[Federal Register Volume 70, Number 53 (Monday, March 21, 2005)]
[Rules and Regulations]
[Pages 13365-13368]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-5299]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NE-41-AD; Amendment 39-14015; AD 2005-06-07]
RIN 2120-AA64


Airworthiness Directives; General Electric Company (GE) CF6-80A1/
A3 and CF6-80C2A Series Turbofan Engines, Installed on Airbus Industrie 
A300-600 and A310 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) for GE CF6-80A1/A3 and CF6-80C2A series turbofan engines. That AD 
currently requires completing one of the following actions before 
further flight:

[[Page 13366]]

     Performing a directional pilot valve (DPV) pressure check 
for leakage, and, if necessary, replacing the DPV assembly with a 
serviceable assembly, or
     Replacing the DPV assembly with a serviceable assembly, or
     Deactivating the thrust reverser, and revising the FAA-
approved airplane flight manual (AFM) to require applying performance 
penalties for certain takeoff conditions if a thrust reverser is 
deactivated.
    That AD also requires revising the Emergency Procedures Section of 
the FAA-approved AFM to include a flight crew operational procedure for 
use in the event of any indication of an in-flight thrust reverser 
deployment.
    This AD specifies the same requirements for leak checks, but 
increases the interval between required checks. This AD also removes 
the requirement to revise the Limitations Section and the Emergency 
Procedures Section of the applicable AFM when deactivating one or both 
thrust reversers. This AD results from Airbus Industrie, the airplane 
manufacturer, revising the master minimum equipment list (MMEL) to 
include procedures for operating the airplane with the thrust reversers 
deactivated, and revising the AFM to include procedures for emergency 
operation if the thrust reversers deploy while in flight. This AD also 
results from the engine manufacturer recommending extending the 
interval between inspecting or replacing the DPV. We are issuing this 
AD to prevent inadvertent thrust reverser deployment, which, if it 
occurs in-flight, could result in loss of control of the airplane.

DATES: This AD becomes effective April 25, 2005. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of April 25, 2005.

ADDRESSES: You can get the service information identified in this AD 
from Middle River Aircraft Systems, Mail Point 46, 103 Chesapeake Park 
Plaza, Baltimore, MD 21220, Attn: Product Support Engineering; 
telephone (410) 682-0098, fax (410) 682-0100.
    You may examine the AD docket at the FAA, New England Region, 
Office of the Regional Counsel, 12 New England Executive Park, 
Burlington, MA.

FOR FURTHER INFORMATION CONTACT: Karen Curtis, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone (781) 
238-7192; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to GE CF6-80A1/A3 and CF6-
80C2A series turbofan engines. We published the proposed AD in the 
Federal Register on July 29, 2004 (69 FR 45295). That action proposed 
the same requirements for leak checks as the AD being superseded, AD 
99-18-19, Amendment 39-11285 (64 FR 48277, September 23, 1999), but 
would increase the interval between required checks.

Examining the AD Docket

    You may examine the AD Docket (including any comments and service 
information), by appointment, between 8 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. See ADDRESSES for the 
location.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments received.

Request That the AD Be Closed

    One commenter requests that the AD be closed instead of superseded. 
The commenter states his airplanes have never experienced a leaky DPV.
    We do not agree. Although the operator has not yet experienced any 
leaks, the possibility still exists that a DPV leak may occur. This 
type of leak is a hidden failure that cannot be detected at the system 
level, and could result in inadvertent thrust reverser deployment, 
which, if it occurs in-flight, could result in loss of control of the 
airplane. This superseding AD reflects the favorable inspection 
results, by extending the inspection interval.

Request To Address Alternative Methods of Compliance (AMOCs)

    One commenter requests that any AMOCs issued under AD 99-18-19 be 
addressed in the superseding AD. The commenter states that it would be 
beneficial if operators did not have to submit new AMOC requests for 
deviations or changes previously approved by the FAA under AD 99-18-19.
    We agree that any known AMOCs should be addressed in this 
superseding AD. The two known AMOCs issued under AD 99-18-19, however, 
are no longer necessary under the superseding AD. Any AMOCs that may 
have been overlooked and are not made obsolete by this superseding AD 
should be brought to the attention of the FAA Engine Certification 
Office.

