Airworthiness Directives; General Electric Company (GE) CF6-80A1/A3 and CF6-80C2A Series Turbofan Engines, Installed on Airbus Industrie A300-600 and A310 Series Airplanes, 13365-13368 [05-5299]
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Federal Register / Vol. 70, No. 53 / Monday, March 21, 2005 / Rules and Regulations
13365
Affected airplanes
Eddy current and visual inspections
Repetitive Eddy current and visual inspection
interval
(1) For Model 414A airplanes, serial numbers
414A001 through 414A0047 and 414A0049
through 414A0200.
At whichever of the following occurs later:
• Upon accumulating 8,500 hours TIS on the
airplanes;
• At the next inspection that would have been
required by emergency AD 2005–05–51
(required at intervals not to exceed 15
hours TIS); or
• Within the next 2 days after the effective
date of this AD (2 days after receipt for
those who received emergency AD
200505–52).
At whichever of the following occurs later:
• Upon accumulting 15,000 hours TIS on the
airplane;
• At the next inspection that would have been
required by emergency AD 2005–05–51
(required at intervals not to exceed 15
hours TIS); or
• Within the next 2 days after effective date
of this AD (2 days after receipt for those
who received emergency AD 2005–05–52).
Thereafter at intervals not to exceed 100
hours TIS.
May I Request an Alternative Method of
Compliance?
(i) You may request a different method of
compliance or a different compliance time
for this AD by following the procedures in 14
CFR 39.19. Unless FAA authorizes otherwise,
send your request to your principal
inspector. The principal inspector may add
comments and will send your request to the
Manager, Wichita Aircraft Certification Office
(ACO), FAA.
(1) For information on any already
approved alternative methods of compliance
or for further information about this AD,
contact Paul Nguyen, Aerospace Engineer,
FAA, Wichita ACO, 1801 Airport Road, MidContinent Airport, Wichita, Kansas 67209;
telephone: (316) 946–4125; facsimile: (316)
946–4107; e-mail: paul.nguyen@faa.gov.
(2) Alternative methods of compliance that
were approved for AD 2000–23–01 or
emergency AD 2005–05–51 are not approved
for this emergency AD.
ibr_locations.html or call (202) 741–6030. To
view the AD docket, go to the Docket
Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW.,
Nassif Building, Room PL–401, Washington,
DC 20590–001 or on the Internet at https://
dms.dot.gov. The docket number is FAA–
2005–20513.
(2) For the following airplanes that have 15,000
hours or more TIS or upon accumulating
15,000 hours TIS:
Thereafter at intervals not to exceed 100
hours TIS.
(i) All Model 402C airplanes.
(ii) Model 414A airplanes, serial numbers
414A0201 through 414A1212.
Note: The Cessna service bulletins allow
for either a visual inspection or eddy current
inspection of the forward spars on all
airplanes affected by this AD. Visual
inspections of the forward spars do not
satisfy the requirements of this AD for the
airplanes referenced in paragraphs (f)(1) and
(f)(2) of this AD. These airplanes must have
the forward spars inspected using the eddy
current methods specified in the Cessna
service bulletins.
(g) Cracks Found: If you find any crack on
any forward, aft, or auxiliary wing spar; or in
surrounding structure such as spar webs or
skins during any inspection required by this
AD, before further flight do the following:
(1) Obtain an FAA-approved repair scheme
from the Cessna Aircraft Company, P.O. Box
7706, Wichita, Kansas 67277; telephone:
(316) 517–5800, facsimile: (316) 942–9006;
and
(2) Incorporate this repair scheme.
(h) Reporting Requirement: As soon as
possible, but no later than 24 hours after any
inspection required by this AD and as
defined below:
(1) Submit a report of inspection findings
to the Manager, Wichita Aircraft Certification
Office (ACO), by fax: (316) 946–4107.
(i) Include a report for ‘‘cracks found’’ or
‘‘no cracks found’’ on the initial inspection;
and
(ii) Include a report only for ‘‘cracks
found’’ on the repetitive inspections.
(2) The report must include your name and
a contact phone number, the results of the
findings, a description of any cracking found,
the airplane serial number, and the total
number of hours TIS on the airplane. The
‘‘Lower Wing Spars and Skin Inspection
Report’’ included in Cessna Service Bulletin
MEB99–3 and MEB00–7 may be utilized for
this reporting requirement.
VerDate jul<14>2003
15:51 Mar 18, 2005
Jkt 205001
Does This AD Incorporate Any Material by
Reference?
(j) You must do the actions required by this
AD following the instructions in Cessna
Service Bulletin MEB99–3 (Model 402C) or
Cessna Service Bulletin MEB00–7 (Model
414A), both at Revision 2 and both dated
February 28, 2005. The Director of the
Federal Register approved the incorporation
by reference of this service bulletin in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. To get a copy of this service
information, contact Cessna Aircraft
Company, Product Support P.O. Box 7706,
Wichita, Kansas 67277; telephone: (316) 517–
5800; facsimile: (316) 942–9006. To review
copies of this service information, go to the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
PO 00000
Frm 00023
Fmt 4700
Sfmt 4700
Issued in Kansas City, Missouri, on March
11, 2005.
