Airworthiness Directives; General Electric Company CF34-3A1 and -3B1 Series Turbofan Engines

[Federal Register Volume 67, Number 46 (Friday, March 8, 2002)]
[Rules and Regulations]
[Pages 10606-10608]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-5527]


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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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), that is applicable to General Electric Company (GE) CF34-3A1 and 
-3B1 series turbofan engines, that currently requires revisions to the 
Engine Maintenance Program specified in the manufacturer's Instructions 
for Continued Airworthiness (ICA) for GE CF34-3A1 and -3B1 series 
turbofan engines. Those revisions require enhanced inspection of 
selected critical life-limited parts at each piece-part exposure. The 
existing AD also requires that an air carrier's approved continuous 
airworthiness maintenance program incorporate these inspection 
procedures. This amendment modifies the airworthiness limitations 
section of the manufacturer's manual and an air carrier's approved 
continuous airworthiness maintenance program to incorporate additional 
inspection requirements. An FAA study of in-service events involving 
uncontained failures of critical rotating engine parts has indicated 
the need for mandatory inspections. The mandatory inspections are 
needed to identify those critical rotating parts with conditions, which 
if allowed to continue in service, could result in uncontained 
failures. The actions specified by this AD are intended to prevent 
critical life-limited rotating engine part failure, which could result 
in an uncontained engine failure and damage to the airplane.

DATES: Effective date April 12, 2002.

ADDRESSES: The information referenced in this AD may be examined, by 
appointment, at the Federal Aviation Administration (FAA), New England 
Region, Office of the Regional Counsel, 12 New England Executive Park, 
Burlington, MA.

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.

[[Page 10607]]


SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 2000-03-03 R1, 
Amendment 39-12228 (66 FR 26787, May 15, 2001), which is applicable to 
General Electric Company CF34-3A1 and -3B1 series turbofan engines was 
published in the Federal Register on October 5, 2001 (66 FR 50891). 
That action proposed to modifiy the airworthiness limitations section 
of the manufacturer's manual and an air carrier's approved continuous 
airworthiness maintenance program to incorporate additional inspection 
requirements.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. No comments were received on the 
proposal or the FAA's determination of the cost to the public. The FAA 
has determined that air safety and the public interest require the 
adoption of the rule as proposed.

Regulatory Analysis

    This final rule does not have federalism implications, as defined 
in Executive Order 13132, because it would not have a substantial 
direct effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government. Accordingly, 
the FAA has not consulted with state authorities prior to publication 
of this final rule.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under the DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) if promulgated, 
will not have a significant economic impact, positive or negative, on a 
substantial number of small entities under the criteria of the 
Regulatory Flexibility Act. A final evaluation has been prepared for 
this action and it is contained in the Rules Docket. A copy of it may 
be obtained by contacting the Rules Docket at the location provided 
under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing Amendment 39-12228 (66 FR 
26787, May 15, 2001) and by adding a new airworthiness directive, 
Amendment 39-12670, to read as follows:

2002-05-02  General Electric Company: Amendment 39-12670. Docket No. 
99-NE-49-AD. Supersedes AD 2000-03-03 R1, Amendment 39-12228.

Applicability

    This airworthiness directive (AD) is applicable to General 
Electric Company (GE) CF34-3A1 and -3B1 series turbofan engines, 
installed on but not limited to Bombardier Canadair CL 600-2B19(RJ) 
aircraft.

    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 critical life-limited rotating engine part failure, 
which could result in an uncontained engine failure and damage to 
the airplane, do the following:

Inspections

    (a) Within 30 days after the effective date of this AD, revise 
the CF34 Engine Maintenance Program, Chapter 5-21-00, of the GE 
CF34-3A1 and -3B1 Series Turbofan Engine Manual, SEI-756. For air 
carrier operations, revise the approved continuous airworthiness 
maintenance program, by adding the following:
    ``9. CF34-3A1 and CF34-3B1 Engine Maintenance Program--Mandatory 
Inspection Requirements.
    (A) This procedure is used to identify specific piece-parts that 
require mandatory inspections that must be accomplished at each 
piece-part exposure using the applicable Chapters referenced in 
Table 804 for the inspection requirements. The inspection 
requirements listed in Table 804 are not required for any piece-part 
exposure resulting when the engine remains on-wing while performing 
maintenance practice, special procedure Number 41 listed in SEI-756, 
chapter 72-00-00.
    (B) Piece-part exposure is defined as follows: Note: Fan disk 
piece-part includes the fan disk with the 56 fan pin bushings 
installed.
    (1) For engines that utilize the ``On Condition'' maintenance 
requirements:
    The part is considered completely disassembled to the piece-part 
level when done in accordance with the disassembly instructions in 
the GEAE authorized overhaul Engine Manual, and the part has 
accumulated more than 100 cycles-in-service since the last piece-
part opportunity inspection, provided that the part was not damaged 
or related to the cause for its removal from the engine.
    (2) For engines that utilize the ``Hard Time'' maintenance 
requirements:
    The part is considered completely disassembled when done in 
accordance with the disassembly instructions used in the ``Minor 
Maintenance'' or ``Overhaul'' instructions in the GEAE engine 
authorized Engine Manual, and the part has accumulated more than 100 
cycles-in-service since the last piece-part opportunity inspection, 
provided that the part was not damaged or related to the cause for 
its removal from the engine.
    C. Refer to Table 804 below for the mandatory inspection 
requirements.