Request for Increased Inspection Interval

    One commenter requests that an increased inspection interval for 
engines configured with the Third Line of Defense (TLOD) system be 
included in this superseding AD. The commenter cites service bulletins 
issued by Airbus, and an AD issued by the Direction Generale de 
L'Aviation Civile (DGAC), the airworthiness authority for France, as 
substantiation for the interval increase. The commenter acknowledges 
that the DGAC AD does not affect U.S. registered airplanes.
    We do not agree. The FAA Engine Certification Office has not yet 
approved the increased interval for engines configured with the TLOD 
system. The DGAC AD referenced by the commenter, AD 1999-242-289 R1, 
dated July 7, 2004, was subsequently cancelled by the European Aviation 
Safety Agency (EASA) with the issuance of AD 1999-242-289 R2. This 
cancellation notice stated that AD 1999-242-289 R1 was replaced by FAA 
AD 99-18-19, as noted on EASA cover document 2002-362-IMP.

Request To Clarify the Reason for Issuing a Superseding AD

    In the proposed AD, we stated that the proposed AD ``results from 
revisions to the manufacturer's alert service bulletins''. We received 
an internal request to clarify the reason for the superseding AD. For 
clarification, we have changed the final rule to state:
    ``This AD results from Airbus Industrie, the airplane manufacturer, 
revising the master minimum equipment list (MMEL) to include procedures 
for operating the airplane with the thrust reversers deactivated, and 
revising the AFM to include procedures for emergency operation if the 
thrust reversers deploy while in flight. This AD also results from the 
engine manufacturer recommending extending the interval between 
inspecting or replacing the DPV.''

Conclusion

    We have carefully reviewed the available data, including the 
comments received, and determined that air safety and the public 
interest require adopting the AD with the changes described previously. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    There are about 544 engines of the affected design in the worldwide 
fleet. We estimate that 192 engines installed on airplanes of U.S. 
registry will be

[[Page 13367]]

affected by this AD. We also estimate that it will take about 1 work 
hour per engine to perform the actions (about 227 per year), and that 
the average labor rate is $65 per work hour. Required parts will cost 
about $12,000 per engine. We estimate that operators will replace 9 
percent of the existing DPVs. Based on these figures, we estimate the 
total cost of the AD to U.S. operators to be $259,915.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will 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.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under 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 substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary by 
sending a request to us at the address listed under ADDRESSES. Include 
``AD Docket No. 99-NE-41-AD'' in your request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends 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. The FAA amends Sec.  39.13 by removing Amendment 39-11285 (64 FR 
48277, September 23, 1999) and by adding a new airworthiness directive, 
Amendment 39-14015, to read as follows:

2005-06-07 General Electric Company: Amendment 39-14015. Docket No. 
99-NE-41-AD.

Effective Date

    (a) This AD becomes effective April 25, 2005.

Affected ADs

    (b) This AD supersedes AD 99-18-19, Amendment 39-11285.
    Applicability: (c) This AD applies to General Electric Company 
(GE) CF6-80A1/A3 and CF6-80C2A series turbofan engines. These 
engines are installed on, but not limited to, Airbus Industrie A300-
600 and A310 series airplanes.

Unsafe Condition

    (d) This AD results from Airbus Industrie, the airplane 
manufacturer, revising the master minimum equipment list (MMEL) to 
include procedures for operating the airplane with the thrust 
reversers deactivated, and revising the Airplane Flight Manual (AFM) 
to include procedures for emergency operation if the thrust 
reversers deploy while in flight. This AD also results from the 
engine manufacturer recommending extending the interval between 
inspecting or replacing the directional pilot valve (DPV). We are 
issuing this AD to prevent inadvertent thrust reverser deployment, 
which, if it occurs in-flight, could result in loss of control of 
the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Credit for Initial Actions

    (f) Performing the initial actions using Middle River Aircraft 
Systems (MRAS) Alert Service Bulletin (ASB) No. CF6-80A1/A3 SB 
78A4022, Revision 2, dated September 17, 2003, or earlier revision 
or MRAS ASB No. CF6-80C2A SB 78A1081, Revision 2, dated September 
17, 2003, or earlier revision, satisfies the requirements of 
paragraphs (g) and (i) of this AD.

