Engine Fuel Systems

Advisory

U.S. Department of Transportation Federal Aviation

Circular

Administration Subject: Engine Fuel Systems Date: 05/2 0 /24 AC No: AC 33.67-1 Initiated By: AIR-625 1. PURPOSE This advisory circular (AC) provides guidance for demonstrating compliance with the requirements of Title 14, Code of Federal Regulations (14 CFR) Section 33.67, Fuel s ystem . This AC addresses turbine aircraft engine compliance methods, failure modes, §33.67 lessons learned, and references to associated aircraft-level guidance. It does not address aircraft-level fuel system icing effects or compliance.

2. APPLICABILITY 2.1 The guidance in this AC is for aircraft engine manufacturers, modifiers, Federal Aviation Administration (FAA) engine type-certification engineers, and FAA designees.

2.2 The contents of this document do not have the force and effect of law and are not meant to bind the public in any way. The document is intended only to provide information to the public regarding existing requirements under the law or agency policies. This AC is not mandatory and does not constitute a regulation. This AC describes an acceptable means, but not the only means, to show compliance to §33.67. However, if you use the means described in the AC, you must follow it in all important respects. When the method of compliance in this AC is used, terms such as “should,” “may,” and “must” are used only in the sense of ensuring applicability to this particular method of compliance. The FAA will consider other means of showing compliance that an applicant may elect to present. While these guidelines are not mandatory, they are derived from extensive FAA and industry experience in determining compliance with the relevant regulations. If, however, the FAA becomes aware of circumstances that convince us that following this AC would not result in compliance with the applicable regulations, we will not be bound by the terms of this AC, and we may require additional substantiation as a basis for finding compliance.

2.3 This material in this AC does not change or create any additional regulatory requirements, nor does it authorize changes in, or permit deviations from, existing regulatory requirements.

AC 33.67-1 0 5/20/24 3. RELA TED READING MATERIAL The following materials are referenced in this document. Unless otherwise indicated, you should use the current edition if following the method of compliance set forth in this AC.

3.1 Title 14, Cod e of Federal Regulations (CFRs) • Section 23.2430, Fuel systems.

• Section 25.1305, Powerplant instruments.

• Section 25.1337, Powerplant Instruments.

• Section 27.1305, Powerplant instruments.

• Section 27.1337, Powerplant Instruments.

• Section 29.1305, Powerplant instruments.

• Section 29.1337, Powerplant Instruments.

• Section 33.5, Instruction manual for installing and operating the engine.

• Section 33.7, Engine r atings and o perating l imitations .

• Section 33.17, Fire protection .

• Section 33.67 , Fuel s ystem.

• Section 33.75, Safety analysis.

• Section 33.89 , Operation t est.

3.2 FAA Documents • AC 20 - 24D, Approval of Propulsion Fuels, Additives, and Lubricating Oils.

• AC 20 - 29 B , Use of Aircraft Fuel Anti - i cing Additives.

• AC 20.135, Power plant Installation and Propulsion S ystem Component Fire Protection Test Methods, Standards, and Criteria.

• AC 25.1309 - 1A, System Design and Analysis.

• AC 33 - 2 C , General Type Certification Guidelines for Turbine Engines .

• AC 33.7 - 1, Ratings a nd Operating Limitations f or Turbine Engines.

• AC 33. 17 - 1A, Engine Fire Protection.

3.3 Other U . S . Government Publications • Military Specification MIL - E - 5007 E , Engines, Aircraft, Turbojet and Turbofan, General Specification For, Table X, Fuel Contaminants , dated September 1, 19 8 3 .

AC 33.67-1 05/20/24 • Military Specification MIL - D TL - 85470B, Detail Specification Inhibitor, Icing, Fuel System, High Flash NATO Code Number S - 1745 , dated June 15 , 199 9 .