              Table 804.--Mandatory Inspection Requirements
------------------------------------------------------------------------
                                     Manual/chapter        Mandatory
        Part nomenclature            section/subject       inspection
------------------------------------------------------------------------
Fan Disk (all)...................  72-21-00,           All areas (FPI)
                                    INSPECTION.        Bores (ECI)
Stage 1 high pressure turbine      72-46-00,           All areas (FPI)
 (HPT) Rotor Disk (all).            INSPECTION.        Bores (ECI)
                                                       Boltholes (ECI)
                                                       Air Holes (ECI)

[[Page 10608]]

 
Stage 2 HPT Rotor Disk (all).....  72-46-00,           All areas (FPI)
                                    INSPECTION.        Bores (ECI)
(a) Boltless Rim Configuration...  ..................  Boltholes (FPI)
                                                       Air Holes (FPI)
(b) Bolted Rim Configuration.....  ..................  Boltholes (ECI)
                                                       Air Holes (ECI)
HPT Rotor Outer Torque Coupling    72-46-00,           All areas (FPI)
 (all).                             INSPECTION.        Bore (ECI)
Forward Fan Shaft (all)..........  72-21-00,           All areas (FPI)
                                    INSPECTION.
Fan Drive Shaft (all)............  72-22-00,           All areas (FPI)
                                    INSPECTION.
Stage 1 Compressor; Rotor Disk     72-33-00,           All areas (FPI)
 (CF34-3A1) or; Stage 1             INSPECTION.
 Compressor Rotor; Blisk (CF34-
 3B1) (all).
Compressor Forward Shaft (all)...  72-33-00,           All areas (FPI)
                                    INSPECTION.
Stage 2 Compressor Rotor Disk      72-33-00,           All areas (FPI)
 (all).                             INSPECTION.
Stage 3-8 Compressor Rotor Spool   72-33-00,           All areas (FPI)
 (all).                             INSPECTION.
Stage 9 Compressor Rotor Disk      72-33-00,           All areas (FPI)
 (all).                             INSPECTION.
Compressor Rotor Rear Shaft (all)  72-33-00,           All areas (FPI)
                                    INSPECTION.
Compressor Discharge Rotating      72-33-00,           All non-coated
 Seal (all).                        INSPECTION.         Areas (FPI)
Stage 10-14 Compressor Areas       72-33-00,           All non-coated
 Rotor Spool (all).                 INSPECTION.         (FPI)
Turbine Rear Shaft (LPT Rotor)     72-53-00,           All areas (FPI)
 (all).                             INSPECTION.
Stage 3 Turbine Disk (all).......  72-53-00,           All areas (FPI)
                                    INSPECTION.
Stage 4 Turbine Disk (all).......  72-53-00,           All areas (FPI)
                                    INSPECTION.
Stage 5 Turbine Disk (all).......  72-53-00,           All areas (FPI)
                                    INSPECTION.
Stage 6 Turbine Disk (all).......  72-53-00,           All areas (FPI)
                                    INSPECTION.
Turbine Driver Cone (all)........  72-53-00,           All areas (FPI)
                                    INSPECTION.
------------------------------------------------------------------------
FPI = Fluorescent Penetrant Inspection Method
ECI = Eddy Current Inspection''

    (b) Except as provided in paragraph (c) of this AD, and 
notwithstanding the provisions of section 43.16 of the Federal 
Aviation Regulations (14 CFR 43.16), these mandatory inspections 
shall be performed only in accordance with the CF34 Engine 
Maintenance Program, Chapter 5-21-00, of the General Electric 
Company, CF34-3A1 and -3B1 Series Turbofan Engine Manual, SEI-756.

Alternative Method 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 requests through an appropriate FAA 
Principal Maintenance Inspector (PMI), 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 AD, if any, may be 
obtained from the ECO.

Special Flight Permits

    (d) Special flight permits may be issued in accordance with 
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 
21.197 and 21.199) to operate the airplane to a location where the 
requirements of this AD can be done.

Continuous Airworthiness Maintenance Program

    (e) FAA-certificated air carriers that have an approved 
continuous airworthiness maintenance program in accordance with the 
recordkeeping requirement of Sec. 121.369(c) of the Federal Aviation 
Regulations (14 CFR 121.369(c)) must maintain records of the 
mandatory inspections that result from revising the CF34 Engine 
Maintenance Program and the air carrier's continuous airworthiness 
program. Alternatively, certificated air carriers may establish an 
approved system of record retention that provides a method for 
preservation and retrieval of the maintenance records that include 
the inspections resulting from this AD, and include the policy and 
procedures for implementing this alternate method in the air 
carrier's maintenance manual required by Sec. 121.369(c) of the 
Federal Aviation Regulations (14 CFR 121.369(c)); however, the 
alternate system must be accepted by the appropriate PMI and require 
the maintenance records be maintained either indefinitely or until 
the work is repeated. Records of the piece-part inspections are not 
required under Sec. 121.380(a)(2)(vi) of the Federal Aviation 
Regulations (14 CFR 121.380(a)(2)(vi)). All other operators must 
maintain the records of mandatory inspections required by the 
applicable regulations governing their operations.

    Note 3: The requirements of this AD have been met when the 
engine manual changes are made and air carriers have modified their 
continuous airworthiness maintenance plans to reflect the Engine 
Maintenance Program requirements specified in the GE CF34-3A1 and -
3B1 Series Turbofan Engine Manual.

Effective Date

    (f) This amendment becomes effective on April 12, 2002.

    Issued in Burlington, Massachusetts, on February 27, 2002.
Mark C. Fulmer,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 02-5527 Filed 3-7-02; 8:45 am]
BILLING CODE 4910-13-P

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