Airworthiness Directives; General Electric Company CF6-50, -80A1/A3, and -80C2A Series Turbofan Engines, 60604-60606 [E7-21000]

Agencies

• Federal Aviation Administration
• DEPARTMENT OF TRANSPORTATION

[Federal Register Volume 72, Number 206 (Thursday, October 25, 2007)]
[Proposed Rules]
[Pages 60604-60606]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-21000]



[[Page 60604]]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0053; Directorate Identifier 98-ANE-54-AD]
RIN 2120-AA64


Airworthiness Directives; General Electric Company CF6-50, -80A1/
A3, and -80C2A Series Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) for General Electric Company (GE) CF6-50, -80A1/A3, and 
-80C2A series turbofan engines, installed on Airbus A300 and A310 
series airplanes. That AD currently requires initial and repetitive 
inspections and checks of the thrust reverser actuation systems. This 
proposed AD would require revised inspection thresholds and intervals, 
and would require the same actions and additional inspections of the 
thrust reverser actuation system locking features. This proposed AD 
results from refined safety analyses performed on the thrust reverser 
systems by GE and Airbus. We are proposing this AD to prevent 
inadvertent in-flight thrust reverser deployment, which can result in 
loss of control of the airplane.

DATES: We must receive any comments on this proposed AD by December 24, 
2007.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD.
     Federal eRulemaking Portal: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility: U.S. Department of 
Transportation, 1200 New Jersey Avenue, SE., West Building Ground 
Floor, Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: (202) 493-2251.
    Contact Middle River Aircraft Systems, Mail Point 46, 103 
Chesapeake Park Plaza, Baltimore, MD, 21220, attn: Warranty Support, 
telephone: (410) 682-0094, fax: (410) 682-0100 for the service 
information identified in this proposed AD.

FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
Robert.green@faa.gov; telephone (781) 238-7754; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-0053; 
Directorate Identifier 98-ANE-54-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact 
with FAA personnel concerning this proposed AD.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (800) 647-5527) is 
the same as the Mail address provided in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

Discussion

    The FAA proposes to amend 14 CFR part 39 by superseding AD 99-18-
20, Amendment 39-11286 (64 FR 48286, September 3, 1999). That AD 
requires initial and repetitive inspections and checks of the thrust 
reverser actuation systems, and allows extended repetitive inspection 
intervals if an optional double p-seal configuration is installed. That 
AD was the result of a report of a higher than anticipated center drive 
unit cone brake failure rate, which reduces the overall thrust reverser 
system protection against inadvertent deployment. That condition, if 
not corrected, could result in inadvertent in-flight thrust reverser 
deployment, which can result in loss of control of the airplane.

Actions Since AD 99-18-20 Was Issued

    Since AD 99-18-20 was issued, refined safety analyses performed on 
the thrust reverser systems installed on GE CF6-50, -80A1/A3, and -
80C2A series turbofan engines were completed by GE and Airbus.

Relevant Service Information

    We have reviewed and approved the technical contents of Middle 
River Aircraft Systems (MRAS) Alert Service Bulletin (ASB) No. CF6-50 
S/B 78A3001, Revision 4, dated August 30, 2007, ASB No. CF6-80A1/A3 S/B 
78A1002, Revision 5, dated July 19, 2007, and ASB No. CF6-80C2A1/A2/A3/
A5/A8/A5F S/B 78A1015, Revision 7, dated August 30, 2007. These ASBs 
describe procedures for performing initial and repetitive thrust 
reverser system inspections and checks.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other products 
of this same type design. For that reason, we are proposing this AD, 
which would require revised inspection thresholds and intervals, and 
would require inspections of the thrust reverser actuation system 
locking features. The proposed AD would require that you do these 
actions using the relevant service information described previously.

Costs of Compliance

    We estimate that this proposed AD would affect 206 engines 
installed on airplanes of U.S. registry. We also estimate that it would 
take about one work-hour per engine to perform the proposed additional 
inspection, and that the average labor rate is $80 per work-hour. Based 
on these figures, we estimate the total additional cost of the proposed 
AD for one inspection of the U.S. fleet, to be $28,000.

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

[[Page 60605]]

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.

Docket Number Change

    We are transferring the docket for this proposed AD to the Federal 
Docket Management System (FDMS) as part of our on-going docket 
management consolidation efforts. The new Docket No. is FAA-2007-0053. 
The old Docket No. became the Directorate Identifier, which is 98-ANE-
54-AD.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD 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.
    For the reasons discussed above, I certify that the proposed AD:
    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. Would 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 regulatory evaluation of the estimated costs to 
comply with this proposed AD. See the ADDRESSES section for a location 
to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Under the authority delegated to me by the Administrator, the 
Federal Aviation Administration proposes to amend 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. The FAA amends Sec.  39.13 by removing Amendment 39-11286 (64 FR 
48286, September 3, 1999) and by adding a new airworthiness directive 
to read as follows:

General Electric Company: Docket No. FAA-2007-0053; Directorate 
Identifier 98-ANE-54-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by December 24, 
2007.

