Airworthiness Directives; General Electric Company CF34-1A, -3A, -3A1, -3A2, -3B, and -3B1 Series Turbofan Engines, 52043-52046 [05-17400]
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Federal Register / Vol. 70, No. 169 / Thursday, September 1, 2005 / Proposed Rules
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 regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket. See the ADDRESSES section
for a location to examine the regulatory
evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Alternative Methods of Compliance
(AMOCs)
(h) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
Related Information
(i) Swedish airworthiness directive 1–198,
dated February 14, 2005, also addresses the
subject of this AD.
Issued in Renton, Washington, on August
24, 2005.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 05–17404 Filed 8–31–05; 8:45 am]
BILLING CODE 4910–13–P
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
Actions Accomplished Previously
(g) A modification accomplished before the
effective date of this AD in accordance with
Saab Service Bulletin 2000–61–006, dated
December 20, 2004, is acceptable for
compliance with paragraph (f) of this AD.
[Amended]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
14 CFR Part 39
Saab Aircraft AB: Docket No. FAA–2005–
22255; Directorate Identifier 2005–NM–
106–AD.
[Docket No. FAA–2004–18648; Directorate
Identifier 2004–NE–26–AD]
RIN 2120–AA64
Comments Due Date
(a) The FAA must receive comments on
this AD action by October 3, 2005.
Affected ADs
(b) None.
Airworthiness Directives; General
Electric Company CF34–1A, –3A, –3A1,
–3A2, –3B, and –3B1 Series Turbofan
Engines
AGENCY:
Applicability
(c) This AD applies to SAAB Model SAAB
2000 airplanes, certificated in any category,
serial numbers –004 through –063 inclusive.
Unsafe Condition
(d) This AD results from reports of in-flight
engine shutdown caused by uncommanded
operation of the feather pump of the
propeller. We are issuing this AD to prevent
uncommanded feathering of the propeller,
which could result in the shutdown of an
engine during flight and consequent reduced
controllability 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.
Modification
(f) Within 12 months after the effective
date of this AD, modify the manual featherand-unfeather system of the propellers by
doing all actions specified in the
Accomplishment Instructions of Saab Service
Bulletin 2000–61–006, Revision 01, dated
February 17, 2005.
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Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that was issued for
General Electric Company (GE) CF34–
3A1 and –3B1 series turbofan engines
with certain part numbers (P/Ns) and
serial numbers (SNs) of stage 5 low
pressure turbine (LPT) disks and stage 6
LPT disks. These engines are installed
in Bombardier Canadair CL600–2B19
Regional Jet (RJ) airplanes. This
proposed AD would add SNs to the
affected disk population for RJ
airplanes. This proposed AD would also
add GE CF34–1 and –3 series turbofan
engines with certain P/Ns and SNs of
stage 5 LPT disks and stage 6 LPT disks,
to the applicability section. These
engines are installed in Bombardier
Canadair models CL–600–2A12 (CL–
601), CL–600–2B16 (CL–601–3A), (CL–
601–3R), and (CL–604) Business Jet (BJ)
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52043
airplanes. This proposed AD would
require initial and repetitive visual and
eddy current inspections (ECI) of the
affected disk population. This proposed
AD would also allow replacement of
those disks as optional terminating
action to the repetitive inspections.
Also, this proposed AD would require
eventual replacement of the affected
disks as terminating action to the
repetitive inspections. This proposed
AD results from the discovery of
additional suspect stage 5 LPT disks and
stage 6 LPT disks. These disks could fail
due to low-cycle fatigue cracking that
may start at the site of an electrical arcout on the disk. We are proposing this
AD to prevent low-cycle-fatigue (LCF)
failure of stage 5 LPT disks and stage 6
LPT disks, which could lead to
uncontained engine failure.
DATES: We must receive any comments
on this proposed AD by October 31,
2005.