3.4 Foreign Authority Publications • Air Accident Investigation Branch (AAIB), United Kingdom, Department for Transport , Aircraft Accident Report 1/2010 - Boeing 777 - 236ER, G - YMMM, 17 January 2008: Report on the accident to Boeing 777 - 236ER, G - YMMM, at London Heathrow Airport on 17 January 2008 , dated December 10, 2014 .

3. 5 Industry Publications • SAE International, SAE Aerosp ace Informational Report AIR4246D, Contaminants for Aircraft Turbine Engine Fuel System Component Testing , dated September 27 , 2017.

• SAE International, SAE Aerospace Recommended Practice ARP1401B, Aircraft Fuel System and Component Icing Test , dated June 6, 2012.

• SAE International, SAE Aerospace Recommended Practice ARP 492C, Aircraft Engine Fuel Pump Cavitation Endurance Test , dated Mar ch, 2021.

• SAE International, SAE Aerospace Recommended Practice ARP4024, Aircraft/Engine Fuel Pump Net Positive Suction Pressure Performance Test and Evaluation , dated April, 2020.

• ASTM International, D 4171 - 03, Standard Specification for Fuel System Icing Inhibitors , dated December 1, 2003.

4. DEFINITIONS The following terms and definitions apply to this AC .

• Sticky range . As identified by test, a fuel temperature range between − 5 ° C and − 20 ° C, within which ice can adhere to surfaces and accumulate in the fuel feed system.

• Minimum e ngine i nlet f uel p ressure . T he minimum aircraft fuel pressure required for the engine fuel pump to operate, in case the aircraft pressurization means fails. This pressure is a lso known as “ suction feed ” pressure.

5. BACKGROUND This AC provides guidance for demonstrating compliance with § 33.6 7 , Fuel s ystem , which provides that the engine must function properly under each operating condition required by part 33 with fuel supplied to the engine at the flow and pressure specified by the applicant . T his AC also provides guidance on addressing failure modes recently observed in service , that relate to specific requirements of § 33.67. In addition, this AC includes information on aircraft - level regulations (listed in paragraph 6.2.1) that may also impact engine design .

AC 33.67-1 05/20/24 6. GUIDANCE 6.1 Minimum Engine Fuel Inlet Pressure With fuel supplied to the engine at the flow and pressure specified by the applicant, § 33.6 7 (a) requires that the engine must function properly under each operating condition required by part 33 . The engine applicant should : • D etermine the min imum engine inlet fuel pressure the engine requires for proper operation.

• As part of the § 33.75 safety analysis, c onsider , when applicable, the condition in which the aircraft ’s means of fuel pressurization fail s ( also known as “ suction feed ” ) and consult with the aircraft manufacturer to determine any other operations in which aircraft - level fuel pressurization is lost .

I nclude any related engine limit ations in the installation instructions required by § 33.5 .

Fuel pressure at the engine fuel inlet is also a requirement of § 33.7(c)(6)(i). Detailed guidance is provided in AC 33.7 - 1 , paragraph 15 , and summarized here . The minimum and maximum fuel inlet pressures , and when applicable, the associated ambient conditions or vapor - to - liquid ratio, will be incorporated in the e ngine t ype c ertificate d ata s heet. The engine instructi ons for continued airworthiness should also include any maintenance actions required if the engine has operated with the aircraft fuel pump in a degraded or failed condition. Findings of c ompliance s hould consider all fuel types , additives, and acceptable fuel property variations as discussed in the fuel designations or specifications proposed under § 33. 7 (c)(2).

6.2 Fuel F ilt ration L imits and B ypass Flight d eck I ndication 6.2.1 Any operational fuel filtration limit ations must be specified as required by § 33.7(c)(9) and included in the approved instruction s for ins talling and operating the engine as required by § 33.5 . The engine applicant should also be aware of aircraft - level requirements that may r equire certain engine instrumentation interfaces , ports, or other fea tures to support flightdeck indication of filter, strainer , or other fuel bypass systems.

