Engine Exhaust and Reverser Systems

Engine Exhaust and Reverser Systems

Overview

This chapter covers the design, function, inspection, maintenance, and troubleshooting of aircraft engine exhaust systems for both reciprocating and turbine engines, as well as thrust reverser systems. The exhaust system is critical for engine performance, aircraft safety, and cabin occupant protection. For reciprocating engines, exhaust systems must safely route hot gases away from the airframe while preventing carbon monoxide entry into the cabin. For turbine engines, the exhaust system manages high-velocity gas flow to produce thrust and may incorporate thrust reversers for ground deceleration. This chapter emphasizes the inspection requirements, damage limits, repair criteria, and documentation obligations that AMEs must understand to maintain airworthiness.

Reciprocating Engine Exhaust Systems

System Components and Functions

Reciprocating engine exhaust systems collect exhaust gases from each cylinder and route them overboard. The primary components include:

Materials and Construction

Exhaust components are typically fabricated from:

Stainless steel is the most common material for reciprocating engine exhaust systems due to its ability to withstand the extreme thermal cycling and corrosive byproducts of combustion. The material must handle temperatures ranging from ambient to over 1,200°F during operation.

Thermal Stress and Failure Modes

Exhaust systems operate under extreme conditions that promote failure:

Common failure locations include:

Inspection Requirements

Exhaust system inspection is a critical part of every 100-hour and annual inspection. The inspection must include:

Repair vs. Replacement Decisions

When exhaust system defects are found, the AME must determine the correct action:

Cracked welds: Cracks in exhaust system welds are serious defects. AC 43.13-1B does not provide for welding repair of cracked exhaust manifolds as an acceptable practice unless specifically approved by the manufacturer. Drilling stop holes or applying sealant is not an approved repair. The component must be replaced unless the manufacturer provides a specific approved repair procedure.

Corrosion holes: Exhaust components with corrosion or holes are unairworthy. Patching with epoxy or other sealants is not an approved repair. Replacement is typically the safest and most compliant action. Welding may be acceptable only if performed per manufacturer instructions with proper inspection.

Damaged mufflers: A cracked or corroded muffler is a serious safety issue due to the risk of carbon monoxide entering the cabin and the potential for fire. Replacement is required rather than repair, as welding can alter material properties and is often not approved by the manufacturer.

Leaking slip joints: Exhaust leaks at slip joints must be properly addressed. Simply tightening or sealing externally is not an acceptable repair. The correct action is to disassemble, inspect, and replace defective parts, then perform a leak check per manufacturer instructions.

Loose flange connections: A small leak at a flange connection is often due to insufficient torque or a slightly loose gasket. The correct maintenance practice is to first torque the fasteners to the manufacturer's specified value, then perform an operational check for leaks. Over-torquing can distort flanges or damage gaskets. Sealants are not approved for exhaust joints as they can break down and create a fire hazard.

Carbon Monoxide Hazards

Carbon monoxide (CO) is a colorless, odorless, and deadly gas produced by incomplete combustion. Exhaust leaks can allow CO to enter the cabin through:

When a pilot reports a burning smell in the cabin or any symptom of CO exposure, the AME must immediately inspect the entire exhaust system, especially the heater shroud, for cracks or leaks. This is a critical safety inspection that cannot be deferred.

Turbine Engine Exhaust Systems

System Components and Functions

Turbine engine exhaust systems manage the high-velocity, high-temperature gas flow exiting the turbine section. Key components include:

Damage Assessment

Turbine exhaust components are subject to:

Inspection and NDT Methods

When thermal distress or cracking is suspected:

Dye penetrant inspection is a non-destructive test that can reveal the extent of cracking in exhaust components. The results determine whether the nozzle is within limits or requires repair/replacement. Polishing or ignoring discoloration is not acceptable.

Damage Limits and Manufacturer's Data

Turbine exhaust components are often subject to strict damage limits defined by the engine manufacturer. The AME must:

For example, if the manufacturer's manual requires replacement if distortion exceeds 0.030 inch, and the measured distortion is 0.028 inch, the part is within limits and is airworthy. Documentation of the inspection is required per 14 CFR 43.9.

If a dent is within allowable limits, no repair is required. If the damage exceeds limits, the component must be repaired per approved procedures or replaced. Hammering out dents or applying patches without approved data is not acceptable.

Repair Procedures

When the manufacturer's manual provides a repair procedure for a cracked weld or other defect, the repair may be accomplished following that procedure. The repair must be documented per 14 CFR 43.9.

When no approved repair procedure exists in the manufacturer's manual, the part must be replaced to maintain airworthiness. AC 43.13-1B provides general repair practices, but for critical engine components like exhaust cones, manufacturer's data takes precedence. Drilling stop-holes or welding without approved data is not acceptable.

Thrust Reverser Systems

Purpose and Types

Thrust reversers are used on turbine engines to:

Common types include:

System Components

Thrust reverser systems typically include:

Rigging and Adjustment

Proper rigging is critical for thrust reverser operation. The rigging procedure typically specifies:

After any maintenance involving the reverser system, rigging must be verified. Static measurements alone are insufficient; the system must be functionally tested. Mechanical components can shift or bind under load and movement, so dynamic verification is required.

