Document ID: FAA-2007-0053-0004
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; General Electric Company CF6-50, -80A1/ A3, and -80C2A Series Turbofan Engines
Posted Date: 2008-01-24T05:00Z

[Federal Register: January 24, 2008 (Volume 73, Number 16)]
[Rules and Regulations]               
[Page 4057-4059]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr24ja08-5]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0053; Directorate Identifier 98-ANE-54-AD; 
Amendment 39-15347; AD 2008-02-17]
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: Final rule.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) for General Electric Company (GE) CF6-50, -80A1/A3, and -80C2A 
series turbofan engines, installed on Airbus A300, A300-600, and A310 
series airplanes. That AD currently requires initial and repetitive 
inspections and checks of the thrust reverser actuation systems. This 
AD requires revised inspection thresholds and intervals, and would 
require the same actions and additional inspections of the thrust 
reverser actuation system locking features. 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.

DATES: This AD becomes effective February 28, 2008. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of February 28, 2008.

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: Warranty Support, telephone: (410) 
682-0094, fax: (410) 682-0100.
    The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.

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: The FAA proposed to amend 14 CFR part 39 by 
superseding AD 99-18-20, Amendment 39-11286 (64 FR 48286, September 3, 
1999), with a proposed AD. The proposed AD applies to GE CF6-50, -80A1/
A3, and -80C2A series turbofan engines, installed on Airbus A300, A300-
600, and A310 series airplanes. We published the proposed AD in the 
Federal Register on October 25, 2007 (72 FR 60604). That action 
proposed to require revised inspection thresholds and intervals, and 
proposed to require the same actions as AD 99-18-20, and additional 
inspections of the thrust reverser actuation system locking features.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://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 AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is provided in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

Comments

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

Service Bulletin Reference Error

    One commenter, GE Aviation, points out that Alert Service Bulletin 
No. CF6-80C2 S/B 78A1015 should be No. CF6-80C2 S/B 78A1005, in 
paragraph (j)(2). We agree and corrected the number in the AD.

Airplane Reference Clarification

    One commenter, Airbus, requests that we clarify paragraphs (i)(1), 
(i)(2), (j)(1), and (j)(2) by referencing that they apply to A300-600 
series airplanes, instead of A300 and A310 series airplanes. We agree 
and made those changes to the AD.

NPRM Costs of Compliance Error

    We inadvertently listed an incorrect estimated cost total of 
$28,000 in the NPRM ``Costs of Compliance'' paragraph. We corrected the 
estimated cost total to $16,480, in this AD.

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

    We estimate that this AD will affect 206 engines installed on 
airplanes of U.S. registry. We also estimate that it will take about 
one work-hour per engine to perform the 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 AD for one inspection of the 
U.S. fleet, to be $16,480.

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

[[Page 4058]]

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 at the 
address listed under ADDRESSES.

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 39-11286 (64 FR 
48286, September 3, 1999), and by adding a new airworthiness directive, 
Amendment 39-15347, to read as follows:

2008-02-17 General Electric Company: Amendment 39-15347. Docket No. 
FAA-2007-0053; Directorate Identifier 98-ANE-54-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective February 
28, 2008.

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, A300-600, 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 78A3001, 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 78A3001, 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 78A1002, 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 
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 A300-600 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 A300-600 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

[[Page 4059]]

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 A300-600 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 A300-600 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 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 78A3001, Revision 2, dated December 
18, 1997; and MRAS ASB No. CF6-50 S/B 78A3001, Revision 3, dated May 
3, 2006.
    (2) MRAS ASB No. CF6-80A1/A3 S/B 78A1002, Revision 3, dated 
January 21, 1999; and MRAS ASB No. CF6-80A1/A3 S/B 78A1002, 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 
pertains to 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.
    (p) You must use the service information specified in Table 1 of 
this AD to perform the inspections 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. 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 a copy of this service information. You may review 
copies at the FAA, New England Region, 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/cfr/ibr-locations.html
.

                                      Table 1.--Incorporation by Reference
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   Middle River Aircraft Systems Alert
          Service Bulletin No.                 Page          Revision                      Date
----------------------------------------------------------------------------------------------------------------
CF6-50 S/B 78A3001......................             All               4  August 30, 2007.
    Total Pages: 50
CF6-80A1/A3 S/B 78A1002.................             All               5  July 19, 2007.
    Total Pages: 38
CF6-80C2A1/A2/A3/A5/A8/A5F S/B 78A1015..             All               7  August 30, 2007.
    Total Pages: 36
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    Issued in Burlington, Massachusetts, on January 15, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E8-975 Filed 1-23-08; 8:45 am]

BILLING CODE 4910-13-P