GE CF6-80A1/A3 Series Engines Initial Actions

    (g) For GE CF6-80A1/A3 series engines, do either paragraph 
(g)(1) or (g)(2) of this AD.
    (1) Before further flight, perform a pressure check of the DPV 
for leakage. Use 2.B.(1) through 2.B.(12) of the Accomplishment 
Instructions of MRAS ASB No. CF6-80A1/A3 SB 78A4022, Revision 2, 
dated September 17, 2003, and if necessary, do either of the 
following:
    (i) Replace the DPV assembly with a serviceable assembly and 
perform an operational check of the thrust reverser. Use 2.C.(1) 
through 2.C.(7) of the Accomplishment Instructions of MRAS ASB No. 
CF6-80A1/A3 SB 78A4022, Revision 2, dated September 17, 2003, or
    (ii) Deactivate the thrust reverser and do the following:
    (A) Replace the DPV with a serviceable DPV within 10 calendar 
days.
    (B) Perform an operational check of the thrust reverser. Use 
2.C.(1) through 2.C.(7) of the Accomplishment Instructions of MRAS 
ASB No. CF6-80A1/A3 SB 78A4022, Revision 2, dated September 17, 
2003.
    (2) Before further flight, replace the DPV assembly with a 
serviceable assembly, and perform an operational check of the thrust 
reverser. Use 2.C.(1) through 2.C.(7) of the Accomplishment 
Instructions of MRAS ASB No. CF6-80A1/A3 SB 78A4022, Revision 2, 
dated September 17, 2003.

GE CF6-80A1/A3 Series Engines Repetitive Actions

    (h) For GE CF6-80A1/A3 series engines, do either paragraph 
(h)(1) or (h)(2) of this AD within 1,400 hours time-in-service (TIS) 
since the last action.
    (1) Perform a pressure check of the DPV for leakage. Use 2.B.(1) 
through 2.B.(12) of the Accomplishment Instructions of MRAS ASB No. 
CF6-80A1/A3 SB 78A4022, Revision 2, dated September 17, 2003, and if 
necessary, do either of the following:
    (i) Replace the DPV assembly with a serviceable assembly and 
perform an operational check of the thrust reverser. Use 2.C.(1) 
through 2.C.(7) of the Accomplishment Instructions of MRAS ASB No. 
CF6-80A1/A3 SB 78A4022, Revision 2, dated September 17, 2003, or
    (ii) Deactivate the thrust reverser and do the following:
    (A) Replace the DPV with a serviceable DPV within 10 calendar 
days.
    (B) Perform an operational check of the thrust reverser. Use 
2.C.(1) through 2.C.(7) of the Accomplishment Instructions of MRAS 
ASB No. CF6-80A1/A3 SB 78A4022, Revision 2, dated September 17, 
2003.
    (2) Replace the DPV assembly with a serviceable assembly, and 
perform an operational check of the thrust reverser. Use 2.C.(1) 
through 2.C.(7) of the Accomplishment Instructions of MRAS ASB No. 
CF6-80A1/A3 SB 78A4022, Revision 2, dated September 17, 2003.

[[Page 13368]]

GE CF6-80C2A Series Engines Initial Actions

    (i) For GE CF6-80C2A series engines, do either paragraph (i)(1) 
or (i)(2) of this AD.
    (1) Before further flight, perform a pressure check of the DPV 
for leakage. Use 2.B.(1) through 2.B.(12) of the Accomplishment 
Instructions of MRAS ASB No. CF6-80C2A SB 78A1081, Revision 2, dated 
September 17, 2003, and if necessary, do either of the following:
    (i) Replace the DPV assembly with a serviceable assembly and 
perform an operational check of the thrust reverser. Use 2.C.(1) 
through 2.C.(5) of the Accomplishment Instructions of MRAS ASB No. 
CF6-80C2A SB 78A1081, Revision 2, dated September 17, 2003, or
    (ii) Deactivate the thrust reverser and do the following:
    (A) Replace the DPV with a serviceable DPV within 10 calendar 
days.
    (B) Perform an operational check of the thrust reverser. Use 
2.C.(1) through 2.C.(5) of the Accomplishment Instructions of MRAS 
ASB No. CF6-80C2A SB 78A1081, Revision 2, dated September 17, 2003.
    (2) Before further flight, replace the DPV assembly with a 
serviceable assembly, and perform an operational check of the thrust 
reverser. Use 2.C.(1) through 2.C.(5) of the Accomplishment 
Instructions of MRAS ASB No. CF6-80C2A SB 78A4022, Revision 2, dated 
September 17, 2003.

