[Federal Register Volume 64, Number 171 (Friday, September 3, 1999)]
[Rules and Regulations]
[Pages 48286-48288]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-22967]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-ANE-54-AD; Amendment 39-11286; AD 99-18-20]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to General Electric Company (GE) CF6-50, -80A1/A3, and -
80C2A series turbofan engines installed on Airbus A300 and A310 series 
airplanes, that requires initial and repetitive thrust reverser 
inspections and checks, and allows extended repetitive inspection 
intervals if an optional double p-seal configuration is installed. This 
amendment is prompted by the report of a higher than anticipated center 
drive unit (CDU) cone brake failure rate which reduces the overall 
thrust reverser system protection against inadvertent deployment. The 
actions specified by this AD are intended to prevent inadvertent in-
flight thrust reverser deployment, which can result in loss of control 
of the airplane.

DATES: Effective November 2, 1999.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 2, 1999.

ADDRESSES: The service information referenced in this AD may be 
obtained from Middle River Aircraft Systems, Mail Point 46, 103 
Chesapeake Park Plaza, Baltimore, MD, 21220-4295, attn: Warranty 
Support, telephone: (410) 682-0094, fax: (410) 682-0100. This 
information may be examined at the Federal Aviation Administration 
(FAA), New England Region, Office of the Regional Counsel, 12 New 
England Executive Park, Burlington, MA; or at the Office of the Federal 
Register, 800 North Capitol Street, NW, suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: William S. Ricci, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone (781) 
238-7742, fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to General Electric Company (GE) CF6-
50, -80A1/A3, and -80C2A series turbofan engines installed on Airbus 
A300 and A310 series airplanes was published in the Federal Register on 
February 23, 1999 (64 FR 8762). That action proposed to require initial 
and repetitive thrust reverser inspections and checks, and allow 
extended repetitive inspection intervals if an optional double p-seal 
configuration is installed.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.
    One commenter requests an initial inspection interval of at least 
860 hours time-in-service (TIS). The commenter states that it performs 
B-checks at intervals of 430 hours TIS and opens the fan reverser at 
every other B-check (at intervals of 860 hours TIS) for engine 
accessibility. The FAA does not concur. The thrust reverser system 
safety analysis indicates that extending the initial compliance 
interval would increase the probability of an inadvertent deployment of 
the thrust reverser in-flight and provide an unacceptable level of 
safety. The FAA determined the need to establish system integrity in 
the fleet, and the 600 hour TIS initial compliance interval for CF6-
80C2A series engines provides that level of safety. The desire to 
conform inspections to an operator's scheduled maintenance, by itself, 
is not sufficient to change the initial inspection interval.
    One commenter requests inspections performed in accordance with 
Revision 1 of Middle River Aircraft Systems CF6-80A1/A3 Service 
Bulletin (SB) No. 78-1002 be accepted for compliance with the proposed 
rule. The FAA does not concur. Revision 3 of SB No. 78-1002 includes 
inspections of electrical cables, the aft frame, and the ball screw 
housing that are not included in earlier revisions.
    One commenter states that airplanes that have not had components 
removed, replaced, or modified which could alter the actuation system 
rigging, or that have undergone previous health check inspections, 
should not be required to have the fan reverser operational check 
portion of the initial inspection performed. The FAA does not concur. 
The purpose of a fan reverser operational check is to ensure that the 
system has been restored to operational status after inspections have 
been completed.
    One commenter requests that the reporting requirement, contained in 
the Accomplishment Instructions of the SB, should be omitted from the 
proposed rule. The FAA does not concur. The instruction to report 
inspection results is to the manufacturer, not the FAA. The FAA did not 
impose a specific reporting requirement in the proposed rule. However, 
the FAA recommends reporting inspection results to the manufacturer in 
accordance with the SB, as reporting inspection results is important to 
ensure that the failure rate data used in the risk analysis to 
establish inspection requirements and intervals remain valid.
    One commenter believes it is not necessary to start the engine to 
perform the operational check. The FAA concurs. Connection of an 
external pneumatic power source to the airplane ground connection, or 
auxiliary power unit (APU), in accordance with the

[[Page 48287]]