Affected ADs

    (b) This AD supersedes AD 99-18-20, Amendment 39-11286.

Applicability

    (c) This AD applies to General Electric Company (GE) CF6-50, -
80A1/A3, and -80C2A series turbofan engines. These engines are 
installed on Airbus A300 and A310 series airplanes.

Unsafe Condition

    (d) This AD results from refined safety analyses performed on 
the thrust reverser systems by GE and Airbus. We are issuing this AD 
to prevent inadvertent in-flight thrust reverser deployment, which 
can 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.

Initial Inspection for CF6-50 Series Turbofan Engines

    (f) For CF6-50 series turbofan engines, perform initial thrust 
reverser inspections using Section 2, Accomplishment Instructions, 
of Middle River Aircraft Systems (MRAS) Alert Service Bulletin (ASB) 
No. CF6-50 S/B 78A-3001, Revision 4, dated August 30, 2007, as 
follows:
    (1) On Airbus A300 series airplanes with a Three Light Reverser 
Indication Circuit configuration, and without thrust reverser 
actuation system (TRAS) locks installed, perform the initial 
inspections and checks within 1,500 hours time-in-service (TIS) 
after the effective date of this AD.
    (2) On Airbus A300 series airplanes with a Three Light Reverser 
Indication Circuit configuration, and with TRAS locks installed, 
perform the initial inspections and checks within 7,000 hours TIS 
after the effective date of this AD.
    (3) On Airbus A300 series airplanes with a Two Light Reverser 
Indication Circuit configuration, and without TRAS locks installed, 
perform the initial inspections and checks within 1,500 hours TIS 
after the effective date of this AD.
    (4) On Airbus A300 series airplanes with a Two Light Reverser 
Indication Circuit configuration, and with TRAS locks installed, 
perform the initial inspections and checks within 7,000 hours TIS 
after the effective date of this AD.

Repetitive Inspections for CF6-50 Series Turbofan Engines

    (g) For CF6-50 series turbofan engines, perform repetitive 
thrust reverser inspections using Section 2, Accomplishment 
Instructions, of MRAS ASB No. CF6-50 S/B 78A-3001, Revision 4, dated 
August 30, 2007, as follows:
    (1) On Airbus A300 series airplanes with a Three Light Reverser 
Indication Circuit configuration, and without TRAS locks installed, 
perform repetitive inspections and checks at the following:
    (i) Within every 2,500 hours time-since-last-inspection (TSLI), 
perform paragraph 2.D., Translating Cowl Air Seal, Dagmar Fairing 
and Aft Frame Inspection; and paragraph 2.I., Fan Reverser 
Operational Check.
    (ii) Within every 6,000 hours TSLI, perform paragraph 2.C., 
Pneumatic Drive Motor (PDM) Disc Brake Holding Torque Check; 
paragraph 2.E., Feedback Rod to Yoke Alignment Check and Inspection 
of Feedback Yoke and Feedback Rod; paragraph 2.F., Translating Cowl 
Auto Re-Stow Function Check; and paragraph 2.I., Fan Reverser 
Operational Check.
    (2) Within every 7,000 hours TSLI on Airbus A300 series 
airplanes with a Three Light Reverser Indication Circuit 
configuration, and with TRAS locks installed, perform repetitive 
inspections and checks.
    (3) On Airbus A300 series airplanes with a Two Light Reverser 
Indication Circuit configuration, and without TRAS locks installed, 
perform repetitive inspections and checks at the following:
    (i) Within every 2,500 hours TSLI, perform paragraph 2.D., 
Translating Cowl Air Seal, Dagmar Fairing and Aft Frame Inspection; 
and paragraph 2.I., Fan Reverser Operational Check.
    (ii) Within every 6,000 hours TSLI, perform paragraph 2.C., 
Pneumatic Drive Motor (PDM) Disc Brake Holding Torque Check; 
paragraph 2.E., Feedback Rod to Yoke Alignment Check and Inspection 
of Feedback Yoke and Feedback Rod; paragraph 2.G., Translating Cowl 
Auto Re-Stow Function Check; paragraph 2.H., Over Pressure Shutoff 
Valve (OPSOV) Indication Check; and paragraph 2.I., Fan Reverser 
Operational Check.
    (4) On Airbus A300 series airplanes with a Two Light Reverser 
Indication Circuit configuration, and with TRAS locks installed, 
perform repetitive inspections and checks within every 7,000 hours 
TSLI.

