65 FR 57 pgs. 15536-15537 - Airworthiness Directives; General Electric Company (GE) CF34 Series Turbofan Engines; Correction
Type: RULEVolume: 65Number: 57Pages: 15536 - 15537
Docket number: [Docket No. 99-NE-49-AD; Amendment 39-11560; AD 2000-03-03]
FR document: [FR Doc. 00-6489 Filed 3-22-00; 8:45 am]
Agency: Transportation Department
Sub Agency: Federal Aviation Administration
Official PDF Version: PDF Version
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NE-49-AD; Amendment 39-11560; AD 2000-03-03]
RIN 2120-AA64
Airworthiness Directives; General Electric Company (GE) CF34 Series Turbofan Engines; Correction
AGENCY:
Federal Aviation Administration, DOT.
ACTION:
Final rule; correction.
SUMMARY:
This document makes a correction to AirworthinessDirective (AD) 2000-03-03 that is applicable to certainGeneral Electric Company CF34 series turbofan engines that was published in the Federal Register on February 7, 2000(65 FR 5759). Two subpart names and two mandatory inspections were inadvertently omitted from the Mandatory Inspection Requirements of Table 804. This document corrects this Table by adding the subparts and inspections.
EFFECTIVE DATE:
March 23, 2000.
FOR FURTHER INFORMATION CONTACT:
Kevin Donovan, AerospaceEngineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-7743, fax (781) 238-7199.
SUPPLEMENTARY INFORMATION:
A final rule airworthiness directive applicable to General Electric Company CF34 series turbofan engines, was published in the Federal Register on February 7, 2000 (65 FR 5759). In the compliance section, an omission was made in Table 804 of the Mandatory Inspection Requirements. This correction adds necessary subpart names and inspections to the mandatory inspection requirements:
§ 39.13 [Corrected]
1. On page 5760, in AD 2000-03-03, table 804 is corrected to read as follows:
| Part name/part No. | Chapter/section subject | Mandatory inspection |
|---|---|---|
| Fan Disk (all) | 72-21-00, INSPECTION | All Areas (FPI)1 Bores (ECI)2 |
| Stage 1 HPT Rotor Disk (all) | 72-46-00, INSPECTION | All Areas (FPI)1 Bores (ECI)2 Boltholes (ECI)2 Air Holes (ECI)2 |
| Stage 2 HPT Rotor Disk (all) | 72-46-00, INSPECTION | All Areas (FPI)1 Bores (ECI)2 |
| (a) Boltless Rim Configuration | Boltholes (FPI)1 Air Holes (FPI)1 | |
| (b) Bolted Rim Configuration | Boltholes (ECI)2 Air Holes (ECI)2 | |
| HPT Rotor Outer Torque | 72-46-00, INSPECTION | All Areas (FPI)1 |
| Coupling (all) | Bores (ECI)2 | |
| 1 FPI = Fluorescent Penetrant Inspection Method. | ||
| 2 ECI = Eddy Current Inspection Method. | ||
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service.
[FR Doc. 00-6489 Filed 3-22-00; 8:45 am]
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