[Federal Register Volume 68, Number 117 (Wednesday, June 18, 2003)]
[Rules and Regulations]
[Pages 36455-36458]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-15223]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NE-09-AD; Amendment 39-13193; AD 2003-12-08]
RIN 2120-AA64
Airworthiness Directives; General Electric Company CF6-80A1/A3
and CF6-80C2A PMC Series Turbofan Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
[[Page 36456]]
SUMMARY: This amendment adopts a new airworthiness directive (AD), that
is applicable to General Electric Company (GE) CF6-80A1/A3 and CF6-
80C2A PMC series turbofan engines. This amendment requires performing
either a directional pilot valve (DPV) pressure switch moisture purge
procedure and an operational check of the fan reverser or replacing the
DPV assembly with a serviceable assembly and performing an operational
check of the fan reverser. Thereafter, this AD requires one of these
actions on a repetitive basis. This amendment is prompted by a review
of fan reverser safety analyses resulting from the discovery of an
undetectable failure mode of the DPV pressure switch on certain GE CF6-
80C2A and CF6-80A1/A3 engine models. The actions specified by this AD
are intended to prevent inadvertent fan reverser deployment, which, if
it occurred in-flight, could result in loss of control of the airplane.
DATES: Effective July 23, 2003. The incorporation by reference of
certain publications listed in the regulations is approved by the
Director of the Federal Register as of July 23, 2003.
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, telephone: (410) 682-
0094; fax: (410) 682-0100. This information may be examined, by
appointment, 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: Karen Curtis, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (781)
238-7192; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an AD that is
applicable to General Electric Company (GE) CF6-80A1/A3 and CF6-80C2A
PMC series turbofan engines was published in the Federal Register on
June 21, 2002 (67 FR 42202). That action proposed to require performing
either a directional pilot valve (DPV) pressure switch moisture purge
procedure and an operational check of the fan reverser, or replacing
the DPV assembly with a serviceable assembly and performing an
operational check of the fan reverser. Thereafter, that action proposed
to require one of these actions on a repetitive basis in accordance
with Middle River Aircraft Systems Alert Service Bulletins (ASBs) CF6-
80A1/A3 SB 78A4030, dated April 4, 2002 or CF6-80C2A PMC SB 78A1118,
dated April 4, 2002.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
Request to Revise Applicability Statement
One commenter requests that the applicability statement be revised
to reference the left-hand fan reverser halves associated with the
engines instead of the engine models themselves. The commenter believes
that the DPV assembly is not a part of the engine, but is instead a
part of the left-hand fan reverser half. The commenter notes the fact
that the reverser halves and engines can be removed or installed
separately.
The FAA does not agree. The FAA acknowledges that in service the
engines and fan reversers can be separated, with the possibility of
reversers remaining installed on-wing, while different engines are
installed. However, the fan reverser assembly and, therefore, the DPV
are part of the engine (14 CFR part 33) type design. The applicability
to the engine model is, therefore, appropriate. No changes will be made
to the AD as a result of this comment.
Request to Add Isopropyl Alcohol as an Alternate to Acetone
One commenter requests that isopropyl alcohol be allowed as an
acceptable alternate to the acetone solvent listed in the consumables
of the ASBs as the fluid used for purging moisture from the DPV
pressure switch assemblies. The commenter notes that some airports may
restrict the use of acetone. The commenter also notes that the DPV
assembly manufacturer has agreed that alcohol is an acceptable
alternate for acetone for the purposes of accomplishing the moisture
purge service bulletins.
The FAA agrees that isopropyl alcohol is an acceptable alternate
for acetone for this application. The FAA, GE, and the component
manufacturer, previously identified this issue and the ASBs were
revised on August 23, 2002, to allow the use of isopropyl alcohol. The
compliance section of this final rule AD has been revised to add
Revision 1 to each of the ASBs.
Alternative for Replacement of Serviceable DPV
One commenter requests that deactivation of the fan reverser be
allowed as an alternative to replacement with a serviceable DPV. The
commenter sites a previous AD (99-18-19) that allowed deactivation
instead of a DPV leak check inspection.
The FAA agrees and the final rule is revised to allow deactivation.
Limitations for operation with one or more reversers deactivated have
also been added and are consistent with the previous AD.
Request to Rewrite Description of the Failure Sequence
One commenter requests that the description of the failure sequence
in the discussion section of the NPRM preamble be reworded to clarify
that an additional failure is required in order for the undetectable
DPV pressure switch freezing failure to result in an inadvertent
deployment (IAD). The commenter believes that the current statement is
misleading. The commenter believes that in addition to the
pressurization failure, a directional failure is required before an IAD
can occur.
The FAA does not agree. While the FAA agrees that the wording could
have been clearer, the requested change does not affect the conclusion
that an unsafe condition has been identified. In addition, the
Discussion section details are not repeated in the final rule after an
NPRM, and therefore, the AD remains unchanged as a result of this
comment.
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.