If a thrust reverser deploys but does not fully lock after actuator replacement, the most likely cause is improper rigging. Improper rigging will prevent the mechanical locks from engaging fully, even if hydraulic pressure is normal. A faulty switch or low pressure would typically prevent deployment altogether or cause erratic movement, not a consistent failure to lock.

Hydraulic System Maintenance

Hydraulic leaks in thrust reverser systems can affect deployment and stow, creating a safety hazard. The aircraft must be in an airworthy condition per 14 CFR 91.7. The maintenance manual requires repairing leaks before return to service. Deferring or merely adding fluid is not an acceptable maintenance action.

When a functional test reveals a longer stow time than specified, this indicates a problem such as:

Troubleshooting is necessary to identify and correct the cause. Simply adjusting the flow control valve or replacing components without diagnosis is not proper practice.

Safety Considerations

Thrust reverser malfunctions can create serious safety hazards:

If an asymmetric deployment occurs during a ground run, the mechanic must immediately stow the reverser and troubleshoot per the AMM to find the root cause before returning the aircraft to service. Simply repeating the run, logging the event, or deactivating without proper troubleshooting does not address the underlying defect and violates the requirement to return the aircraft to service in an airworthy condition.

Troubleshooting Approach

The first step in any troubleshooting process is to consult the applicable maintenance manual (AMM) or manufacturer's instructions. This ensures the technician follows approved procedures, safety precautions, and system-specific logic. Randomly cycling or deploying the reverser without following the manual could cause further damage or create a safety hazard.

The AMM will guide the technician through a systematic approach, which is a fundamental principle of airworthiness per 14 CFR 43.13(a).

Safetying Requirements

Safety Wire Installation

Safety wire is a critical locking device on engine components, especially those subject to vibration. This includes:

Per AC 43.13-1B, safety wire must be installed in accordance with the manufacturer's instructions. If safety wire is missing, the correct action is to install new safety wire and make a logbook entry per 14 CFR 43.9.

Important: Using thread-locking compound is not an approved substitute for safety wire unless explicitly authorized by the manufacturer. Replacing the bolt is unnecessary unless it is damaged. Deferring the repair is not acceptable because the component is not in an airworthy condition.

Safetying Methods

AC 43.13-1B Chapter 7 provides detailed safetying methods, including:

Exhaust System Troubleshooting

Symptom-Based Diagnosis

Soot streaks around exhaust stack flanges: Typically indicate an exhaust leak. The first step is to verify that all fasteners are properly torqued per the maintenance manual, as loose flange nuts are a common cause. Simply replacing the gasket or sealing externally does not address the root cause and may be an unacceptable practice.

Increased exhaust gas temperature (EGT) with increased fuel flow: A partially blocked exhaust nozzle throat increases exhaust backpressure, which reduces the pressure ratio across the turbine and reduces mass flow, requiring more fuel to maintain the same power setting and resulting in higher exhaust gas temperature.

A leaking exhaust joint would allow cooler air to enter and lower indicated EGT. A faulty thermocouple would cause an erratic or erroneous indication, not necessarily a consistent rise with increased fuel flow. Worn turbine blade tips would cause a loss of efficiency but typically would not show a significant EGT rise with only a slight fuel flow increase.

Burning smell in the cabin: Most likely caused by exhaust leaks in cabin heater systems. This is extremely dangerous and can lead to carbon monoxide poisoning. The mechanic must immediately inspect the entire exhaust system, especially the heater shroud, for cracks or leaks.

Documentation and Regulatory Requirements

Return to Service Documentation

Per 14 CFR 43.9, the following documentation is required when returning an aircraft to service after maintenance:

This applies to:

FAA Form 337 Requirements

FAA Form 337 is required for major repairs and major alterations. Examples of when it is NOT required:

Airworthiness Requirements

14 CFR 43.13(a) requires the mechanic to ensure the aircraft is in condition for safe operation. This means:

FAA-PMA Parts

FAA-PMA (Parts Manufacturer Approval) parts are approved as replacement parts and may be installed by A&P mechanics. A return-to-service entry must be made per 14 CFR 43.9. There is no requirement for repair station approval for a simple part replacement.

Key Relationships and Concepts

Manufacturer's Data vs. General Practices

The hierarchy of maintenance authority is:

For critical engine components like exhaust cones and thrust reverser components, manufacturer's data takes precedence. AC 43.13-1B provides general repair practices, but specific procedures and limits from the manufacturer must be followed.

Inspection and Documentation Cycle

The maintenance process follows a logical sequence:

Safety Priorities

The primary safety concerns in exhaust and reverser systems are:

These priorities drive the inspection requirements and the strict standards for repair vs. replacement decisions.

Summary of Critical Actions

Conclusion

The exhaust and thrust reverser systems are critical to aircraft safety and performance. The AME must understand the materials, failure modes, inspection requirements, and repair criteria for these systems. The key principles are:

By applying these principles, the AME ensures that exhaust and reverser systems are maintained to the highest standards of airworthiness.