These aircraft requirements include : Section 23.2430, Fuel systems , Section 25.1305, Powerplant instruments, Section 27.1305, Powerplant instruments Section 29.1305, Powerplant instruments, The applicant should coordinate with the aircraft manufacturer to determine which bypass systems require flightdeck indication. In addition to the required fuel filter, engine fuel systems commonly include additional filters and screens to prevent clogging and damage to engine components in the fuel system, such as screens that have been installed downstream of the engine-driven pump to prevent debris from contaminating downstream components. The aircraft manufacturer will assess these AC 33.67-1 05/20/24 features as part of the engine and aircraft fuel system analysis with the support of the engine manufacturer in order to determine potentia l consequences of bypass operations on the engine. The sections referenced at the beginning of this paragraph contain the requirement s for the flightdeck indication for different aircraft types .

6.3 Prevention of H azardous Engine Effects from F uel L ine F ailur es Section 33.67 (b)(3) requires that any fuel strainer or filter must be mounted so that its weight is not supported by the connecting lines or by the inlet or outlet connections of the strainer or filter, unless adequate strength margins under all loading conditions are provided in the lines and connections. Other regulations also include requi rements that may affect the fuel system design. Section 33.75 , Safety analysis , paragraph (a)(3) states , in pertinent part , “ The applicant must show that hazardous engine effects are predicted to occur at a rate not in excess of that defined as extremely remote ( at a rate - 7 - 9 of occurrence less than 10 to 10 per engine flight hour). ” Section 33.75 (g) (2) (iv) states that an uncontrolled fire is considered a hazardous engine effect. Applicants should show that the chance of uncontrolled fire from failures of fuel lines is extremely remote. Section 33.17, Fire protection includes requirements on uncontrolled fire prevention and protection. Refer to AC 20 - 135 , Powerplant Installation and Propulsion System Component Fire Protection Test Methods, Standards, a nd Criter i a , and AC 33.17 - 1A , Engine Fire Protection for further guidance . Also, engine manufacturers should be aware that aircraft airworthiness standards (§ § 23.1337, 25.1337 , 27.1337 and 29.1337 ) specifically call out requirement s for instrumentation lines carrying flammable fluids under pressure to have restricting orifices or other safety devices at the source of pressure to prevent the escape of excessive fluid if the line fails. One means of limiting the fluid loss in a pipe f ailure is to include a restricting feature near each fuel pressure connection provided for instrumentation.

6.4 Hazards from W ater and I ce in F uel 6.4.1 S everal types of hazards can result from water in the fuel.

Section 33.67(b)(4)(ii) requires that the fuel system is capable of sustained operation throughout its flow and pressure range with the fuel initially saturated with water at 80 ° F (27 ° C) and having 0.025 fluid ounces per gallon (0.20 milliliters per liter) of free water added and cooled to th e most critical condition for icing likely to be encountered in operation. Fuel is hydrophilic and will absorb water from the atmosphere over time.

This absorption can be mitigated but not eliminated by the use of ground refueling water filtration system s . T herefore , applicants should expect water to be absorbed by fuel in service .

6.4.2 Engine operation with water in the fuel .

Applicants must ensure that their engine will operate satisfactorily throughout the flight envelope , in accordance with § 33.65 , Surge and s tall c haracteristics and § 33.89 (b) , Operation t est , with the concentration of liquid water required by § 33.67 (b) (4)(ii) . In addition, applicants should ensure that operation with the amounts of water specified will not result in engine damage that could lead to a hazardous engine effect or failure.

05/20/24 AC 33.67-1 6.4.3 Ice from aircraft fuel system .

One accident , described below, and at least three in - flight incidents have been attributed to engine power interruption due to restrict ion in fuel flow to the engine caused by the release of ice from aircraft fuel tubing.

