[Federal Register Volume 61, Number 157 (Tuesday, August 13, 1996)]
[Rules and Regulations]
[Pages 41951-41953]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-20397]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 96-ANE-16; Amendment 39-9707, AD 96-16-07]
RIN 2120-AA64
Airworthiness Directives; General Electric Company (GE) CF6-80C2
Series Turbofan Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to General Electric Company (GE) CF6-80C2 series turbofan
engines. This action supersedes priority letter AD 96-09-01 that
currently requires borescope inspections of the rear right hand mount
link to determine if the serial number matches those listed in
applicable service bulletins as improperly manufactured, and
replacement, if necessary, with a serviceable part. This action
references a newly revised service bulletin and bases the compliance
time on the effective date of this superseding AD for engines installed
on McDonnell Douglas MD-11 series aircraft. This amendment is prompted
by the availability of the newly revised service bulletin. The actions
specified by this AD are intended to prevent rear right hand mount link
failure, which could result in engine separation from the aircraft.
DATES: Effective August 28, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of August 28, 1996.
Comments for inclusion in the Rules Docket must be received on or
before October 15, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 96-ANE-16, 12 New England
Executive Park, Burlington, MA 01803-5299. Comments may also be
submitted to the Rules Docket by using the following Internet address:
``[email protected]''.
All comments must contain the Docket No. in the subject line of the
comment.
The service information referenced in this AD may be obtained from
General Electric Technical Services, Attn: Leader for Distribution/
Microfilm, 10525 Chester Road, Cincinnati, OH 45215; phone (513) 672-
8400 ext. 114, fax (513) 672-8422. This information may be examined at
the FAA, New England Region, Office of the Assistant Chief 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: Richard Woldan, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (617)
238-7136, fax (617) 238-7199.
SUPPLEMENTARY INFORMATION: On April 15, 1996, the Federal Aviation
Administration (FAA) issued priority
[[Page 41952]]
letter airworthiness directive (AD) 96-09-01, applicable to General
Electric Company (GE) CF6-80C2 series turbofan engines, which requires
borescope inspections of the rear right hand mount link to determine if
the serial number matches those listed in applicable service bulletins
as improperly manufactured, and replacement, if necessary, with a
serviceable part. That action was prompted by reports of rear right
hand mount links that were not properly heat treated during
manufacture. Rear right hand mount links that are not properly heat
treated are susceptible to failure due to insufficient strength. That
condition, if not corrected, could result in rear right hand mount link
failure, which could result in engine separation from the aircraft.
Since the issuance of that priority letter AD, GE has issued CF6-
80C2 Service Bulletin (SB) No. 72-835, Revision 1, dated May 2, 1996.
This AD references this new revision, and bases the compliance time on
the effective date of this superseding AD for engines installed on
McDonnell Douglas MD-11 series aircraft.
Since an unsafe condition has been identified that is likely to
exist or develop on other engines of this same type design, this AD
supersedes priority letter AD 96-09-01 to require the following:
For certain engines installed on Airbus A300 and A310 series
aircraft, prior to further flight, borescope inspect the rear right
hand mount link to determine if the link S/N is listed in GE CF6-80C2
SB No. 72-835, Revision 1, dated May 2, 1996. If the link S/N matches
those listed in that SB, prior to further flight, remove the rear right
hand mount link from service and replace with a serviceable part.
For certain engines installed on McDonnell Douglas MD-11 series
aircraft, within 15 days after the effective date of this AD, borescope
inspect the rear right hand mount link to determine if the link S/N is
listed in GE CF6-80C2 SB No. 72-835, Revision 1, dated May 2, 1996. If
the link S/N matches those listed in that SB, within 60 days after the
effective date of this AD, remove the rear right hand mount link from
service and replace with a serviceable part.
Engines installed on Airbus A300 and A310 series aircraft have
higher certification mount loads than those installed on McDonnell
Douglas MD-11 aircraft, and therefore require immediate inspection. The
actions are required to be accomplished in accordance with the service
bulletin described previously.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this rule by
submitting such written data, views, or arguments as they may desire.