Nancy C. Lane,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–5382 Filed 3–18–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99–NE–41–AD; Amendment 39–
14015; AD 2005–06–07]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company (GE) CF6–80A1/A3
and CF6–80C2A Series Turbofan
Engines, Installed on Airbus Industrie
A300–600 and A310 Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD) for
GE CF6–80A1/A3 and CF6–80C2A
series turbofan engines. That AD
currently requires completing one of the
following actions before further flight:
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13366
Federal Register / Vol. 70, No. 53 / Monday, March 21, 2005 / Rules and Regulations
• Performing a directional pilot valve
(DPV) pressure check for leakage, and,
if necessary, replacing the DPV
assembly with a serviceable assembly,
or
• Replacing the DPV assembly with a
serviceable assembly, or
• Deactivating the thrust reverser, and
revising the FAA-approved airplane
flight manual (AFM) to require applying
performance penalties for certain takeoff
conditions if a thrust reverser is
deactivated.
That AD also requires revising the
Emergency Procedures Section of the
FAA-approved AFM to include a flight
crew operational procedure for use in
the event of any indication of an inflight thrust reverser deployment.
This AD specifies the same
requirements for leak checks, but
increases the interval between required
checks. This AD also removes the
requirement to revise the Limitations
Section and the Emergency Procedures
Section of the applicable AFM when
deactivating one or both thrust
reversers. This AD results from Airbus
Industrie, the airplane manufacturer,
revising the master minimum
equipment list (MMEL) to include
procedures for operating the airplane
with the thrust reversers deactivated,
and revising the AFM to include
procedures for emergency operation if
the thrust reversers deploy while in
flight. This AD also results from the
engine manufacturer recommending
extending the interval between
inspecting or replacing the DPV. We are
issuing this AD to prevent inadvertent
thrust reverser deployment, which, if it
occurs in-flight, could result in loss of
control of the airplane.
DATES: This AD becomes effective April
25, 2005. The Director of the Federal
Register approved the incorporation by
reference of certain publications listed
in the regulations as of April 25, 2005.
ADDRESSES: You can get the service
information identified in this AD from
Middle River Aircraft Systems, Mail
Point 46, 103 Chesapeake Park Plaza,
Baltimore, MD 21220, Attn: Product
Support Engineering; telephone (410)
682–0098, fax (410) 682–0100.
You may examine the AD docket at
the FAA, New England Region, Office of
the Regional Counsel, 12 New England
Executive Park, Burlington, MA.
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.
VerDate jul<14>2003
15:51 Mar 18, 2005
Jkt 205001
The FAA
proposed to amend 14 CFR part 39 with
a proposed AD. The proposed AD
applies to GE CF6–80A1/A3 and CF6–
80C2A series turbofan engines. We
published the proposed AD in the
Federal Register on July 29, 2004 (69 FR
45295). That action proposed the same
requirements for leak checks as the AD
being superseded, AD 99–18–19,
Amendment 39–11285 (64 FR 48277,
September 23, 1999), but would
increase the interval between required
checks.
SUPPLEMENTARY INFORMATION:
Examining the AD Docket
You may examine the AD Docket
(including any comments and service
information), by appointment, between
8 a.m. and 4:30 p.m., Monday through
Friday, except Federal holidays. See
ADDRESSES for the location.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Request That the AD Be Closed
One commenter requests that the AD
be closed instead of superseded. The
commenter states his airplanes have
never experienced a leaky DPV.
We do not agree. Although the
operator has not yet experienced any
leaks, the possibility still exists that a
DPV leak may occur. This type of leak
is a hidden failure that cannot be
detected at the system level, and could
result in inadvertent thrust reverser
deployment, which, if it occurs in-flight,
could result in loss of control of the
airplane. This superseding AD reflects
the favorable inspection results, by
extending the inspection interval.
Request To Address Alternative
Methods of Compliance (AMOCs)
One commenter requests that any
AMOCs issued under AD 99–18–19 be
addressed in the superseding AD. The
commenter states that it would be
beneficial if operators did not have to
submit new AMOC requests for
deviations or changes previously
approved by the FAA under AD 99–18–
19.
We agree that any known AMOCs
should be addressed in this superseding
AD. The two known AMOCs issued
under AD 99–18–19, however, are no
longer necessary under the superseding
AD. Any AMOCs that may have been
overlooked and are not made obsolete
by this superseding AD should be
brought to the attention of the FAA
Engine Certification Office.
PO 00000
Frm 00024
Fmt 4700
Sfmt 4700
Request for Increased Inspection
Interval
One commenter requests that an
increased inspection interval for engines
configured with the Third Line of
Defense (TLOD) system be included in
this superseding AD. The commenter
cites service bulletins issued by Airbus,
and an AD issued by the Direction
Generale de L’Aviation Civile (DGAC),
the airworthiness authority for France,
as substantiation for the interval
increase. The commenter acknowledges
that the DGAC AD does not affect U.S.
registered airplanes.