6.4.3.1 Engine F uel R estriction or B lockage C aused by I ce O n January 17, 2008, an accident occurred when a t ransport airplane powered by two large turbofan engines operating from Beijing , China to London , England , crash - landed short of London Heathrow Airport runway 27L . The United Kingdom , Department for Transport, Air Accident Investigation Branch ( AAIB ), December 10, 2014, Aircraft Accident Repor t 1/2010 - Boeing 777 - 2 36ER, G - YMMM, 17 January 2008: Report on the accident to Boeing 777 - 236ER, G - YMMM, at London Heathrow Airport on 17 January 2008 ( “ AAIB report ” ) , identified the following probable causal factors that led to the fuel flow restrictions: • Ice had formed within the fuel system, from water that occurred naturally in the fuel, while the aircraft operated with low fuel flows and lower fuel velocities in the fuel lines over a long period, and the localized fuel temperatures were in an area desc ribed as the “ sticky range. ” • When the throttle was increased , which increased the fuel demand, accreted ice from within the fuel system released, causing a restriction to the engine fuel flow at the face of the FOHE on both of the engines.

• The FOHE, although it had shown compliance to the applicable certification requirements, was susce ptible to restriction when presented with soft ice in a high concentration, with a fuel temperature that is below ‑10°C and a fuel flow above flight idle.

Note: The investigation team discovered no abnormal water concentrations in the fuel system and subse quent analysis of fuel samples showed the fuel met all applicable standards, including for water content.

6.4.3.2 Sudden Release of Ice and Water I n some aircraft designs, under certain conditions, water and ice can accumulate and suddenly release . Those conditions include operation at very low ambient temperatures for long periods, followed by warmer ambient conditions. This can occur even though bulk fuel water concentrations are consistent with § 33.67 (b)(4)(ii) . Soft and compactable ice can c ause flow blockage around entries to narrow passages of th e FOHE , filter elements , or strainers. This fuel icing behavior has become better understood as a result of investigation s and should be addressed when showing compliance to § 33.67(b)(4)(ii).

05/20/24 AC 33.67-1 6.4.3.3 Analysis of Sudden Release of Ice and Water To address the sudden release of ice and water into the engine fuel system, aircraft fuel system analysis is necessary to establish both the amount and physical state of ice and water that could threaten the engine. When setting the aircraft threat, the engine manufacturer should work with the aircraft manufacturer to establish the maximum amount of ice in the fuel released from the aircraft fuel system that the engine may encoun ter in service. Afterward, each engine fuel system component should be evaluated under its most critical condition for fuel icing regarding fuel temperature, duration, fuel flow, fuel properties, water content , and potential continuous exposure to ice acc umulation and release in the engine fuel system. Test experience has shown difficulty in consistently forming ice under laboratory conditions that can replicate the ice formation observed in actual installations. The aircraft applicant should consider fa ctors that affect the formation and possible release of ice in the aircraft fuel system, such as temperature ranges that influence the creation, collection , and release of the ice , such as the sticky temperature range described in the AAIB report . The aircraft applicant s hould communicate the appropriate technical requirements from this analysis to the engine applicant so that the engine applica nt can show compliance with § 33.67.

Critical icing temperature and component features that could contribute t o the formation and possible release of ice in the engine fuel system should be reexamined for derivative engine models and new applications of existing engines.

6.4.3.4 Ice Proportions The engine must function properly when exposed to the maximum amount of ice that may be released from the aircraft into the engine, or up to the limit defined by the engine manufacturer , given the concentrations of water in § 33.67(b)(4)(ii) . In addition, § 33.67(b)(4)(ii) requires that the fuel system is capable of sustained operation throughout its flow and pressure range, with the fuel initially saturated with water and cooled to the most critical condition for icing likely to be encountered in operation.

The analysis should consider each area in the engine fuel s ystem vulnerable to ice accretion. I ce release may not cause any unrecoverable or permanent thrust loss .

6.4.3.5 Compliance Demonstration During the compliance demonstration of the cooled, water - saturated fuel portion of § 33.67 (b)(4)(ii) , the applicant may either: 1. D e monstrate tolerance to the maximum amount of ice that may be released from the aircraft to the engine .