ADDRESSES: Use one of the following
addresses to comment on this proposed
AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• Fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Contact GE Aircraft Engines, 1000
Western Avenue, Lynn, MA 01910;
Attention: CF34 Product Support
Engineering, Mail Zone: 34017;
telephone (781) 594–6323; fax (781)
594–0600, for the service information
identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Tara
Fitzgerald, Aerospace Engineer, Engine
Certification Office, FAA, Engine and
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803–
5299; telephone (781) 238–7130; fax
(781) 238–7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments
regarding this proposal. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
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Federal Register / Vol. 70, No. 169 / Thursday, September 1, 2005 / Proposed Rules
2004–18648; Directorate Identifier
2004–NE–26–AD’’ in the subject line of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the proposed AD. We will
consider all comments received by the
closing date and may amend the
proposed AD in light of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this proposed AD.
Using the search function of the Docket
Management System (DMS) Web site,
anyone can find and read the comments
in any of our dockets, including the
name of the individual who sent the
comment (or signed the comment on
behalf of an association, business, labor
union, etc.). You may review the DOT’s
complete Privacy Act Statement in the
Federal Register published on April 11,
2000 (65 FR 19477–78) or you may visit
https://dms.dot.gov.
Examining the AD Docket
You may examine the docket that
contains the proposal, any comments
received and any final disposition in
person at the DMS Docket Offices
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Office (telephone (800) 647–
5227) is located on the plaza level of the
Department of Transportation Nassif
Building at the street address stated in
ADDRESSES. Comments will be available
in the AD docket shortly after the DMS
receives them.
Discussion
On August 9, 2004, the FAA issued
AD 2004–15–03R1, Amendment 39–
13773 (69 FR 50299, August 16, 2004).
That AD requires initial and repetitive
visual inspections and ECIs of certain
SNs of stage 5 LPT disks, P/N
6078T92P01, and certain SNs of stage 6
LPT disks, P/N 6078T89P01, installed in
GE CF34–3A1 and –3B1 series turbofan
engines that power certain Bombardier
Canadair RJ airplanes. That AD also
allows replacement of those SN disks as
an optional terminating action to the
repetitive inspections. Also, that AD
requires replacement of certain stage 5
and stage 6 LPT disks. That AD was the
result of an LCF failure of a stage 5 LPT
disk that occurred during factory
testing. GE performed a metallurgical
evaluation of the disk. The evaluation
showed that the origin of the LCF failure
was a disk crack caused by inadvertent
contact with electrochemical etch
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probes. These probes were used to
match-mark components during engine
assembly. GE’s evaluation concluded
that the probe contact caused damage
known as electrical arc-out. Electrical
arc-out damage can lead to crack
initiation and subsequent LCF failure of
the disk. That AD also resulted from the
discovery that an incorrect part number
for stage 6 LPT disks was published in
the existing AD and recognition of the
need to allow credit for actions
completed per previous releases of GE
Alert Service Bulletin (ASB) No. CF34–
AL S/B 72–A0173. That electrical arcout damage condition, if not corrected,
could result in LCF failure of stage 5
LPT disks and stage 6 LPT disks, and
lead to uncontained engine failure.
Actions Since AD 2004–15–03R1 Was
Issued
Since we issued AD 2004–15–03R1,
GE identified additional suspect stage 5
LPT disks, P/Ns 4922T16P01,
5024T53P01, 5024T53P02, and
6078T92P01, and stage 6 LPT disks, P/
Ns 4922T17P01, 5023T45P03,
5023T45P04, and 6078T89P01, that
might have the same arc-out indications.
These disks are installed in GE CF34–
1A, –3A, –3A1, –3A2, –3B, and –3B1
series turbofan engines that power
Bombardier Canadair BJ and RJ
airplanes. GE has issued ASBs to
address these additional suspect disks.
Relevant Service Information
We have reviewed and approved the
technical contents of GE ASB No. CF34–
AL S/B 72–A0173, Revision 05, dated
May 24, 2005, and GE ASB No. CF34–
BJ S/B 72–A0148, Revision 02, dated
May 24, 2005. These SBs identify the
suspect disks by serial number, and
describe procedures for initial and
repetitive visual inspections and ECIs
and eventual replacement of those
disks.