Initial and Repetitive Inspections for CF6-80A1/A3 Series Turbofan 
Engines

    (h) For CF6-80A1/A3 series turbofan engines installed on Airbus 
A310-200 airplanes, perform initial and repetitive thrust reverser 
inspections using Section 2, Accomplishment Instructions, of MRAS 
ASB No. CF6-80A1/A3 S/B 78A-1002, Revision 5, dated July 19, 2007, 
at the following:
    (1) For initial inspection, within 1,500 hours TIS after the 
effective date of this AD.
    (2) For repetitive inspections, within every 7,000 hours TSLI.

Initial Inspection for CF6-80C2A Series Turbofan Engines

    (i) For CF6-80C2A series turbofan engines, perform initial 
thrust reverser inspections using Section 2, Accomplishment

[[Page 60606]]

Instructions, of MRAS ASB No. CF6-80C2A1/A2/A3/A5/A8/A5F S/B 
78A1015, Revision 7, dated August 30, 2007, at the following:
    (1) On Airbus A300 and A310 series airplanes with left-hand and 
right-hand reverser halves that do not have the double/backup P-seal 
introduced by MRAS SB No. CF6-80C2 S/B 78A1005, and that do not have 
locking actuator assemblies (LAAs) installed, within 600 hours TIS 
after the effective date of this AD.
    (2) On Airbus A300 and A310 series airplanes with left-hand and 
right-hand reverser halves that have the double/backup P-seal 
introduced by MRAS SB No. CF6-80C2 S/B 78A1005, or that have LAAs 
installed, within 7,000 hours TIS after the effective date of this 
AD.

Directional Pilot Valve (DPV) Pressure Switch Check on Airbus Airplanes 
With CF6-80C2A5F Engines Is Not Applicable

    (3) The DPV pressure switch check per paragraph 2.F. is not 
applicable to Airbus airplanes with CF6-80C2A5F left-hand and right-
hand fan reverser halves (model ES-CF6-5), because this check is 
performed through the full authority digital electronic control 
fault detection system.

Repetitive Inspections for CF6-80C2A Series Turbofan Engines

    (j) For CF6-80C2A series turbofan engines, perform repetitive 
thrust reverser inspections using Section 2, Accomplishment 
Instructions, of MRAS ASB No. CF6-80C2A1/A2/A3/A5/A8/A5F S/B 
78A1015, Revision 7, dated August 30, 2007, at the following:
    (1) On Airbus A300 and A310 series airplanes with left-hand and 
right-hand reverser halves that do not have the double/backup P-
seal, introduced by MRAS SB No. CF6-80C2 S/B 78A1005, and that do 
not have LAAs installed, within every 600 hours TSLI.
    (2) On Airbus A300 and A310 series airplanes with left-hand and 
right-hand reverser halves that have the double/backup P-seal, 
introduced by MRAS SB No. CF6-80C2 S/B 78A1015, or that have LAAs 
installed, within every 7,000 hours TSLI.

Engines That Fail an Inspection or Check

    (k) On engines that fail an inspection or check required by this 
AD, perform corrective actions or deactivate the fan reverser per 
Section 2, Accomplishment Instructions, of the applicable MRAS ASB, 
before further flight.

Previous Credit

    (l) Initial and repetitive inspections and checks of the thrust 
reverser actuation systems done before the effective date of this AD 
that use the following ASBs, comply with the requirements specified 
in this AD:
    (1) MRAS ASB No. CF6-50 S/B 78A-3001, Revision 2, dated December 
18, 1997; and MRAS ASB No. CF6-50 S/B 78A-3001, Revision 3, dated 
May 3, 2006.
    (2) MRAS ASB No. CF6-80A1/A3 S/B 78A-1002, Revision 3, dated 
January 21, 1999; and MRAS ASB No. CF6-80A1/A3 S/B 78A-1002, 
Revision 4, dated May 3, 2006.
    (3) MRAS ASB No. CF6-80C2 S/B 78A1015, Revision 5, dated January 
21, 1999; and MRAS ASB No. CF6-80C2A1/A2/A3/A5/A8/A5F S/B 78A1015, 
Revision 6, dated May 3, 2006.

Alternative Methods of Compliance

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

Related Information

    (n) France AD 1999-422- IMP(B), dated October 20, 1999, also 
addresses the subject of this AD.
    (o) Contact Robert Green, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
Robert.green@faa.gov; telephone (781) 238-7754; fax (781) 238-7199, 
for more information about this AD.

    Issued in Burlington, Massachusetts, on October 18, 2007.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. E7-21000 Filed 10-24-07; 8:45 am]
BILLING CODE 4910-13-P