Engine m anufacturers should work with the engine installer or air - framer to define the maximum amount of ice that can be released at AC 33.67-1 05/20/24 once by the aircraft’s fuel system . T he maximum amount of ice should be declared in the engine installation instructions . Then, t he engine manufacturer should show through component , system, or engine test s that the turbine engine and its components (e.g., engine or generator FOHE s, fuel filter, engine - driven pump, or fuel control), will not be adversely affected by that amount of ice , or 2. Define the maximum water or ice that will not affect the engine .

A n engine manufacturer may show, independent of the installer through component or engine test, the maximum ice amount that will not adversely affect engine operati on. In this case, the applicant should include an engine limitation within the installation instructions required by § 33.5, the maximum amount of ice that will not adversely affect engine operation .

The engine applicant may perform component testing as re commended in SAE ARP1401B to comply with § 33.67(b)(4)(ii).

6.4.3.6 High Concentra t ions of Water The applicant should consider a nother hazard related to ice formation in the aircraft fuel system which i nvolves releasing transiently high water concentrations into the engine fuel system. Water concentrations much higher than the amount in § 33.67(b)(4 ) (ii) can be released into the engine when ice forms in the aircraft fuel system and then melts, either before reaching the engine or upon contact w ith the first engine component it encounters.

6.4.3.7 Engine Power Loss Engine manufacturers should consider power loss from high concentrations of water which can freeze inside the engine fuel filter (s) or cause additional ice downstream of the f ilter(s) . Freezing of the water in a saturated filter could reduce the ice holding capability of the filter.

Alternatively, release of water from a pre - wetted filter may result in additional ice down s tream of the fuel filter, over and above what may be p resented by a filter bypass. This is caused by transport of ice from upstream of the filter causing a reduction in fuel temperature and freezing of the released water.

6. 4 .3.8 Other Failure Modes There are o ther failure modes caused by the ingestion of me lted ice in the fuel to consider. Depending on the engine design, the water concentration and the total amount of water released can cause failures such as flameout or fuel system damage. Applicants should consider these additional failure modes when evaluating the potential effects of ice in the fuel.

6.4.4 Anti - icing additives AC 33.67-1 05/20/24 The engine applicant may show compliance to § 33.67(b)(4 ) (ii) by stipulating the use of specified , approved fuel anti - icing additives . A lternatively, the engine applicant may demonst rate that the engine fuel system will maintain the fuel temperatu re at the fuel strainer or fuel inlet above 32°F (0°C) under the most critical conditions .

6. 4 .4.1 Guidance for Fuel Anti - Icing Additives AC 20 - 29 B , Use of Aircraft Fuel Anti - icing Additives , provides guidance on the use of anti - icing additives PFA - 55MB and MIL - I - 27686 in turbine aircraft fuel systems. MIL - DTL - 85470B and Type 3 Diethylene glycol monomethyl ether (DiEGME) as described in ASTM D 4171 - 03 may also be used. Applicants should coordinate the use of anti - icing additives with the aircraft manufacturer since an engine requirement to use anti - icing additives will become a limitation in the Aircraft Flight Manual.

6. 4 .4.2 Fuel Anti - Icing Additives If an applicant elect s to compl y with § 33.67(b)(4 ) (ii) by means of fuel anti - icing additives , an operating limitation must be specified in accordance with § 33.7 and included in the installation instructions required by § 33.5 . The applicant must also include appropriate engine operating information on the use of fuel anti - icing additives in the § 33.5 operating instructions . Information will be included in the engine t ype d esign d ata s heet if fuel anti - icing additives are used to comply with § 33.67 (b)(4)(ii) .

6.5 Fuel Contamination For § 33.67(b)(5) compliance, one - half the maximum predicted mission flight time has been considered to be a period acceptable to the Administrator for the demonstration time period. Test demonstrations should be conducted at typical running conditions with respect to rotational speeds, pressures and fuel flow. Refer to Table X of Military Specification MIL - E - 5007 E , “ Engines, Aircraft, Turbojet and Turbofan, General Specification For , Table X, Fuel Cont aminants ” for examples of fuel contaminants, particle sizes, and quantities to be considered. SAE International, SAE Aerospace Informational Report AIR 4246D, Contaminants for Aircraft Turbine Engine Fuel System Component Testing contains additional infor mation on potential contaminants.