Differences Between the Proposed AD
and the Manufacturer’s Service
Information
GE ASB No. CF34–AL S/B 72–A0173,
Revision 05, dated May 24, 2005, and
GE ASB No. CF34–BJ S/B 72–A0148,
Revision 02, dated May 24, 2005,
require visually inspecting for electrical
arc out indications around the match
marks on stage 3 disk arms and stage 4
disk arms. This proposed AD would not
mandate these inspections, as the stage
3 disks and stage 4 disks are not part of
the suspect population.
FAA’s Determination and Requirements
of the Proposed AD
We have evaluated all pertinent
information and identified an unsafe
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condition that is likely to exist or
develop on other products of this same
type design. For that reason, we are
proposing this AD, which would require
initial and repetitive visual inspections
and ECIs of suspect disks and eventual
replacement of those disks. The
proposed AD would require that you do
these actions using the service
information described previously.
Costs of Compliance
There are about 973 GE CF34–3A1
and –3B1 series turbofan engines
installed in Bombardier Canadair RJ
airplanes in the worldwide fleet and 683
of those engines are installed on
airplanes of U.S. registry. We estimate
that 355 of those engines would be
affected by this proposed AD. There are
about 970 CF34–1A, –3A, –3A1, –3A2,
and –3B series turbofan engines
installed in Bombardier Canadair BJ
airplanes in the worldwide fleet and 690
of those engines are installed on
airplanes of U.S. registry. We estimate
that 249 of those engines would be
affected by this proposed AD. We also
estimate that it would take about 70
work hours per engine to perform the
proposed disk inspections when the
LPT module is exposed in the shop, and
about 94 work hours per engine to
perform the proposed disk inspections
when the LPT module is forced offwing. We also estimate that the average
labor rate is $65 per work hour. Prorated
stage 5 LPT disks would cost about
$42,650 (RJ), and $71,083 (BJ) per
engine and prorated stage 6 LPT disks
would cost about $30,110 (RJ) and
$50,183 (BJ) per engine. We also
estimate that about 24 stage 5 LPT disks
and about 24 stage 6 LPT disks would
be found with the arc-out condition and
require replacement. Based on these
figures, we estimate the total cost of the
proposed AD to U.S. operators to be
$14,409,772.
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD 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.
For the reasons discussed above, I
certify that the proposed regulation:
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
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Federal Register / Vol. 70, No. 169 / Thursday, September 1, 2005 / Proposed Rules
3. Would 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 regulatory evaluation
of the estimated costs to comply with
this proposed AD. See the ADDRESSES
section for a location to examine the
regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Under the authority delegated to me
by the Administrator, the Federal
Aviation Administration proposes to
amend 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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 13773 (69 FR
50299, August 16, 2004) and by adding
a new airworthiness directive,
Amendment 39–XXXXX, to read as
follows:
General Electric Company: Docket No. FAA–
2004–18648; Directorate Identifier 2004–
NE–26–AD.
Comments Due Date
(a) The Federal Aviation Administration
(FAA) must receive comments on this
airworthiness directive (AD) action by
October 31, 2005.
Affected ADs
(b) This AD supersedes AD 2004–15–03R1,
Amendment 39–13773.
Applicability
(c) This AD applies to the following two
groups of engine models:
(1) General Electric Company (GE) CF34–
3A1 and –3B1 series turbofan engines with
stage 5 low pressure turbine (LPT) disks, part
number (P/N) 6078T92P01 or stage 6 LPT
disks P/N 6078T89P01, or both, with serial
numbers (SNs) listed in Figure 3 or Figure 4
of GE Alert Service Bulletin (ASB) No. CF34–
AL S/B 72–A0173, Revision 05, dated May
24, 2005. These engines are installed on
Bombardier Canadair CL600–2B19 Regional
Jet (RJ) airplanes.