Regulatory Analysis
This final rule does not have federalism implications, as defined
in Executive Order 13132, because it would not have a substantial
direct effect 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. Accordingly,
the FAA has not consulted with state authorities prior to publication
of this final rule.
[[Page 36457]]
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 the 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
by contacting 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
0
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
0
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]
0
2. Section 39.13 is amended by adding a new airworthiness directive to
read as follows:
2003-12-08 General Electric Company: Amendment 39-13193. Docket No.
2002-NE-09-AD.
Applicability: This airworthiness directive (AD) is applicable
to General Electric Company (GE) CF6-80A1/A3 and CF6-80C2A PMC
series turbofan engines. These engines are installed on, but not
limited to Airbus Industrie A300-600 and A310 series airplanes.
Note 1: This 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 (k) 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: Compliance with this AD is required as indicated,
unless already done. To prevent inadvertent fan reverser deployment,
which, if it occurred in-flight, could result in loss of control of
the airplane, do the following:
GE CF6-80A1/A3 Series Engines
(a) For GE CF6-80A1/A3 series engines, perform one of the
following no later than 1,400 flight hours time-since-new (TSN) or
600 flight hours time-in-service (TIS) after the effective date of
this AD, whichever occurs later:
(1) Perform the directional pilot valve (DPV) pressure switch
moisture purge, in accordance with Paragraph 3.C. of the
Accomplishment Instructions of Middle River Aircraft Systems Alert
Service Bulletins (ASBs) CF6-80A1/A3 SB 78A4030, dated April 4,
2002, or CF6-80A1/A3 SB 78A4030, Revision 1, dated August 23, 2002,
or
(2) Replace the DPV assembly with a serviceable assembly, or
(3) Deactivate the thrust reverser. The DPV must be replaced
with a serviceable assembly within 10 days after deactivation.
Information on deactivating the thrust reverser can be found in the
applicable Aircraft Maintenance Manual (AMM).
(b) After each purge or replacement done in accordance with
paragraph (a)(1), (a)(2), or (a)(3) of this AD, perform an
operational check of the fan reverser in accordance with Paragraph
3.E. of the Accomplishment Instructions of ASBs CF6-80A1/A3 SB
78A4030, dated April 4, 2002, or CF6-80A1/A3 SB 78A4030, Revision 1,
dated August 23, 2002.
(c) Thereafter, for GE CF6-80A1/A3 series engines, at intervals
not to exceed 1,400 hours TIS since the last pressure switch purge
or replacement of the DPV assembly, perform one of the following:
(1) Perform the DPV pressure switch moisture purge, in
accordance with Paragraph 3.C. of the Accomplishment Instructions of
Middle River Aircraft Systems ASBs CF6-80A1/A3 SB 78A4030, dated
April 4, 2002, or CF6-80A1/A3 SB 78A4030, Revision 1, dated August
23, 2002, or
(2) Replace the DPV assembly with a serviceable assembly, or
(3) Deactivate the thrust reverser. The DPV must be replaced
with a serviceable assembly within 10 days after deactivation.
Information on deactivating the thrust reverser can be found in the
applicable AMM.
(d) After each purge or replacement done in accordance with
paragraph (c)(1), (c)(2), or (c)(3) of this AD, perform an
operational check of the fan reverser in accordance with Paragraph
3.E. of the Accomplishment Instructions of ASBs CF6-80A1/A3 SB
78A4030, dated April 4, 2002, or CF6-80A1/A3 SB 78A4030, Revision 1,
dated August 23, 2002.
GE CF6-80C2A Series Engines
(e) For GE CF6-80C2A1/A2/A3/A5/A8 series engines, perform one of
the following no later than 1,400 flight hours TSN or 600 flight
hours TIS after the effective date of this AD, whichever occurs
later:
(1) Perform the DPV pressure switch moisture purge, in
accordance with Paragraph 3.C. of the Accomplishment Instructions of
Middle River Aircraft Systems ASBs CF6-80C2A PMC SB 78A1118, dated
April 4, 2002, or CF6-80C2A PMC SB 78A1118, Revision 1, dated August
23, 2002, or
(2) Replace the DPV assembly with a serviceable assembly, or
(3) Deactivate the thrust reverser. The DPV must be replaced
with a serviceable assembly within 10 days after deactivation.
Information on deactivating the thrust reverser can be found in the
applicable AMM.
(f) After each purge or replacement done in accordance with
paragraphs (e)(1), (e)(2), or (e)(3) of this AD, perform an
operational check of the fan reverser, in accordance with Paragraph
3.E. of the Accomplishment Instructions ASBs CF6-80C2A PMC SB
78A1118, dated April 4, 2002, or CF6-80C2A PMC SB 78A1118, Revision
1, dated August 23, 2002.
