[Federal Register Volume 60, Number 94 (Tuesday, May 16, 1995)]
[Rules and Regulations]
[Pages 25985-25987]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-11904]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-ANE-17; Amendment 39-9228; AD 95-10-11]
Airworthiness Directives; General Electric Company CF6 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 [[Page 25986]] applicable to General Electric Company (GE) CF6-80C2
series turbofan engines. This action requires an initial and repetitive
brake holding torque check of the fan reverser center drive unit (CDU),
visual inspection of the translating cowl inner bondment seal, and
functional check of the translating cowl auto re-stow system. This
action also requires removal and replacement of certain CDU's as a
terminating action to the repetitive check and inspection program. This
amendment is prompted by a report of a CDU not able to hold the fan
reverser translating cowl at the required position when manually driven
to its stow position during routine maintenance. The actions specified
in this AD are intended to prevent the loss of the CDU's brake holding
feature, which could result in possible movement of the fan reverser
translating cowl towards the deploy position in flight.
DATES: Effective May 31, 1995. -
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of May 31, 1995.
Comments for inclusion in the Rules Docket must be received on or
before July 17, 1995.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Assistant Chief
Counsel, Attention: Rules Docket No. 95-ANE-17, 12 New England
Executive Park, Burlington, MA 01803-5299.
The service information referenced in this AD may be obtained from
Martin Marietta Services, Inc., Attn: Karen Lyons, 10525 Chester Road,
Cincinnati, OH 45215. 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: Robert Ganley, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (617)
238-7138; fax (617) 238-7199.
SUPPLEMENTARY INFORMATION: The Federal Aviation Administration (FAA)
received a report of a center drive unit (CDU) not able to hold the fan
reverser translating cowl at the required position when manually driven
to its stow position during routine maintenance. Investigation revealed
that the CDU brake shaft had worn to the extent that the braking
feature was inoperative. This feature, in conjunction with two
additional features (auto re-stow and stow retention), prevents the
uncommanded movement of the translating cowl towards the deploy
position. Further investigation revealed that the wear was due to the
low material hardness of the brake shaft. This low material hardness is
the result of a heat treat step that was inadvertently omitted from the
manufacturing cycle of the brake shaft. This condition, if not
corrected, could result in loss of the CDU's brake holding feature,
which could result in possible movement of the fan reverser translating
cowl towards the deploy position in flight.
The FAA has reviewed and approved the technical contents of Martin
Marietta CF6-80C2 Service Bulletin (SB) No. 78-1002, Revision 1, dated
March 23, 1995, that describes procedures for the brake holding torque
check of the fan reverser CDU, visual inspection of the translating
cowl inner bondment seal, functional check of the translating cowl auto
re-stow system, and the removal and replacement of the CDU.
Since an unsafe condition has been identified that is likely to
exist or develop on other General Electric Company (GE) CF6-80C2 series
turbofan engines of the same type design, this AD is being issued to
prevent the loss of the CDU's brake holding feature, which could result
in possible movement of the fan reverser translating cowl towards the
deploy position in flight. This AD requires an initial and repetitive
brake holding torque check of the fan reverser CDU, visual inspection
of the translating cowl inner bondment seal, and functional check of
the translating cowl auto re-stow system. This AD also requires removal
and replacement of certain CDU's as a terminating action to the
repetitive check and inspection program. 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 95-ANE-17.'' 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.'' [[Page 25987]]
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. App. 1354(a), 1421 and 1423; 49 U.S.C.
106(g); and 14 CFR 11.89.
Sec. 39.13 [Amended] -
2. Section 39.13 is amended by adding the following new
airworthiness directive:
95-10-11 General Electric Company: Amendment 39-9228. Docket 95-
ANE-17.
-Applicability: General Electric Company (GE) CF6-80C2 series
turbofan engines installed on, but not limited to, Airbus A300 and
A310 series, Boeing 747 and 767 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 use the
authority provided in paragraph (e) to request approval from the
Federal Aviation Administration (FAA). This approval may address
either no action, if the current configuration eliminates the unsafe
condition, or different actions necessary to address the unsafe
condition described in this AD. Such a request should include an
assessment of the effect of the changed configuration on the unsafe
condition addressed by this AD. In no case does the presence of any
modification, alteration, or repair remove any engine from the
applicability of this AD.-
-Compliance: Required as indicated, unless accomplished
previously. -
To prevent a loss of the center drive units (CDU) brake holding
feature, which could result in possible movement of the fan reverser
translating cowl towards the deploy position in flight, accomplish
the following: -
(a) For fan reversers that have a CDU identified in paragraph
1.A.(1) of Martin Marietta (MM) CF6-80C2 Service Bulletin (SB) No.