(2) GE CF34–1A, –3A, –3A1, –3A2, and
–3B series turbofan engines with stage 5 LPT
disks P/N 4922T16P01, 5024T53P01,
5024T53P02, or 6078T92P01 or stage 6 LPT
disks P/Ns 4922T17P01, 5023T45P03,
5023T45P04, or 6078T89P01, or both, with
SNs listed in Figure 3 or Figure 4 of GE ASB
52045
No. CF34–BJ S/B 72–A0148, Revision 02,
dated May 24, 2005. These engines are
installed on Bombardier Canadair Models
CL–600–2A12 (CL–601), CL–600–2B16 (CL–
601–3A), (CL–601–3R), and (CL–604)
Business Jet (BJ) airplanes.
Unsafe Condition
(d) This AD results from the discovery of
an additional population of suspect stage 5
LPT disks and stage 6 LPT disks that could
fail due to low-cycle fatigue cracking that
may start at the site of an electrical arc-out
on the disk.
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.
Initial Inspection or Replacement
(f) Using the compliance schedule in Table
1 of this AD, do the following:
(1) For engines installed in Bombardier
Canadair RJ airplanes, if a stage 5 LPT disk
or stage 6 LPT disk listed in Figure 3 of GE
ASB No. CF34–AL S/B 72–A0173, Revision
05, dated May 24, 2005 or listed in any
previous issue of ASB No. CF34–AL S/B 72–
A0173 did not complete a visual inspection
and eddy current inspection (ECI) using
paragraphs 3.C.(1) through 3.D.(2) and
paragraphs 3.E. through 3.E.(6) of the
Accomplishment Instructions of that SB
before June 1, 2005, then replace that disk at
the next piece-part exposure.
TABLE 1.—COMPLIANCE SCHEDULE
On the effective date of this AD, if the disk has:
Then perform the actions defined in paragraph (f) of this AD at next
piece-part exposure, not to exceed the accumulation of:
(i) 14,750 or more cycles-since-new (CSN) and has not been fluorescent penetrant inspected (FPI) at an earlier piece-part exposure.
(ii) 14,750 or more CSN and has been FPI at an earlier piece-part exposure..
(iii) 14,500 or more CSN but fewer than 14,750 CSN .............................
(iv) 14,250 or more CSN but fewer than 14,500 CSN .............................
(v) 13,000 or more CSN but fewer than 14,250 CSN .............................
(vi) 2,500 or more CSN but fewer than 13,000 CSN ...............................
An additional 250 cycles-in-service (CIS) after the effective date of this
AD
An additional 500 CIS after the effective date of this AD
(vii) Fewer than 2,500 cycles-since-new (CSN) .......................................
(2) For engines installed in Bombardier
Canadair BJ airplanes, perform an initial
visual inspection and ECI of stage 5 LPT
disks and stage 6 LPT disks listed in Figure
3 of GE ASB No. CF34–BJ S/B 72–A0148,
Revision 02, dated May 24, 2005, before
January 1, 2010. Use paragraphs 3.C.(1)
through 3.D.(2) and paragraphs 3.E. through
3.E.(6) of Accomplishment Instructions of GE
ASB No. CF34–BJ S/B 72–A0148, Revision
02, dated May 24, 2005 to do the inspections.
Repetitive Inspections
(g) For engines installed in Bombardier
Canadair RJ airplanes with stage 5 LPT disks
and stage 6 LPT disks listed in Figure 3 of
GE ASB No. CF34–AL S/B 72–A0173,
Revision 05, dated May 24, 2005, that were
initially visually inspected and ECI’ed before
June 1, 2005, do the following:
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An additional 500 CIS after the effective date of this AD.
An additional 750 CIS after the effective date of this AD.
An additional 1,000 CIS after the effective date of this AD.
An additional 4,000 CIS after the effective date of this AD, or 14,000
CSN, whichever comes first.
