[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]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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]]
----------------------------------------------------------------------------------------------------------------
Document No. Pages Revision Date
----------------------------------------------------------------------------------------------------------------
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.
----------------------------------------------------------------------------------------------------------------
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