applicable aircraft maintenance manual, is allowed for fan reverser 
operational checks.
    One commenter requests that specific revision numbers and part 
numbers be omitted from the proposed rule and that the phrase ``current 
or later revision'' be added. The FAA does not concur. It is the FAA's 
policy not to issue blanket approvals for documents that have not been 
published yet. Each document is reviewed individually to make sure it 
fulfills all requirements. Operators may request an alternate method of 
compliance (AMOC) to utilize later revisions of SBs in accordance with 
paragraph (b) of this final rule.
    One commenter (the manufacturer of the thrust reverser system) 
requests that the mail stop and telephone number for its technical 
publications department be changed. The FAA concurs and the information 
has been changed in this final rule.
    One commenter (the engine manufacturer) requests that the engine 
model designation of the GE CF6-80C2 engine be changed to -80C2A. The 
FAA concurs and this final rule has been corrected.
    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 with the changes described 
previously. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.
    There are approximately 849 engines of the affected design in the 
worldwide fleet. The FAA estimates that 193 engines installed on 
aircraft of US registry will be affected by this AD, that it will take 
approximately 5 work hours per engine to accomplish the required 
actions, and that the average labor rate is $60 per work hour. Based on 
these figures, the total cost impact of the AD on US operators is 
estimated to be $57,900.
    The regulations adopted herein will not have substantial direct 
effects 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. Therefore, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    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 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. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air Transportation, Aircraft, Aviation safety, Incorporation by 
reference, 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 adding the following new 
airworthiness directive:

99-18-20  General Electric Company: Amendment 39-11286. Docket 98-
ANE-54-AD.

    Applicability: General Electric Company (GE) CF6-50, -80A1/A3, 
and -80C2A series turbofan engines, installed on Airbus A300 and 
A310 series airplanes.

    Note 1: This airworthiness directive (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 (b) 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: Required as indicated, unless accomplished 
previously.
    To prevent inadvertent in-flight thrust reverser deployment, 
which can result in loss of control of the airplane, accomplish the 
following:
    (a) Perform initial and repetitive thrust reverser inspections 
and checks as follows:
    (1) For GE CF6-50 series engines, perform inspections and checks 
in accordance with paragraph 2, Accomplishment Instructions, of 
Middle River Aircraft Systems CF6-50 Service Bulletin (SB) No. 78-
3001, Revision 2, dated December 18, 1997, as follows:
    (i) Perform the initial inspections and checks within 1,500 
hours time-in-service (TIS) after the effective date of this AD.
    (ii) Thereafter, perform inspections and checks at intervals not 
to exceed 6,000 hours TIS since last check.
    (2) For CF6-80A1/A3 series engines, perform inspections and 
checks in accordance with paragraph 2, Accomplishment Instructions, 
of Middle River Aircraft Systems CF6-80A1/A3 SB No. 78-1002, 
Revision 3, dated January 21, 1999, as follows:
    (i) Perform the initial inspections and checks within 1,500 
hours TIS after the effective date of this AD.
    (ii) Thereafter, perform inspections and checks at intervals not 
to exceed 7,000 hours TIS since last check.
    (3) For CF6-80C2A series engines, perform inspections and checks 
in accordance with paragraph 2, Accomplishment Instructions, of 
Middle River Aircraft Systems CF6-80C2 Alert Service Bulletin (ASB) 
No. 78A1015, Revision 5, dated January 21, 1999, as follows:
    (i) Perform the initial inspections and checks within 600 hours 
TIS after the effective date of this AD.
    (ii) Thereafter, perform repetitive inspections and checks as 
follows:
    (A) For engines with a double p-seal configuration, having 
translating cowl part numbers 491B1613000-109 or D52B1000-9, perform 
repetitive inspections and checks at intervals not to exceed 7,000 
hours TIS since last inspection.
    (B) For all other engines, perform repetitive inspections and 
checks at intervals not to exceed 600 hours TIS since last 
inspection.
    (4) Perform corrective actions or deactivate the fan reverser in 
accordance with paragraph 2, Accomplishment Instructions, of the 
applicable SB or ASB prior to further flight.
    (b) 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. 
Operators shall submit their request through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Engine Certification Office.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the Engine Certification Office.

    (c) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the aircraft to a location where 
the requirements of this AD can be accomplished.
    (d) The actions required by this AD shall be done in accordance 
with the following Middle River Aircraft Systems service documents:

[[Page 48288]]



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                 Document No.                    Pages     Revision                      Date
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CF6-50 SB 78-3001............................       1-43          2  December 18, 1997.
Total Pages: 43.
CF6-80A1/A3 SB 78-1002.......................       1-31          3  January 21, 1999.
Total Pages: 31.
CF6-80C2 ASB 78A1015.........................       1-32          5  January 21, 1999.
Total Pages: 32.
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This incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Middle River Aircraft Systems, Mail 
Point 46, 103 Chesapeake Park Plaza, Baltimore, MD, 21220-4295, 
attn: Warranty Support, telephone: (410) 682-0094, fax: (410) 682-
0100. Copies may be inspected at the FAA, New England Region, Office 
of the Regional Counsel, 12 New England Executive Park, Burlington, 
MA; or at the Office of the Federal Register, 800 North Capitol 
Street, NW, suite 700, Washington, DC.
    (e) This amendment becomes effective on November 2, 1999.

    Issued in Burlington, Massachusetts, on August 26, 1999.
Jorge A. Fernandez,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 99-22967 Filed 9-2-99; 8:45 am]
BILLING CODE 4910-13-P