6,500 CSN.
(1) Perform repetitive visual inspections
and ECIs within every 3,100 cycles-sincelast-inspection (CSLI), until the life limit of
the disk is reached.
(2) Use paragraphs 3.C.(1) through 3.D.(2)
and paragraphs 3.E. through 3.E.(6) of
Accomplishment Instructions of GE ASB No.
CF34–AL S/B 72–A0173, Revision 05, dated
May 24, 2005 to do the inspections.
(h) For engines installed in Bombardier
Canadair BJ airplanes, with stage 5 LPT disks
and stage 6 LPT disks initially inspected as
specified in paragraph (f)(2) of this AD, do
the following:
(1) Perform repetitive visual inspections
and ECIs within every 3,100
CSLI, until the life limit of the disk is
reached.
(2) Use paragraphs 3.C.(1) through 3.D.(2)
and paragraphs 3.E. through 3.E.(6) of
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Accomplishment Instructions of GE ASB No.
CF34–BJ S/B 72–A0148, Revision 02, dated
May 24, 2005, to do the inspections.
Disks That Pass Inspection
(i) Reinstall disks that pass the inspections
in paragraphs (f), (g), and (h) of this AD into
the same LPT module from which they were
removed.
LPT Stage 5 and Stage 6 Disk Removal
(j) Remove any disk from service if there
is an arc-out found on that disk.
(k) At the next piece-part exposure for
engines installed in Bombardier Canadair RJ
airplanes, remove from service stage 5 LPT
disks and stage 6 LPT disks listed in Figure
4 of GE ASB No. CF34–AL S/B 72–A0173,
Revision 05, dated May 24, 2005.
(l) At the next piece-part exposure for
engines installed in Bombardier Canadair BJ
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airplanes, remove from service stage 5 LPT
disks and stage 6 LPT disks listed in Figure
4 of GE ASB No. CF34–BJ S/B 72–A0148
Revision 02, dated May 24, 2005.
Optional Terminating Action
(m) Replacement of an affected stage 5 LPT
disk or affected stage 6 LPT disk, with a disk
not listed in Figure 3 or Figure 4 of GE ASB
No. CF34–AL S/B 72–A0173 Revision 05,
dated May 24, 2005 or not listed in Figure
3 or Figure 4 of GE ASB No. CF34–BJ S/B 72–
A0148, Revision 02, dated May 24, 2005 is
terminating action to the repetitive
inspections and removals required by this
AD for that disk.
Terminating Action
(n) As terminating action to the repetitive
inspections and removals in this AD, replace
all disks by January 1, 2013 that are listed in
Figure 3 and Figure 4 of GE ASB No. CF34–
AL S/B 72–A0173, Revision 05, dated May
24, 2005, and that are listed in Figure 3 and
Figure 4 of GE ASB No. CF34-BJ 72–A0148,
Revision 02, dated May 24, 2005.
Actions Completed Per Previous Releases of
Alert Service Bulletins
(o) Actions completed before the effective
date of this AD using GE ASB No. CF34–AL
S/B 72–A0173, dated April 2, 2004; or
Revision 01, dated May 20, 2004; or Revision
02, dated June 22, 2004; or Revision 03, dated
July 20, 2004; or Revision 04, dated February
7, 2005; or GE ASB No. CF34–BJ S/B 72–
A0148, dated September 2, 2004; or Revision
01, dated March 10, 2005, are considered
acceptable for compliance with the
corresponding action in this AD.
Serviceable LPT Disk Definition
(p) For the purpose of this AD, a
serviceable LPT disk is a disk not listed in
Figure 3 or Figure 4 of GE ASB No. CF34–
AL S/B 72–A0173 Revision 05, dated May 24,
2005, or Figure 3 or Figure 4 of GE ASB No.
CF34–BJ 72–A0148, Revision 02, dated May
24, 2005.
Piece-Part Exposure Definitions
(q) For the purpose of this AD, the
definition of piece part exposure for the stage
5 LPT disk is when the disk is separated from
the forward and aft bolted joints.