We do not agree. The FAA Engine
Certification Office has not yet approved
the increased interval for engines
configured with the TLOD system. The
DGAC AD referenced by the commenter,
AD 1999–242–289 R1, dated July 7,
2004, was subsequently cancelled by the
European Aviation Safety Agency
(EASA) with the issuance of AD 1999–
242–289 R2. This cancellation notice
stated that AD 1999–242–289 R1 was
replaced by FAA AD 99–18–19, as noted
on EASA cover document 2002–362–
IMP.
Request To Clarify the Reason for
Issuing a Superseding AD
In the proposed AD, we stated that the
proposed AD ‘‘results from revisions to
the manufacturer’s alert service
bulletins’’. We received an internal
request to clarify the reason for the
superseding AD. For clarification, we
have changed the final rule to state:
‘‘This AD results from Airbus
Industrie, the airplane manufacturer,
revising the master minimum
equipment list (MMEL) to include
procedures for operating the airplane
with the thrust reversers deactivated,
and revising the AFM to include
procedures for emergency operation if
the thrust reversers deploy while in
flight. This AD also results from the
engine manufacturer recommending
extending the interval between
inspecting or replacing the DPV.’’
Conclusion
We have carefully reviewed the
available data, including the comments
received, and determined that air safety
and the public interest require adopting
the AD with the changes described
previously. We have determined that
these changes will neither increase the
economic burden on any operator nor
increase the scope of the AD.
Costs of Compliance
There are about 544 engines of the
affected design in the worldwide fleet.
We estimate that 192 engines installed
on airplanes of U.S. registry will be
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Federal Register / Vol. 70, No. 53 / Monday, March 21, 2005 / Rules and Regulations
affected by this AD. We also estimate
that it will take about 1 work hour per
engine to perform the actions (about 227
per year), and that the average labor rate
is $65 per work hour. Required parts
will cost about $12,000 per engine. We
estimate that operators will replace 9
percent of the existing DPVs. Based on
these figures, we estimate the total cost
of the AD to U.S. operators to be
$259,915.
List of Subjects in 14 CFR Part 39
Authority for This Rulemaking
PART 39—AIRWORTHINESS
DIRECTIVES
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in subtitle VII,
part A, subpart III, section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
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.
For the reasons discussed above, I
certify that this AD:
(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.
We prepared a summary of the costs
to comply with this AD and placed it in
the AD Docket. You may get a copy of
this summary by sending a request to us
at the address listed under ADDRESSES.
Include ‘‘AD Docket No. 99–NE–41–
AD’’ in your request.
VerDate jul<14>2003
15:51 Mar 18, 2005
Jkt 205001
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends 14 CFR part 39 as follows:
I
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–11285 (64 FR
48277, September 23, 1999) and by
adding a new airworthiness directive,
Amendment 39–14015, to read as
follows:
I
2005–06–07 General Electric Company:
Amendment 39–14015. Docket No. 99–
NE–41–AD.
Effective Date
(a) This AD becomes effective April 25,
2005.
Affected ADs
(b) This AD supersedes AD 99–18–19,
Amendment 39–11285.
Applicability: (c) This AD applies to
General Electric Company (GE) CF6–80A1/
A3 and CF6–80C2A series turbofan engines.
These engines are installed on, but not
limited to, Airbus Industrie A300–600 and
A310 series airplanes.
Unsafe Condition
(d) This AD results from Airbus Industrie,
the airplane manufacturer, revising the
master minimum equipment list (MMEL) to
include procedures for operating the airplane
with the thrust reversers deactivated, and
revising the Airplane Flight Manual (AFM) to
include procedures for emergency operation
if the thrust reversers deploy while in flight.
This AD also results from the engine
manufacturer recommending extending the
interval between inspecting or replacing the
directional pilot valve (DPV). We are issuing
this AD to prevent inadvertent thrust reverser
deployment, which, if it occurs in-flight,
could result in loss of control of the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Credit for Initial Actions
(f) Performing the initial actions using
Middle River Aircraft Systems (MRAS) Alert
Service Bulletin (ASB) No. CF6–80A1/A3 SB
78A4022, Revision 2, dated September 17,
2003, or earlier revision or MRAS ASB No.
CF6–80C2A SB 78A1081, Revision 2, dated
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Frm 00025
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13367
September 17, 2003, or earlier revision,
satisfies the requirements of paragraphs (g)
and (i) of this AD.
GE CF6–80A1/A3
Actions
Series Engines Initial
(g) For GE CF6–80A1/A3 series engines, do
either paragraph (g)(1) or (g)(2) of this AD.
(1) Before further flight, perform a pressure
check of the DPV for leakage. Use 2.B.(1)
through 2.B.(12) of the Accomplishment
Instructions of MRAS ASB No. CF6–80A1/A3
SB 78A4022, Revision 2, dated September 17,
2003, and if necessary, do either of the
following:
(i) Replace the DPV assembly with a
serviceable assembly and perform an
operational check of the thrust reverser. Use
2.C.(1) through 2.C.(7) of the
Accomplishment Instructions of MRAS ASB
No. CF6–80A1/A3 SB 78A4022, Revision 2,
dated September 17, 2003, or
(ii) Deactivate the thrust reverser and do
the following:
(A) Replace the DPV with a serviceable
DPV within 10 calendar days.