Communications should identify the Rules Docket number and be submitted
in triplicate to the address specified under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. All comments submitted will be
available, both before and after the closing date for comments, in the
Rules Docket for examination by interested persons. A report that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 96-ANE-16.'' The postcard will be date stamped and
returned to the commenter.
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.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and is not a ``significant regulatory action''
under Executive Order 12866. It has been determined further that this
action involves an emergency regulation under DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979). If it is determined
that this emergency regulation otherwise would be significant under DOT
Regulatory Policies and Procedures, a final regulatory evaluation will
be prepared and placed in the Rules Docket. A copy of it, if filed, 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:
96-16-07 General Electric Company: Amendment 39-9707. Docket No. 96-
ANE-16. Supersedes AD 96-09-01.
Applicability: General Electric Company (GE) CF6-80C2 series
turbofan engines identified by Serial Numbers (S/N's) listed in GE
CF6-80C2 Service Bulletin (SB) No. 72-835, Revision 1, dated May 2,
1996. These engines are installed on but not limited to Airbus A300
and A310 series, and McDonnell Douglas MD-11 series aircraft.
Note: 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 (d) 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.
[[Page 41953]]
To prevent rear right hand mount link failure, which could
result in engine separation from the aircraft, accomplish the
following:
(a) No further action is required for operators that have
complied with priority letter AD 96-09-01.
(b) For engines installed on Airbus A300 and A310 series
aircraft, accomplish the following:
(1) Prior to further flight, borescope inspect the rear right
hand mount link in accordance with the Accomplishment Instructions
of GE CF6-80C2 SB No. 72-835, Revision 1, dated May 2, 1996, to
determine if the link S/N is listed in that SB.
(2) If the link S/N does not match those listed in that SB, no
further action is required.
(3) If the link S/N matches those listed in that SB, prior to
further flight remove the rear right hand mount link from service
and replace with a serviceable part in accordance with the
Accomplishment Instructions of GE CF6-80C2 SB No. 72-835, Revision
1, dated May 2, 1996.
(c) For engines installed on McDonnell Douglas MD-11 series
aircraft, accomplish the following:
(1) Within 15 days after the effective date of this AD,
borescope inspect the rear right hand mount link in accordance with
the Accomplishment Instructions of GE CF6-80C2 SB No. 72-835,
Revision 1, dated May 2, 1996, to determine if the S/N is listed in
that SB.
(2) If the S/N does not match those listed in that SB, no
further action is required.
(3) If the S/N matches those listed in that SB, within 60 days
after the effective date of this AD, remove the rear right hand
mount link from service and replace with a serviceable part in
accordance with the Accomplishment Instructions of GE CF6-80C2 SB
No. 72-835, Revision 1, dated May 2, 1996.
(d) 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. The
request should be forwarded through an appropriate FAA Principal
Maintenance Inspector, who may add comments and then send it to the
Manager, Engine Certification Office.
Note: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the Engine Certification Office.
(e) 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.
(f) The actions required by this AD shall be done in accordance
with the following SB:
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Document No. Pages Revision Date
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GE CF6-80C2 SB No. 72-835.................. 1-16 1 May 2, 1996.
Total pages: 16.
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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 General Electric Technical Services,
Attn: Leader for Distribution/Microfilm, 10525 Chester Road,
Cincinnati, OH 45215; phone (513) 672-8400 ext. 114, fax (513) 672-
8422. Copies may be inspected at the FAA, New England Region, Office
of the Assistant Chief 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.
(g) This amendment supersedes priority letter AD 96-09-01,
issued April 15, 1996.
(h) This amendment becomes effective on August 28, 1996.
Issued in Burlington, Massachusetts, on July 31, 1996.
Mark C. Fulmer,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 96-20397 Filed 8-12-96; 8:45 am]
BILLING CODE 4910-13-U