78-1002, Revision 1, dated March 23, 1995, installed, perform the
following: -
(1) If the requirements of MM CF6-80C2 SB No. 78-1002, dated
February 27, 1995, or MM CF6-80C2 SB No. 78-1002, Revision 1, dated
March 23, 1995, have not been previously accomplished, perform a
brake holding torque check of the fan reverser CDU, a visual
inspection of the translating cowl inner bondment seal, and a
functional check of the translating cowl auto re-stow system in
accordance with paragraphs 2.B, 2.C, and 2.D of MM CF6-80C2 SB No.
78-1002, Revision 1, dated March 23, 1995, prior to accumulating 250
cycles in service (CIS) or 30 days, after the effective date of this
AD, whichever occurs earlier.
(2) If the requirements of MM CF6-80C2 SB No. 78-1002, dated
February 27, 1995, or MM CF6-80C2 SB No. 78-1002, Revision 1, dated
March 23, 1995, have been previously accomplished, accomplish the
following: -
(i) Perform a brake holding torque check of the fan reverser CDU
in accordance with paragraph 2.B of MM CF6-80C2 SB No. 78-1002,
Revision 1, dated March 23, 1995, prior to accumulating 250 CIS
since the last brake holding torque check. -
(ii) Perform a visual inspection of the translating cowl inner
bondment seal, and a functional check of the translating cowl auto
re-stow system in accordance with paragraphs 2.C and 2.D of MM CF6-
80C2 SB No. 78-1002, Revision 1, dated March 23, 1995, prior to
accumulating 1,000 hours since the last visual inspection of the
translating cowl inner bondment seal and functional check of the
translating cowl auto re-stow system. -
(b) Thereafter, for fan reversers that have accomplished the
inspection and check requirements in accordance with paragraph (a)
of this AD, accomplish the following: -
(1) Perform a brake holding torque check of the fan reverser CDU
in accordance with paragraph 2.B of MM CF6-80C2 SB No. 78-1002,
Revision 1, dated March 23, 1995, prior to accumulating 250 CIS
since the last brake holding torque check. -
(2) Perform a visual inspection of the translating cowl inner
bondment seal, and a functional check of the translating cowl auto
re-stow system in accordance with paragraphs 2.C and 2.D of MM CF6-
80C2 SB No. 78-1002, Revision 1,dated March 23, 1995, prior to
accumulating 1,000 hours since the last visual inspection of the
translating cowl inner bondment seal and functional check of the
translating cowl auto re-stow system. -
(c) Remove from service the CDU's identified in paragraph
1.A.(1) of MM CF6-80C2 SB No. 78-1002, Revision 1, dated March 23,
1995, in accordance with paragraph 2.F of MM CF6-80C2 SB No. 78-
1002, Revision 1, dated March 23, 1995, prior to December 31, 1995,
and replace with a serviceable part. Removal and replacement of the
CDU in accordance with this paragraph constitutes terminating action
to the initial and repetitive inspection and check requirements of
paragraph (a) and (b) of this AD. -
(d) For the purpose of this AD, a serviceable part is defined as
a CDU that has accomplished any revision level of MM CF6-80C2 SB No.
78-1014; or a CDU whose shaft has received the hardness inspection
in accordance with any revision level of GE CF6-80C2 SB No. 78-131,
and that has not had a brake shaft replacement subsequent to the
hardness inspection. -
(e) 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 alternate
methods of compliance with this airworthiness directive, if any, may
be obtained from the Engine Certification Office.
(f) Special flight permits may be issued in accordance with FAR
21.197 and 21.199 to operate the aircraft to a location where the
requirements of this AD can be accomplished.
(g) The actions required by this AD shall be done in accordance
with the following service bulletin:
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Document No.-- Pages-- Revision- Date
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Martin Marietta CF6-80C2......... 2, 11, 12, 14-18, 20............. Original............ Feb. 27, 1995.
SB No. 78-1002-.................. 1, 3-10, 13, 19--................ 1................... Mar. 23, 1995.
Total pages: 20.
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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 Martin Marietta Services, Inc.,
Attn: Karen Lyons, 10525 Chester Road, Cincinnati, OH 45215. 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. -
(h) This amendment becomes effective on May 31, 1995.
Issued in Burlington, Massachusetts, on May 2, 1995.
Mark C. Fulmer,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 95-11904 Filed 5-12-95; 3:16 pm]
BILLING CODE 4910-13-U