(B) Perform an operational check of the
thrust reverser. Use 2.C.(1) through 2.C.(7) of
the Accomplishment Instructions of MRAS
ASB No. CF6–80A1/A3 SB 78A4022,
Revision 2, dated September 17, 2003.
(2) Before further flight, replace the DPV
assembly with a serviceable assembly, and
perform an operational check of the thrust
reverser. Use 2.C.(1) through 2.C.(7) of the
Accomplishment Instructions of MRAS ASB
No. CF6–80A1/A3 SB 78A4022, Revision 2,
dated September 17, 2003.
GE CF6–80A1/A3 Series Engines Repetitive
Actions
(h) For GE CF6–80A1/A3 series engines, do
either paragraph (h)(1) or (h)(2) of this AD
within 1,400 hours time-in-service (TIS)
since the last action.
(1) Perform a pressure check of the DPV for
leakage. Use 2.B.(1) through 2.B.(12) of the
Accomplishment Instructions of MRAS ASB
No. CF6–80A1/A3 SB 78A4022, Revision 2,
dated September 17, 2003, and if necessary,
do either of the following:
(i) Replace the DPV assembly with a
serviceable assembly and perform an
operational check of the thrust reverser. Use
2.C.(1) through 2.C.(7) of the
Accomplishment Instructions of MRAS ASB
No. CF6–80A1/A3 SB 78A4022, Revision 2,
dated September 17, 2003, or
(ii) Deactivate the thrust reverser and do
the following:
(A) Replace the DPV with a serviceable
DPV within 10 calendar days.
(B) Perform an operational check of the
thrust reverser. Use 2.C.(1) through 2.C.(7) of
the Accomplishment Instructions of MRAS
ASB No. CF6–80A1/A3 SB 78A4022,
Revision 2, dated September 17, 2003.
(2) Replace the DPV assembly with a
serviceable assembly, and perform an
operational check of the thrust reverser. Use
2.C.(1) through 2.C.(7) of the
Accomplishment Instructions of MRAS ASB
No. CF6–80A1/A3 SB 78A4022, Revision 2,
dated September 17, 2003.
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Federal Register / Vol. 70, No. 53 / Monday, March 21, 2005 / Rules and Regulations
GE CF6–80C2A Series Engines Initial
Actions
(i) For GE CF6–80C2A series engines, do
either paragraph (i)(1) or (i)(2) of this AD.
(1) Before further flight, perform a pressure
check of the DPV for leakage. Use 2.B.(1)
through 2.B.(12) of the Accomplishment
Instructions of MRAS ASB No. CF6–80C2A
SB 78A1081, Revision 2, dated September 17,
2003, and if necessary, do either of the
following:
(i) Replace the DPV assembly with a
serviceable assembly and perform an
operational check of the thrust reverser. Use
2.C.(1) through 2.C.(5) of the
Accomplishment Instructions of MRAS ASB
No. CF6–80C2A SB 78A1081, Revision 2,
dated September 17, 2003, or
(ii) Deactivate the thrust reverser and do
the following:
(A) Replace the DPV with a serviceable
DPV within 10 calendar days.
(B) Perform an operational check of the
thrust reverser. Use 2.C.(1) through 2.C.(5) of
the Accomplishment Instructions of MRAS
ASB No. CF6–80C2A SB 78A1081, Revision
2, dated September 17, 2003.
(2) Before further flight, replace the DPV
assembly with a serviceable assembly, and
perform an operational check of the thrust
reverser. Use 2.C.(1) through 2.C.(5) of the
Accomplishment Instructions of MRAS ASB
No. CF6–80C2A SB 78A4022, Revision 2,
dated September 17, 2003.
GE CF6–80C2A Series Engines Repetitive
Actions
(j) For GE CF6–80C2A series engines, do
either (j)(1) or (j)(2) of this AD within 1,400
hours TIS since the last action.
(1) Perform a pressure check of the DPV for
leakage. Use 2.B.(1) through 2.B.(12) of the
Accomplishment Instructions of MRAS ASB
No. CF6–80C2A SB 78A1081, Revision 2,
dated September 17, 2003, and if necessary,
do either of the following:
(i) Replace the DPV assembly with a
serviceable assembly and perform an
operational check of the thrust reverser. Use
2.C.(1) through 2.C.(5) of the
Accomplishment Instructions of MRAS ASB
No. CF6–80C2A SB 78A1081, Revision 2,
dated September 17, 2003, or
(ii) Deactivate the thrust reverser and do
the following:
(A) Replace the DPV with a serviceable
DPV within 10 calendar days.
