AD 2004-12-08

[Federal Register Volume 69, Number 117 (Friday, June 18, 2004)]
[Rules and Regulations]
[Pages 34051-34053]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 04-13698]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 
Prices of new books are listed in the first FEDERAL REGISTER issue of each 
week.

========================================================================


Federal Register / Vol. 69, No. 117 / Friday, June 18, 2004 / Rules 
and Regulations

[[Page 34051]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-ANE-45-AD; Amendment 39-13667; AD 2004-12-08]
RIN 2120-AA64


Airworthiness Directives; International Aero Engines (IAE) AG 
V2500-A1, V2522-A5, V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, 
V2528-D5, V2530-A5, and V2533-A5 Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) for IAE AG V2500-A1, V2522-A5, V2524-A5, V2525-D5, V2527-A5, 
V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, and V2533-A5 turbofan 
engines. That AD currently requires revisions to the Airworthiness 
Limitations Section (ALS) and Maintenance Scheduling Section (MSS) of 
the Instructions for Continued Airworthiness (ICA), located in the Time 
Limits Manual (Chapter 05-10-00) of the Engine Manuals, to include 
required enhanced inspection of selected critical life-limited parts at 
each piece-part exposure. This action would add critical life-limited 
parts for enhanced inspection. This action is prompted by additional 
focused inspection procedures that have been developed by the 
manufacturer. 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: This AD becomes effective July 23, 2004.

ADDRESSES: You may examine the AD docket, by appointment, at the FAA, 
New England Region, Office of the Regional Counsel, 12 New England 
Executive Park, Burlington, MA.

FOR FURTHER INFORMATION CONTACT: James Rosa, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7152; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 2000-12-05, 
Amendment 39-11783 (65 FR 36783, June 12, 2000), which is applicable to 
IAE AG V2500-A1, V2522-A5, V2524-A5, V2525-D5, V2527-A5, V2527E-A5, 
V2527M-A5, V2528-D5, V2530-A5, and V2533-A5 turbofan engines, was 
published in the Federal Register on June 25, 2003 (68 FR 37774). That 
action proposed to revise the Airworthiness Limitations Section (ALS) 
and Maintenance Scheduling Section (MSS) of the Instructions for 
Continued Airworthiness (ICA), located in the Time Limits Manual 
(Chapter 05-10-00) of the Engine Manuals, to add critical life-limited 
parts for enhanced inspection at each piece-part exposure.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

High Pressure Compressor (HPC) Rear Airseal

    One commenter requests that the HPC rear airseal be removed from 
the list of parts requiring inspection because it is smaller and 
lighter than other parts requiring inspection and its failure is 
unlikely to cause an uncontained failure. We do not agree. Although 
failure of the HPC rear airseal is less likely to cause an uncontained 
failure than other listed parts, it has been identified as a critical 
part, the failure of which can lead to a hazardous condition.

Inspection of New Parts

    One commenter questions the need for additional non-destructive 
inspections for the new high pressure compressor (HPC) and low pressure 
turbine (LPT) parts added to this AD, as the original AD requires 
fluorescent penetrant inspection (FPI) only. We agree. FPI was the only 
intended method of inspection. The intent of this AD is to specify all 
parts and all critical features of these parts requiring inspection. 
New parts added to the mandatory inspection list by this AD will 
require the same inspections as parts listed in the original AD. The 
Compliance Section of the final rule will reflect this change.

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule as proposed. The FAA has 
determined that these changes will neither increase the economic burden 
on any operator nor increase the scope of the AD.

Economic Analysis

    The FAA estimates that 734 engines installed on airplanes of U.S. 
registry would be affected by this AD, that it would take approximately 
24 work hours per engine to perform the enhanced inspection for HPC 
stage 3-8 drums, HPC stage 9-12 drum, HPC rear shaft, HPC rear rotating 
seal, and stages 3 through 7 LPT disks. The average labor rate is $65 
per work hour. The total cost of the added inspections per engine would 
be approximately $1,560. Using average shop visitation rates, the 
annual cost of the added inspections on U.S. operators is approximately 
$1,145,040.

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) will not have a 
significant economic impact, positive or negative, on a

[[Page 34052]]

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

0
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

0
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]

0
2. Section 39.13 is amended by removing Amendment 39-11783 (65 FR 
36783, June 12, 2000) and by adding a new airworthiness directive, 
Amendment 39-13667, to read as follows:

2004-12-08 International Aero Engines: Amendment 39-13667. Docket 
No. 98-NE-45-AD. Supersedes AD 2000-12-05, Amendment 39-11783.