(g) Thereafter, for GE CF6-80C2A1/A2/A3/A5/A8 series engines,
perform one of the following at intervals not to exceed 1,400 hours
TIS since the last pressure switch purge or replacement of the DPV
assembly:
(1) Perform the DPV pressure switch moisture purge, in
accordance with Paragraph 3.C. of the Accomplishment Instructions of
Middle River Aircraft Systems ASBs CF6-80C2A PMC SB 78A1118, dated
April 4, 2002, or CF6-80C2A PMC SB 78A1118, Revision 1, dated August
23, 2002, or
(2) Replace the DPV assembly with a serviceable assembly, or
(3) Deactivate the thrust reverser. The DPV must be replaced
with a serviceable assembly within 10 days after deactivation.
Information on deactivating the thrust reverser can be found in the
applicable AMM.
(h) After each purge or replacement done in accordance with
paragraphs (g)(1), (g)(2), or (g)(3) of this AD, perform an
operational check of the fan reverser, in accordance with Paragraph
3.E. of the Accomplishment Instructions of ASBs CF6-80C2A PMC SB
78A1118, dated April 4, 2002, or CF6-80C2A PMC SB 78A1118, Revision
1, dated August 23, 2002.
Serviceable DPV Assembly
(i) For the purpose of this AD, a serviceable DPV assembly is an
assembly that has:
(1) Accumulated zero time since new, or
(2) Passed the tests in the Middle River Aircraft Systems
Component Maintenance Manual GEK 85007 (78-31-51), Revision No. 7 or
later, Directional Pilot Solenoid Valve, Page Block 101, Testing and
Troubleshooting, and that has zero flight hours TIS since passing
the tests, or
(3) Been successfully purged according to paragraphs (a)(1), (c)
(1), (e)(1) or (g)(1) of this AD immediately before installation on
the fan reverser.
Deactivation Requirements
(j) If one or both thrust reversers are deactivated, then prior
to further flight, revise the Limitations Section of the FAA-
approved AFM to include the following:
``The takeoff performance on wet and contaminated runways with a
thrust
[[Page 36458]]
reverser(s) deactivated shall be determined in accordance with
Airbus Flight Operations Telex (FOT) 999.0066/99, dated June 9,
1999, as follows:
For takeoff on wet runways, use performance data in accordance
with paragraph 4.1.1 of the FOT.
For takeoff on contaminated runways, use performance data in
accordance with paragraph 4.1.2 of the FOT.''
(1) Notwithstanding the provisions of the FAA approved A300-600
and A310 Master Minimum Equipment List (MMEL), dispatch with both
thrust reversers deactivated, for the purposes of complying with
this AD, is approved.
(2) Notwithstanding the provisions of the FAA Approved A300-600
and A310 MMEL, airplanes which have deactivated one or both thrust
reversers in compliance with this AD, may not conduct operation on
contaminated runways, as defined in Airbus Flight Crew Operating
Manual Section 2.18.50, unless all components of the Main Wheel
Brakes, Green and Yellow Brake Systems, Antiskid System, Ground
Spoiler System, and all Spoiler and Speed Brake Surfaces, operate
normally.
Note 2: The ``FCOM'' referenced in Airbus FOT 999.0066/99, dated
June 9, 1999, is Airbus Industrie Flight Crew Operating Manual
(FCOM), Revision 27 for Airbus Model A310 series airplanes and
Revision 22 for A300-600 series airplanes. [The revision number is
indicated on the List of Effective Pages (LEP) of the FCOM.]
Alternative Methods of Compliance
(k) 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 (ECO).
Operators must submit their request through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, ECO.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the ECO.
Special Flight Permits
(l) Special flight permits may be issued in accordance with
Sec. Sec. 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the airplane to a location where
the requirements of this AD can be done.
Documents That Have Been Incorporated By Reference
(m) The actions must be done in accordance with the following
Middle River Aircraft Systems Alert Service Bulletins:
----------------------------------------------------------------------------------------------------------------
Document no. Pages Revision Date
----------------------------------------------------------------------------------------------------------------
CF6-80C2A, PMC SB 78A1118............. All................... Original.............. April 4, 2002
Total Pages: 18...................
CF6-80C2A, PMC SB 78A1118............. 1..................... 1..................... August 23, 2002
2-4................... Original.............. April 4, 2002
5..................... 1..................... August 23, 2002
6-8................... Original.............. April 4, 2002
9-10.................. 1..................... August 23, 2002
11-18................. Original.............. April 4, 2002
Total Pages: 18...................
CF6-80A1/A3, SB 78A4030............... All................... Original.............. April 4, 2002
Total Pages: 18...................
CF6-80A1/A3, SB 78A4030............... 1..................... 1..................... August 23, 2002
2-4................... Original.............. April 4, 2002
5..................... 1..................... August 23, 2002
6-8................... Original.............. April 4, 2002
9-10.................. 1..................... August 23, 2002
11-18................. Original.............. April 4, 2002
Total Pages: 18...................
----------------------------------------------------------------------------------------------------------------
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,
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.
Effective Date
(n) This amendment becomes effective on July 23, 2003.
Issued in Burlington, Massachusetts, on June 9, 2003.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 03-15223 Filed 6-17-03; 8:45 am]
BILLING CODE 4910-13-P