M IL - E - 5007E and SAE AIR 4246D contain representative, but not exhaustive, examples of fuel contaminants; an engine applicant should consider other fuel contaminants from service history or other sources that may not be di scussed in MIL - E - 5007E and SAE AIR 4246D if applicable. If the engine is intended for use in Extended Operations (ETOPS), the mission time for calculating the amount of fuel contamination should be either the approved ETOPS diversion capability, plus 15 m inutes, or one - half of the maximum predicted flight time, whichever is longer.

6.6 Fluid I njection When complying with § 33.67(c) , the applicant must show for each fluid injection ( other than fuel ) system and its controls that the flow of the injected fluid is adequately AC 33.67-1 05/20/24 controlled . F luid injection (other than fuel) refers to any fluid (for example, water) injected into the airstream . The requirements of § 33.67(c) apply irrespective of the location of fl uid injection into the engine.

6.7 Communicating the Certification Plan and Results The engine applicant should coordinate with the aircraft manufacturer to ensure that engine characteristics, limitations , or requirements that may affect aircraft certifica tion are properly documented and communicated. As a minimum, any engine limitations must be included in the operating instruction required by § 33.5 (b)(1) . Issues to coordinate may consist of : • F uel anti - icing additives required or allowed to be used .

• The maximum limit of allowable ice in the fuel that the engine can accept and still function properly in accordance with § 33.67(a). If the engine applicant has determined the amount of ice that the engine can accept and still properly function independent of an ai r craft manufacturer, the applicant should include a limitation in the installation instruction s .

• Minimum fuel pressure requirements with and without operating aircraft fuel pumps and any maintenance requirements resulting from engine operation wit h a failed aircraft fuel pump.

• Fuel transfer back to the aircraft fuel tank if a fuel - return circuit is included in the engine design. If the engine has a system that sends excess fuel back to the aircraft fuel tank, the applicant should coordinate with the aircraft manufacturer about necessary information on the amount of fuel returned . This information should include return fuel flow rate requirements to ensure proper engine function, the temperature of the returned fuel , and the amount of heat expect ed to be added to the aircraft fuel tank.

AC 33.67-1 05/20/24 7. SUGGESTIONS FOR IMPROVING THIS AC If you have suggestions for improving this AC, you may use the Advisory Circular Feedback Form at the end of this AC.

Digitally signed by

DANIEL

DANIEL J. ELGAS Date: 2024.05.20

J. ELGAS

13:13:20 -04'00' Daniel J. Elgas Director, Policy and Standards Division, Aircraft Certification Service.

OMB Control Number: 2120-0746 Expiration Date: 11/30/2024 Advisory Circular Feedback Form Paperwork Reduction Act Burden Statement: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collecti on of information displays a currently valid OMB Control Number. The OMB Control Number for this information collection is 2120 - 0746. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. All responses to this collection of information are voluntary to obtain or retain bene fits per 14 CFR 77. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to: Information Collection Clearance Officer, Federal Aviation Administration, 10101 Hill wood Parkway, Fort Worth, TX 76177 - 1524.

If you find an error in this AC, have recommendations for improving it, or have suggestions for new items/subjects to be added, you may let us know by (1) emailing this form to ( ) or (2) faxing it to the attention of the LOB/SO ( ).

Subject: Date: Please mark all appropriate line items: □ An error (procedural or typographical) has been noted in paragraph on page .

□ Recommend paragraph on page be changed as follows: □ In a future change to this AC, please cover the following subject: (Briefly describe what you want added.)

□ Other comments: □ I would like to discuss the above. Please contact me.

Submitted by: Date: FAA Form 1320-73 (11/21) SUPERSEDES PREVIOUS EDITIONS