(B) Perform an operational check of the
thrust reverser. Use 2.C.(1) through 2.C.(5) of
the Accomplishment Instructions of MRAS
ASB No. CF6–80C2A SB 78A1081, Revision
2, dated September 17, 2003.
(2) Replace the DPV assembly with a
serviceable assembly, and perform an
operational check of the thrust reverser. Use
2.C.(1) through 2.C.(5) of the
Accomplishment Instructions of MRAS ASB
No. CF6–80C2A SB 78A1081, Revision 2,
dated September 17, 2003.
Definition of Serviceable DPV Assembly
(k) For the purpose of this AD, a
serviceable DPV assembly is:
(1) An assembly that has accumulated zero
time in service, or
(2) An assembly that has accumulated zero
time in service after having passed the tests
in the MRAS Component Maintenance
Manual GEK 85007 (78–31–51), Revision No.
6 or later, Directional Pilot Valve, Page Block
101, Testing and Troubleshooting, or
(3) An assembly that has been successfully
leak checked using Paragraph 2.B. of the
Accomplishment Instructions of MRAS ASB
No. 78A4022, Revision 2, dated September
17, 2003, or earlier revision, or ASB No.
78A1081, Revision 2, dated September 17,
2003, or earlier revision, as applicable,
immediately before installation on the
airplane.
Alternative Methods of Compliance
(l) The Manager, Engine Certification
Office, has the authority to approve
alternative methods of compliance for this
AD, if requested, using the procedures found
in 14 CFR 39.19.
Material Incorporated by Reference
(m) You must use the Middle River Aircraft
Systems (MRAS) Alert Service Bulletins
(ASB) listed in Table 1 of this AD to perform
the actions required by this AD. The Director
of the Federal Register approved the
incorporation by reference of the documents
listed in Table 1 of this AD in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51. You
can get a copy from Middle River Aircraft
Systems, Mail Point 46, 103 Chesapeake Park
Plaza, Baltimore, MD 21220, Attn: Product
Support Engineering; telephone (410) 682–
0098, fax (410) 682–0100. You can review
copies at the FAA, New England Region,
Office of the Regional Counsel, 12 New
England Executive Park, Burlington, MA; or
at the National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Table 1 follows:
TABLE 1.—INCORPORATION BY REFERENCE
Middle River Aircraft Systems ASB No.
Page number(s)
shown on the page
78A4022, Total pages: 18 ...........................................................................................
78A1081, Total pages: 18 ...........................................................................................
Revision
level
shown on
the page
Date shown on the
page
2
2
September 17, 2003.
September 17, 2003.
ALL ............................
ALL ............................
Related Information
DEPARTMENT OF TRANSPORTATION
(n) None.
Issued in Burlington, Massachusetts, on
March 9, 2005.
Francis A. Favara,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 05–5299 Filed 3–18–05; 8:45 am]
BILLING CODE 4910–13–P
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2004–19493; Directorate
Identifier 2004–NM–69–AD; Amendment 39–
14018; AD 2005–06–10]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 767–200, –300, and –300F Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
VerDate jul<14>2003
15:51 Mar 18, 2005
Jkt 205001
PO 00000
Frm 00026
Fmt 4700
Sfmt 4700
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Boeing Model 767–200, –300, and
–300F series airplanes. This AD requires
replacing the inboard fairing seal
common to the vapor barrier seal of
each strut assembly. This AD is
prompted by discovery during
production that a section of vapor
barrier seal was missing from the spar
web cavities of the upper aft struts of
both wings. We are issuing this AD to
prevent flammable fluids from leaking
onto parts of a hot exhaust system of a
shut-down engine of an airplane on the
ground, which could result in ignition
of the flammable fluids and an
uncontained fire. This could also lead to
an emergency evacuation of the airplane
and possible injury to passengers.
E:\FR\FM\21MRR1.SGM
21MRR1
]]>Agencies
[Federal Register Volume 70, Number 53 (Monday, March 21, 2005)]
[Rules and Regulations]
[Pages 13365-13368]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-5299]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NE-41-AD; Amendment 39-14015; AD 2005-06-07]
RIN 2120-AA64
Airworthiness Directives; General Electric Company (GE) CF6-80A1/
A3 and CF6-80C2A Series Turbofan Engines, Installed on Airbus Industrie
A300-600 and A310 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for GE CF6-80A1/A3 and CF6-80C2A series turbofan engines. That AD
currently requires completing one of the following actions before
further flight:
[[Page 13366]]
Performing a directional pilot valve (DPV) pressure check
for leakage, and, if necessary, replacing the DPV assembly with a
serviceable assembly, or
Replacing the DPV assembly with a serviceable assembly, or
Deactivating the thrust reverser, and revising the FAA-
approved airplane flight manual (AFM) to require applying performance
penalties for certain takeoff conditions if a thrust reverser is
deactivated.
That AD also requires revising the Emergency Procedures Section of
the FAA-approved AFM to include a flight crew operational procedure for
use in the event of any indication of an in-flight thrust reverser
deployment.
