporting of failures, malfunc-tions, and defects.

(a) Except as provided in paragraph(d) of this section, the holder of a TypeCertificate (including a SupplementalType Certificate), a Parts Manufac-turer Approval (PMA), or a TSO au-thorization, or the licensee of a TypeCertificate shall report any failure,malfunction, or defect in any product,part, process, or article manufacturedby it that it determines has resulted in

any of the occurrences listed in para-graph (c) of this section.

(b) The holder of a Type Certificate(including a Supplemental Type Cer-tificate), a Parts Manufacturer Ap-proval (PMA), or a TSO authorization,or the licensee of a Type of Certificateshall report any defect in any product,part, or article manufactured by itthat has left its quality control systemand that it determines could result inany of the occurrences listed in para-graph (c) of this section.

(c) The following occurrences mustbe reported as provided in paragraphs(a) and (b) of this section:

(1) Fires caused by a system or equip-ment failure, malfunction, or defect.

(2) An engine exhaust system failure,malfunction, or defect which causesdamage to the engine, adjacent aircraftstructure, equipment, or components.

(3) The accumulation or circulationof toxic or noxious gases in the crewcompartment or passenger cabin.

(4) A malfunction, failure, or defectof a propeller control system.

(5) A propeller or rotorcraft hub orblade structural failure.

(6) Flammable fluid leakage in areaswhere an ignition source normally ex-ists.

(7) A brake system failure caused bystructural or material failure duringoperation.

(8) A significant aircraft primarystructural defect or failure caused byany autogenous condition (fatigue, un-derstrength, corrosion, etc.).

(9) Any abnormal vibration or buf-feting caused by a structural or systemmalfunction, defect, or failure.

(10) An engine failure.(11) Any structural or flight control

system malfunction, defect, or failurewhich causes an interference with nor-mal control of the aircraft for whichderogates the flying qualities.

(12) A complete loss of more than oneelectrical power generating system orhydraulic power system during a givenoperation of the aircraft.

(13) A failure or malfunction of morethan one attitude, airspeed, or altitudeinstrument during a given operation ofthe aircraft.

(d) The requirements of paragraph (a)of this section do not apply to—

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