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2003-09-14: Combustion chamber assemblies

FAA order 2003-09-14 is an airworthiness directive in force since June 12, 2003. The FAA's subject line: Combustion chamber assemblies. It names the General Electric CF34-8C1 engine: about 1 aircraft on the U.S. register today, though an order usually covers particular versions or serial numbers rather than every one. System: engine.

What it applies to as the FAA lists it

Kind of product
Engine
Makes
General Electric Company
Models
CF34-8C1
Engine series
General Electric CF34-8C1 1 aircraft

Dates and paperwork

In force since
June 12, 2003
Published
May 8, 2003 (signed May 1, 2003)
Docket
2002-NE-23-AD
Status
Current
The FAA's document
Read the order on the FAA's site

The FAA's summary their words, unchanged

This amendment adopts a new airworthiness directive (AD), that is applicable to General Electric (GE) CF34-8C1 turbofan engines. This amendment requires replacing combustion chamber assemblies, part number (P/N) 4126T87G04, before accumulating a new reduced cyclic life limit. This amendment is prompted by stress and life analysis conducted by GE. The actions specified by this AD are intended to prevent rupture of the combustion chamber assembly and possible engine fire.

The order itself the regulatory text, as published

Show the full text (2,226 characters)
2003-09-14 General Electric: Amendment 39-13143. Docket No. 2002-NE-23-AD. Applicability: This airworthiness directive (AD) is applicable to General Electric (GE) CF34-8C1 turbofan engines with combustion chamber assembly, part number (P/N) 4126T87G04, installed. These engines are installed on, but not limited to Bombardier Inc. Model CL-600-2C10 (CRJ-700 & 701) airplanes. Note 1: This AD applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Compliance with this AD is required as indicated, unless already done. To prevent rupture of the combustion chamber assembly and possible engine fire, do the following: (a) Replace combustion chamber assembly, P/N 4126T87G04, at or before the combustion chamber assembly accumulates 28,000 cycles-since-new (CSN). (b) After the effective date of this AD, do not install any combustion chamber assembly, P/N 4126T87G04, that exceeds 28,000 CSN. Alternative Methods of Compliance (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office (ECO). Operators must submit their request through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager,ECO. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the ECO. Effective Date (d) This amendment becomes effective on June 12, 2003.

Source: FAA Dynamic Regulatory System, airworthiness directives. The FAA's document is the authority; the register counts are this site's, from the FAA register of October 7, 2026. Connections as data: /graph/directive/2003-09-14.json · aircraft systems.