This AD specifies the same requirements for leak checks, but
increases the interval between required checks. This AD also removes
the requirement to revise the Limitations Section and the Emergency
Procedures Section of the applicable AFM when deactivating one or both
thrust reversers. This AD results from Airbus Industrie, the airplane
manufacturer, revising the master minimum equipment list (MMEL) to
include procedures for operating the airplane with the thrust reversers
deactivated, and revising the AFM to include procedures for emergency
operation if the thrust reversers deploy while in flight. This AD also
results from the engine manufacturer recommending extending the
interval between inspecting or replacing the DPV. We are issuing this
AD to prevent inadvertent thrust reverser deployment, which, if it
occurs in-flight, could result in loss of control of the airplane.
DATES: This AD becomes effective April 25, 2005. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of April 25, 2005.
ADDRESSES: You can get the service information identified in this AD
from Middle River Aircraft Systems, Mail Point 46, 103 Chesapeake Park
Plaza, Baltimore, MD 21220, Attn: Product Support Engineering;
telephone (410) 682-0098, fax (410) 682-0100.
You may examine the AD docket at the FAA, New England Region,
Office of the Regional Counsel, 12 New England Executive Park,
Burlington, MA.
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: The FAA proposed to amend 14 CFR part 39
with a proposed AD. The proposed AD applies to GE CF6-80A1/A3 and CF6-
80C2A series turbofan engines. We published the proposed AD in the
Federal Register on July 29, 2004 (69 FR 45295). That action proposed
the same requirements for leak checks as the AD being superseded, AD
99-18-19, Amendment 39-11285 (64 FR 48277, September 23, 1999), but
would increase the interval between required checks.
Examining the AD Docket
You may examine the AD Docket (including any comments and service
information), by appointment, between 8 a.m. and 4:30 p.m., Monday
through Friday, except Federal holidays. See ADDRESSES for the
location.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Request That the AD Be Closed
One commenter requests that the AD be closed instead of superseded.
The commenter states his airplanes have never experienced a leaky DPV.
We do not agree. Although the operator has not yet experienced any
leaks, the possibility still exists that a DPV leak may occur. This
type of leak is a hidden failure that cannot be detected at the system
level, and could result in inadvertent thrust reverser deployment,
which, if it occurs in-flight, could result in loss of control of the
airplane. This superseding AD reflects the favorable inspection
results, by extending the inspection interval.
Request To Address Alternative Methods of Compliance (AMOCs)
One commenter requests that any AMOCs issued under AD 99-18-19 be
addressed in the superseding AD. The commenter states that it would be
beneficial if operators did not have to submit new AMOC requests for
deviations or changes previously approved by the FAA under AD 99-18-19.
We agree that any known AMOCs should be addressed in this
superseding AD. The two known AMOCs issued under AD 99-18-19, however,
are no longer necessary under the superseding AD. Any AMOCs that may
have been overlooked and are not made obsolete by this superseding AD
should be brought to the attention of the FAA Engine Certification
Office.
Request for Increased Inspection Interval
One commenter requests that an increased inspection interval for
engines configured with the Third Line of Defense (TLOD) system be
included in this superseding AD. The commenter cites service bulletins
issued by Airbus, and an AD issued by the Direction Generale de
L'Aviation Civile (DGAC), the airworthiness authority for France, as
substantiation for the interval increase. The commenter acknowledges
that the DGAC AD does not affect U.S. registered airplanes.
We do not agree. The FAA Engine Certification Office has not yet
approved the increased interval for engines configured with the TLOD
system. The DGAC AD referenced by the commenter, AD 1999-242-289 R1,
dated July 7, 2004, was subsequently cancelled by the European Aviation
Safety Agency (EASA) with the issuance of AD 1999-242-289 R2. This
cancellation notice stated that AD 1999-242-289 R1 was replaced by FAA
AD 99-18-19, as noted on EASA cover document 2002-362-IMP.
Request To Clarify the Reason for Issuing a Superseding AD
In the proposed AD, we stated that the proposed AD ``results from
revisions to the manufacturer's alert service bulletins''. We received
an internal request to clarify the reason for the superseding AD. For
clarification, we have changed the final rule to state:
``This AD results from Airbus Industrie, the airplane manufacturer,
revising the master minimum equipment list (MMEL) to include procedures
for operating the airplane with the thrust reversers deactivated, and
revising the AFM to include procedures for emergency operation if the
thrust reversers deploy while in flight. This AD also results from the
engine manufacturer recommending extending the interval between
inspecting or replacing the DPV.''
Conclusion
We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
There are about 544 engines of the affected design in the worldwide
fleet. We estimate that 192 engines installed on airplanes of U.S.
registry will be
[[Page 13367]]
affected by this AD. We also estimate that it will take about 1 work
hour per engine to perform the actions (about 227 per year), and that
the average labor rate is $65 per work hour. Required parts will cost
about $12,000 per engine. We estimate that operators will replace 9
percent of the existing DPVs. Based on these figures, we estimate the
total cost of the AD to U.S. operators to be $259,915.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
subtitle VII, part A, subpart III, section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will 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.