(r) For the purpose of this AD, the
definition of piece part exposure for the stage
6 LPT disk is when the disk is separated from
the forward bolted joint.
Replacement Engine or Replacement LPT
Module Definition
(s) For the purpose of this AD, the
definition of a replacement engine or
replacement LPT module is an engine or LPT
module that does not have installed any of
the suspect disks listed in Figure 3 or Figure
4 of GE ASB No. CF34–AL S/B 72–A0173
Revision 05, dated May 24, 2005, or Figure
3 or Figure 4 of GE ASB No. CF34–BJ 72–
A0148, Revision 02, dated May 24, 2005.
Alternative Methods of Compliance
(t) 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.
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Related Information
(u) GE ASB No. CF34–AL S/B 72–A0178
and ASB No. CF34–BJ S/B 72–A0152 contain
the information necessary to identify and
inspect the suspect disks that are the subject
of this AD.
Issued in Burlington, Massachusetts, on
August 26, 2005.
Jay J. Pardee,
Manager, Engine and Propeller Directorate,
Aircraft Certification Service.
[FR Doc. 05–17400 Filed 8–31–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–22254; Directorate
Identifier 2005–NM–001–AD]
RIN 2120–AA64
Airworthiness Directives; McDonnell
Douglas Model DC–9–10, DC–9–20,
DC–9–30, DC–9–40, and DC–9–50
Series Airplanes; McDonnell Douglas
Model DC–9–81 (MD–81), DC–9–82
(MD–82), DC–9–83 (MD–83), and DC–9–
87 (MD–87) Airplanes; McDonnell
Douglas Model MD–88 Airplanes;
McDonnell Douglas Model MD–90–30
Airplanes; and McDonnell Douglas
Model 717–200 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain McDonnell Douglas transport
category airplanes. This proposed AD
would require an inspection to
determine the part number of the upper
and lower stop pad support fittings of
all the lower cargo doors, repetitive
inspections of all early configuration
stop pad support fittings, and corrective
action if necessary. This proposed AD
would also provide an optional
terminating action for the repetitive
inspections. This proposed AD is
prompted by a report of cracks found in
the area of the upper and lower stop pad
support fittings of the cargo door pan on
numerous airplanes. We are proposing
this AD to prevent cracks in the cargo
door pan, which could result in the
inability to fully pressurize an airplane
and possible rapid decompression of the
airplane.
DATES: We must receive comments on
this proposed AD by October 17, 2005.
PO 00000
Frm 00010
Fmt 4702
Sfmt 4702
Use one of the following
addresses to submit comments on this
proposed AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street SW., Nassif Building,
room PL–401, Washington, DC 20590.
• By fax: (202) 493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in
this proposed AD, contact Boeing
Commercial Airplanes, Long Beach
Division, 3855 Lakewood Boulevard,
Long Beach, California 90846,
Attention: Data and Service
Management, Dept. C1–L5A (D800–
0024).
You can examine the contents of this
AD docket on the Internet at https://
dms.dot.gov, or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street
SW., room PL–401, on the plaza level of
the Nassif Building, Washington, DC.
This docket number is FAA–2005–
22254; the directorate identifier for this
docket is 2005–NM–001–AD.
FOR FURTHER INFORMATION CONTACT:
Maureen Moreland, Aerospace
Engineer, Airframe Branch, ANM–120L,
FAA, Los Angeles Aircraft Certification
Office, 3960 Paramount Boulevard,
Lakewood, California 90712–4137;
telephone (562) 627–5238; fax (562)
627–5210.
SUPPLEMENTARY INFORMATION:
ADDRESSES:
Comments Invited
We invite you to submit any relevant
written data, views, or arguments
regarding this proposed AD. Send your
comments to an address listed under
ADDRESSES. Include ‘‘Docket No. FAA–
2005–22254; Directorate Identifier
2005–NM–001–AD’’ in the subject line
of your comments. We specifically
invite comments on the overall
regulatory, economic, environmental,
and energy aspects of the proposed AD.