GE CF6-80C2A Series Engines Repetitive Actions

    (j) For GE CF6-80C2A series engines, do either (j)(1) or (j)(2) 
of this AD within 1,400 hours TIS since the last action.
    (1) Perform a pressure check of the DPV for leakage. Use 2.B.(1) 
through 2.B.(12) of the Accomplishment Instructions of MRAS ASB No. 
CF6-80C2A SB 78A1081, Revision 2, dated September 17, 2003, and if 
necessary, do either of the following:
    (i) Replace the DPV assembly with a serviceable assembly and 
perform an operational check of the thrust reverser. Use 2.C.(1) 
through 2.C.(5) of the Accomplishment Instructions of MRAS ASB No. 
CF6-80C2A SB 78A1081, Revision 2, dated September 17, 2003, or
    (ii) Deactivate the thrust reverser and do the following:
    (A) Replace the DPV with a serviceable DPV within 10 calendar 
days.
    (B) Perform an operational check of the thrust reverser. Use 
2.C.(1) through 2.C.(5) of the Accomplishment Instructions of MRAS 
ASB No. CF6-80C2A SB 78A1081, Revision 2, dated September 17, 2003.
    (2) Replace the DPV assembly with a serviceable assembly, and 
perform an operational check of the thrust reverser. Use 2.C.(1) 
through 2.C.(5) of the Accomplishment Instructions of MRAS ASB No. 
CF6-80C2A SB 78A1081, Revision 2, dated September 17, 2003.

Definition of Serviceable DPV Assembly

    (k) For the purpose of this AD, a serviceable DPV assembly is:
    (1) An assembly that has accumulated zero time in service, or
    (2) An assembly that has accumulated zero time in service after 
having passed the tests in the MRAS Component Maintenance Manual GEK 
85007 (78-31-51), Revision No. 6 or later, Directional Pilot Valve, 
Page Block 101, Testing and Troubleshooting, or
    (3) An assembly that has been successfully leak checked using 
Paragraph 2.B. of the Accomplishment Instructions of MRAS ASB No. 
78A4022, Revision 2, dated September 17, 2003, or earlier revision, 
or ASB No. 78A1081, Revision 2, dated September 17, 2003, or earlier 
revision, as applicable, immediately before installation on the 
airplane.

Alternative Methods of Compliance

    (l) The Manager, Engine Certification Office, has the authority 
to approve alternative methods of compliance for this AD, if 
requested, using the procedures found in 14 CFR 39.19.

Material Incorporated by Reference

    (m) You must use the Middle River Aircraft Systems (MRAS) Alert 
Service Bulletins (ASB) listed in Table 1 of this AD to perform the 
actions required by this AD. The Director of the Federal Register 
approved the incorporation by reference of the documents listed in 
Table 1 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. You can get a copy from Middle River Aircraft Systems, Mail 
Point 46, 103 Chesapeake Park Plaza, Baltimore, MD 21220, Attn: 
Product Support Engineering; telephone (410) 682-0098, fax (410) 
682-0100. You can review copies at the FAA, New England Region, 
Office of the Regional Counsel, 12 New England Executive Park, 
Burlington, MA; or at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
    Table 1 follows:

                                      Table 1.--Incorporation by Reference
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                                                                       Revision
 Middle River Aircraft Systems ASB                                      level
                No.                 Page number(s) shown on the page   shown on       Date shown on the page
                                                                       the page
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78A4022, Total pages: 18..........  ALL.............................          2  September 17, 2003.
78A1081, Total pages: 18..........  ALL.............................          2  September 17, 2003.
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Related Information

    (n) None.

    Issued in Burlington, Massachusetts, on March 9, 2005.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 05-5299 Filed 3-18-05; 8:45 am]
BILLING CODE 4910-13-P