AD 2002-05-02
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | General Electric Aircraft Engines | CF34-3A1 | Airworthiness Directives; General Electric Company CF34-3A1 and - 3B1 Series Turbofan Engines |
| engine | General Electric Aircraft Engines | CF34-3B1 | Airworthiness Directives; General Electric Company CF34-3A1 and - 3B1 Series Turbofan Engines |
Unsafe Condition
Cracks in the high-pressure turbine (HPT) blade platforms can occur due to high-cycle fatigue.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Conduct inspections for cracks in the HPT blade platforms using the specified methods and replace affected blades if cracks are found.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Before further flight
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
General Electric Company CF34-3A1 and -3B1 series turbofan engines
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
This document makes a correction to Airworthiness Directive (AD) 2002-05-02, applicable to General Electric Company (GE) CF34-3A1 and -3B1 series turbofan engines. AD 2002-05-02 was published in the Federal Register on March 8, 2002 (67 FR 10606). Information in the Mandatory Inspections Requirements Table is incorrect in two places. In all other respects, the original document remains the same.
Document Text
Show stored source text (verify against official source)
[Federal Register Volume 67, Number 124 (Thursday, June 27, 2002)]
[Rules and Regulations]
[Pages 43229-43230]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-16175]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NE-49-AD; Amendment 39-12670; AD 2002-05-02]
RIN 2120-AA64
Airworthiness Directives; General Electric Company CF34-3A1 and -
3B1 Series Turbofan Engines; Correction
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; correction.
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SUMMARY: This document makes a correction to Airworthiness Directive
(AD) 2002-05-02, applicable to General Electric Company (GE) CF34-3A1
and -3B1 series turbofan engines. AD 2002-05-02 was published in the
Federal
[[Page 43230]]
Register on March 8, 2002 (67 FR 10606). Information in the Mandatory
Inspections Requirements Table is incorrect in two places. In all other
respects, the original document remains the same.
EFFECTIVE DATE: April 12, 2002.
FOR FURTHER INFORMATION CONTACT: Barbara Caufield, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (781)
238-7146; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: A final rule airworthiness directive FR DOC.
02-5527, applicable to General Electric Company (GE) CF34-3A1 and -3B1
series turbofan engines, was published in the Federal Register on March
8, 2002 (67 FR 10606). The following correction is needed:
Sec. 39.13 [Corrected]
On page 10608, in AD 2002-05-02, in Table 804 Mandatory Inspection
Requirements, in the Part nomenclature column, fourth line, ``HPT Rotor
Outer Torque Coupling (all)'' is corrected to read ``HPT Rotor Outer
Torque Coupling'' and in the eleventh line, ``Stage 3-8 Compressor
Rotor Spool (all)'', in the Mandatory inspection column for that line,
``All Areas (FPI)'' is corrected to read ``All Non-coated Areas
(FPI)''.
Issued in Burlington, MA, on June 17, 2002.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 02-16175 Filed 6-26-02; 8:45 am]
BILLING CODE 4910-13-P
Source: Official FAA Source ↗
Retrieved: Apr 6, 2026
Rights: U.S. Government Public Domain
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