[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