For the reasons discussed above, I certify that this AD:
(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.
We prepared a summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary by
sending a request to us at the address listed under ADDRESSES. Include
``AD Docket No. 99-NE-41-AD'' in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration amends 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. The FAA amends Sec. 39.13 by removing Amendment 39-11285 (64 FR
48277, September 23, 1999) and by adding a new airworthiness directive,
Amendment 39-14015, to read as follows:
2005-06-07 General Electric Company: Amendment 39-14015. Docket No.
99-NE-41-AD.
Effective Date
(a) This AD becomes effective April 25, 2005.
Affected ADs
(b) This AD supersedes AD 99-18-19, Amendment 39-11285.
Applicability: (c) This AD applies to General Electric Company
(GE) CF6-80A1/A3 and CF6-80C2A series turbofan engines. These
engines are installed on, but not limited to, Airbus Industrie A300-
600 and A310 series airplanes.
Unsafe Condition
(d) This AD results from Airbus Industrie, the airplane
manufacturer, revising the master minimum equipment list (MMEL) to
include procedures for operating the airplane with the thrust
reversers deactivated, and revising the Airplane Flight Manual (AFM)
to include procedures for emergency operation if the thrust
reversers deploy while in flight. This AD also results from the
engine manufacturer recommending extending the interval between
inspecting or replacing the directional pilot valve (DPV). We are
issuing this AD to prevent inadvertent thrust reverser deployment,
which, if it occurs in-flight, could result in loss of control of
the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Credit for Initial Actions
(f) Performing the initial actions using Middle River Aircraft
Systems (MRAS) Alert Service Bulletin (ASB) No. CF6-80A1/A3 SB
78A4022, Revision 2, dated September 17, 2003, or earlier revision
or MRAS ASB No. CF6-80C2A SB 78A1081, Revision 2, dated September
17, 2003, or earlier revision, satisfies the requirements of
paragraphs (g) and (i) of this AD.
GE CF6-80A1/A3 Series Engines Initial Actions
(g) For GE CF6-80A1/A3 series engines, do either paragraph
(g)(1) or (g)(2) of this AD.
(1) Before further flight, perform a pressure check of the DPV
for leakage. Use 2.B.(1) through 2.B.(12) of the Accomplishment
Instructions of MRAS ASB No. CF6-80A1/A3 SB 78A4022, Revision 2,
dated September 17, 2003, and if necessary, do either of the
following:
(i) Replace the DPV assembly with a serviceable assembly and
perform an operational check of the thrust reverser. Use 2.C.(1)
through 2.C.(7) of the Accomplishment Instructions of MRAS ASB No.
CF6-80A1/A3 SB 78A4022, Revision 2, dated September 17, 2003, or
(ii) Deactivate the thrust reverser and do the following:
(A) Replace the DPV with a serviceable DPV within 10 calendar
days.
(B) Perform an operational check of the thrust reverser. Use
2.C.(1) through 2.C.(7) of the Accomplishment Instructions of MRAS
ASB No. CF6-80A1/A3 SB 78A4022, Revision 2, dated September 17,
2003.
(2) Before further flight, replace the DPV assembly with a
serviceable assembly, and perform an operational check of the thrust
reverser. Use 2.C.(1) through 2.C.(7) of the Accomplishment
Instructions of MRAS ASB No. CF6-80A1/A3 SB 78A4022, Revision 2,
dated September 17, 2003.
GE CF6-80A1/A3 Series Engines Repetitive Actions
(h) For GE CF6-80A1/A3 series engines, do either paragraph
(h)(1) or (h)(2) of this AD within 1,400 hours time-in-service (TIS)
since the last action.
(1) Perform a pressure check of the DPV for leakage. Use 2.B.(1)
through 2.B.(12) of the Accomplishment Instructions of MRAS ASB No.
CF6-80A1/A3 SB 78A4022, Revision 2, dated September 17, 2003, and if
necessary, do either of the following:
(i) Replace the DPV assembly with a serviceable assembly and
perform an operational check of the thrust reverser. Use 2.C.(1)
through 2.C.(7) of the Accomplishment Instructions of MRAS ASB No.
CF6-80A1/A3 SB 78A4022, Revision 2, dated September 17, 2003, or
(ii) Deactivate the thrust reverser and do the following:
(A) Replace the DPV with a serviceable DPV within 10 calendar
days.
(B) Perform an operational check of the thrust reverser. Use
2.C.(1) through 2.C.(7) of the Accomplishment Instructions of MRAS
ASB No. CF6-80A1/A3 SB 78A4022, Revision 2, dated September 17,
2003.
(2) Replace the DPV assembly with a serviceable assembly, and
perform an operational check of the thrust reverser. Use 2.C.(1)
through 2.C.(7) of the Accomplishment Instructions of MRAS ASB No.
CF6-80A1/A3 SB 78A4022, Revision 2, dated September 17, 2003.
[[Page 13368]]
GE CF6-80C2A Series Engines Initial Actions
(i) For GE CF6-80C2A series engines, do either paragraph (i)(1)
or (i)(2) of this AD.