We will consider all comments
submitted by the closing date and may
amend the proposed AD in light of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
E:\FR\FM\01SEP1.SGM
01SEP1
]]>Agencies
[Federal Register Volume 70, Number 169 (Thursday, September 1, 2005)]
[Proposed Rules]
[Pages 52043-52046]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-17400]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-18648; Directorate Identifier 2004-NE-26-AD]
RIN 2120-AA64
Airworthiness Directives; General Electric Company CF34-1A, -3A,
-3A1, -3A2, -3B, and -3B1 Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that was issued for General Electric Company (GE) CF34-
3A1 and -3B1 series turbofan engines with certain part numbers (P/Ns)
and serial numbers (SNs) of stage 5 low pressure turbine (LPT) disks
and stage 6 LPT disks. These engines are installed in Bombardier
Canadair CL600-2B19 Regional Jet (RJ) airplanes. This proposed AD would
add SNs to the affected disk population for RJ airplanes. This proposed
AD would also add GE CF34-1 and -3 series turbofan engines with certain
P/Ns and SNs of stage 5 LPT disks and stage 6 LPT disks, to the
applicability section. These engines are installed in Bombardier
Canadair models CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A), (CL-601-
3R), and (CL-604) Business Jet (BJ) airplanes. This proposed AD would
require initial and repetitive visual and eddy current inspections
(ECI) of the affected disk population. This proposed AD would also
allow replacement of those disks as optional terminating action to the
repetitive inspections. Also, this proposed AD would require eventual
replacement of the affected disks as terminating action to the
repetitive inspections. This proposed AD results from the discovery of
additional suspect stage 5 LPT disks and stage 6 LPT disks. These disks
could fail due to low-cycle fatigue cracking that may start at the site
of an electrical arc-out on the disk. We are proposing this AD to
prevent low-cycle-fatigue (LCF) failure of stage 5 LPT disks and stage
6 LPT disks, which could lead to uncontained engine failure.
DATES: We must receive any comments on this proposed AD by October 31,
2005.
ADDRESSES: Use one of the following addresses to comment on this
proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-0001.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact GE Aircraft Engines, 1000 Western Avenue, Lynn, MA 01910;
Attention: CF34 Product Support Engineering, Mail Zone: 34017;
telephone (781) 594-6323; fax (781) 594-0600, for the service
information identified in this proposed AD.
FOR FURTHER INFORMATION CONTACT: Tara Fitzgerald, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (781)
238-7130; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-
[[Page 52044]]
2004-18648; Directorate Identifier 2004-NE-26-AD'' in the subject line
of your comments. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the proposed
AD. We will consider all comments received by the closing date and may
amend the proposed AD in light of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of the
Docket Management System (DMS) Web site, anyone can find and read the
comments in any of our dockets, including the name of the individual
who sent the comment (or signed the comment on behalf of an
association, business, labor union, etc.). You may review the DOT's
complete Privacy Act Statement in the Federal Register published on
April 11, 2000 (65 FR 19477-78) or you may visit https://dms.dot.gov.
Examining the AD Docket
You may examine the docket that contains the proposal, any comments
received and any final disposition in person at the DMS Docket Offices
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Office (telephone (800) 647-5227) is located on
the plaza level of the Department of Transportation Nassif Building at
the street address stated in ADDRESSES. Comments will be available in
the AD docket shortly after the DMS receives them.