Applicability

    This airworthiness directive (AD) is applicable to International 
Aero Engines AG (IAE) V2500-A1, V2522-A5, V2524-A5, V2525-D5, V2527-
A5, V2527E-A5, V2527M-A5, V2528-D5, V2530-A5, and V2533-A5 turbofan 
engines. These engines are installed on, but not limited to, Airbus 
Industrie A319, A320, and A321 series, and McDonnell Douglas MD-90 
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 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 the next 90 days after the effective date of this AD, 
revise the Airworthiness Limitations Section (ALS) and Maintenance 
Scheduling Section (MSS) of the Instructions for Continued 
Airworthiness (ICA) located in the Time Limits Manual (Chapter 05-
10-00) of the Engine Manuals, part number (P/N) E-V2500-1IA and P/N 
E-V2500-3IA, and for air carrier operations revise the approved 
continuous airworthiness maintenance program, by
    (1) Adding the following to paragraph 1, entitled 
``Airworthiness Limitations:'' ``Refer to paragraph 2--Maintenance 
Scheduling for information that sets forth the operator's 
maintenance requirements for the V2500 On-Condition engine.''
    (2) Adding the following paragraph 2, entitled ``Maintenance 
Scheduling:''

``Whenever a Group A part identified in this paragraph (see 4.0 for 
definition of Group A) satisfies both of the following conditions:
    The part is considered completely disassembled when accomplished 
in accordance with the disassembly instructions in the engine 
manufacturer's 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; then that part is considered to be at the piece-part level 
and it is mandatory to perform the inspections for that part as 
specified in the following:

----------------------------------------------------------------------------------------------------------------
            Part nomenclature                  Part number  (P/N)          Inspect per engine manual chapter
----------------------------------------------------------------------------------------------------------------
Fan Disk................................  All........................  Chapter 72-31-12, Subtask 72-31-12-230-
                                                                        054.
Stage 1 HP Turbine Hub..................  All........................  Chapter 72-45-11, Task 72-45-11-200-002.
Stage 2 HP Turbine Hub..................  All........................  Chapter 72-45-31, Task 72-45-31-200-004.
High Pressure Compressor (HPC) Stage 3-8  All........................  Chapter 72-41-11, Subtask 72-41-11-230-
 Drum.                                                                  104.
HPC Stage 9-12 Drum.....................  All........................  Chapter 72-41-12, Subtask 72-41-12-230-
                                                                        079.
HPC Rear Shaft..........................  All........................  Chapter 72-41-13, Subtask 72-41-13-230-
                                                                        097 & 72-41-13-230-098.
HPC Stage Rear Rotating Seal............  All........................  Chapter 72-41-14, Subtask 72-41-14-230-
                                                                        064 & 72-41-14-230-065.
Stages 3 through 7 Low Pressure Turbine   All........................  Chapter 72-50-31, Task 72-50-31-200-006.
 (LPT) Disks.
----------------------------------------------------------------------------------------------------------------

    (b) Except as provided in paragraph (c) of this AD, and 
notwithstanding contrary provisions in section 43.16 of the Federal 
Aviation Regulations (14 CFR 43.16), these mandatory inspections 
must be performed only in accordance with the ALS and MSS of the ICA 
in the Time Limits Manual (Chapter 05-10-00) of the Engine Manuals, 
P/N E-V2500-1IA and P/N E-V2500-3IA.

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 (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 airworthiness directive, 
if any, may be obtained from the ECO.

Special Flight Permits

    (d) Special flight permits may be issued in accordance with 
Sec. Sec.  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 
record keeping requirement of Sec.  121.369(c) of the Federal 
Aviation Regulations (14 CFR 121.369(c)) of this chapter must 
maintain records of the mandatory inspections that result from 
revising the ALS and MSS of the ICA in the Time Limits Manual 
(Chapter 05-10-00) of the Engine Manuals, P/N E-V2500-1IA and P/N E-
V2500-3IA, 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

[[Page 34053]]

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 
requirements in the Engine Manuals.

Effective Date

    (f) This amendment becomes effective on July 23, 2004.

    Issued in Burlington, Massachusetts, on June 8, 2004.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 04-13698 Filed 6-17-04; 8:45 am]
BILLING CODE 4910-13-P