(1) Before further flight, perform a pressure check of the DPV
for leakage. Use 2.B.(1) through 2.B.(12) of the Accomplishment
Instructions of MRAS ASB No. CF6-80C2A SB 78A1081, Revision 2, dated
September 17, 2003, and if necessary, do either of the following:
(i) Replace the DPV assembly with a serviceable assembly and
perform an operational check of the thrust reverser. Use 2.C.(1)
through 2.C.(5) of the Accomplishment Instructions of MRAS ASB No.
CF6-80C2A SB 78A1081, Revision 2, dated September 17, 2003, or
(ii) Deactivate the thrust reverser and do the following:
(A) Replace the DPV with a serviceable DPV within 10 calendar
days.
(B) Perform an operational check of the thrust reverser. Use
2.C.(1) through 2.C.(5) of the Accomplishment Instructions of MRAS
ASB No. CF6-80C2A SB 78A1081, Revision 2, dated September 17, 2003.
(2) Before further flight, replace the DPV assembly with a
serviceable assembly, and perform an operational check of the thrust
reverser. Use 2.C.(1) through 2.C.(5) of the Accomplishment
Instructions of MRAS ASB No. CF6-80C2A SB 78A4022, Revision 2, dated
September 17, 2003.
GE CF6-80C2A Series Engines Repetitive Actions
(j) For GE CF6-80C2A series engines, do either (j)(1) or (j)(2)
of this AD within 1,400 hours TIS since the last action.
(1) Perform a pressure check of the DPV for leakage. Use 2.B.(1)
through 2.B.(12) of the Accomplishment Instructions of MRAS ASB No.
CF6-80C2A SB 78A1081, Revision 2, dated September 17, 2003, and if
necessary, do either of the following:
(i) Replace the DPV assembly with a serviceable assembly and
perform an operational check of the thrust reverser. Use 2.C.(1)
through 2.C.(5) of the Accomplishment Instructions of MRAS ASB No.
CF6-80C2A SB 78A1081, Revision 2, dated September 17, 2003, or
(ii) Deactivate the thrust reverser and do the following:
(A) Replace the DPV with a serviceable DPV within 10 calendar
days.
(B) Perform an operational check of the thrust reverser. Use
2.C.(1) through 2.C.(5) of the Accomplishment Instructions of MRAS
ASB No. CF6-80C2A SB 78A1081, Revision 2, dated September 17, 2003.
(2) Replace the DPV assembly with a serviceable assembly, and
perform an operational check of the thrust reverser. Use 2.C.(1)
through 2.C.(5) of the Accomplishment Instructions of MRAS ASB No.
CF6-80C2A SB 78A1081, Revision 2, dated September 17, 2003.
Definition of Serviceable DPV Assembly
(k) For the purpose of this AD, a serviceable DPV assembly is:
(1) An assembly that has accumulated zero time in service, or
(2) An assembly that has accumulated zero time in service after
having passed the tests in the MRAS Component Maintenance Manual GEK
85007 (78-31-51), Revision No. 6 or later, Directional Pilot Valve,
Page Block 101, Testing and Troubleshooting, or
(3) An assembly that has been successfully leak checked using
Paragraph 2.B. of the Accomplishment Instructions of MRAS ASB No.
78A4022, Revision 2, dated September 17, 2003, or earlier revision,
or ASB No. 78A1081, Revision 2, dated September 17, 2003, or earlier
revision, as applicable, immediately before installation on the
airplane.
Alternative Methods of Compliance
(l) The Manager, Engine Certification Office, has the authority
to approve alternative methods of compliance for this AD, if
requested, using the procedures found in 14 CFR 39.19.
Material Incorporated by Reference
(m) You must use the Middle River Aircraft Systems (MRAS) Alert
Service Bulletins (ASB) listed in Table 1 of this AD to perform the
actions required by this AD. The Director of the Federal Register
approved the incorporation by reference of the documents listed in
Table 1 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part
51. You can get a copy from Middle River Aircraft Systems, Mail
Point 46, 103 Chesapeake Park Plaza, Baltimore, MD 21220, Attn:
Product Support Engineering; telephone (410) 682-0098, fax (410)
682-0100. You can review copies at the FAA, New England Region,
Office of the Regional Counsel, 12 New England Executive Park,
Burlington, MA; or at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: https://
www.archives.gov/federal_register/code_of_federal_regulations/
ibr_locations.html.
Table 1 follows:
Table 1.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
Revision
Middle River Aircraft Systems ASB level
No. Page number(s) shown on the page shown on Date shown on the page
the page
----------------------------------------------------------------------------------------------------------------
78A4022, Total pages: 18.......... ALL............................. 2 September 17, 2003.
78A1081, Total pages: 18.......... ALL............................. 2 September 17, 2003.
----------------------------------------------------------------------------------------------------------------
Related Information
(n) None.
Issued in Burlington, Massachusetts, on March 9, 2005.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 05-5299 Filed 3-18-05; 8:45 am]
BILLING CODE 4910-13-P