Discussion
On August 9, 2004, the FAA issued AD 2004-15-03R1, Amendment 39-
13773 (69 FR 50299, August 16, 2004). That AD requires initial and
repetitive visual inspections and ECIs of certain SNs of stage 5 LPT
disks, P/N 6078T92P01, and certain SNs of stage 6 LPT disks, P/N
6078T89P01, installed in GE CF34-3A1 and -3B1 series turbofan engines
that power certain Bombardier Canadair RJ airplanes. That AD also
allows replacement of those SN disks as an optional terminating action
to the repetitive inspections. Also, that AD requires replacement of
certain stage 5 and stage 6 LPT disks. That AD was the result of an LCF
failure of a stage 5 LPT disk that occurred during factory testing. GE
performed a metallurgical evaluation of the disk. The evaluation showed
that the origin of the LCF failure was a disk crack caused by
inadvertent contact with electrochemical etch probes. These probes were
used to match-mark components during engine assembly. GE's evaluation
concluded that the probe contact caused damage known as electrical arc-
out. Electrical arc-out damage can lead to crack initiation and
subsequent LCF failure of the disk. That AD also resulted from the
discovery that an incorrect part number for stage 6 LPT disks was
published in the existing AD and recognition of the need to allow
credit for actions completed per previous releases of GE Alert Service
Bulletin (ASB) No. CF34-AL S/B 72-A0173. That electrical arc-out damage
condition, if not corrected, could result in LCF failure of stage 5 LPT
disks and stage 6 LPT disks, and lead to uncontained engine failure.
Actions Since AD 2004-15-03R1 Was Issued
Since we issued AD 2004-15-03R1, GE identified additional suspect
stage 5 LPT disks, P/Ns 4922T16P01, 5024T53P01, 5024T53P02, and
6078T92P01, and stage 6 LPT disks, P/Ns 4922T17P01, 5023T45P03,
5023T45P04, and 6078T89P01, that might have the same arc-out
indications. These disks are installed in GE CF34-1A, -3A, -3A1, -3A2,
-3B, and -3B1 series turbofan engines that power Bombardier Canadair BJ
and RJ airplanes. GE has issued ASBs to address these additional
suspect disks.
Relevant Service Information
We have reviewed and approved the technical contents of GE ASB No.
CF34-AL S/B 72-A0173, Revision 05, dated May 24, 2005, and GE ASB No.
CF34-BJ S/B 72-A0148, Revision 02, dated May 24, 2005. These SBs
identify the suspect disks by serial number, and describe procedures
for initial and repetitive visual inspections and ECIs and eventual
replacement of those disks.
Differences Between the Proposed AD and the Manufacturer's Service
Information
GE ASB No. CF34-AL S/B 72-A0173, Revision 05, dated May 24, 2005,
and GE ASB No. CF34-BJ S/B 72-A0148, Revision 02, dated May 24, 2005,
require visually inspecting for electrical arc out indications around
the match marks on stage 3 disk arms and stage 4 disk arms. This
proposed AD would not mandate these inspections, as the stage 3 disks
and stage 4 disks are not part of the suspect population.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other products
of this same type design. For that reason, we are proposing this AD,
which would require initial and repetitive visual inspections and ECIs
of suspect disks and eventual replacement of those disks. The proposed
AD would require that you do these actions using the service
information described previously.
Costs of Compliance
There are about 973 GE CF34-3A1 and -3B1 series turbofan engines
installed in Bombardier Canadair RJ airplanes in the worldwide fleet
and 683 of those engines are installed on airplanes of U.S. registry.
We estimate that 355 of those engines would be affected by this
proposed AD. There are about 970 CF34-1A, -3A, -3A1, -3A2, and -3B
series turbofan engines installed in Bombardier Canadair BJ airplanes
in the worldwide fleet and 690 of those engines are installed on
airplanes of U.S. registry. We estimate that 249 of those engines would
be affected by this proposed AD. We also estimate that it would take
about 70 work hours per engine to perform the proposed disk inspections
when the LPT module is exposed in the shop, and about 94 work hours per
engine to perform the proposed disk inspections when the LPT module is
forced off-wing. We also estimate that the average labor rate is $65
per work hour. Prorated stage 5 LPT disks would cost about $42,650
(RJ), and $71,083 (BJ) per engine and prorated stage 6 LPT disks would
cost about $30,110 (RJ) and $50,183 (BJ) per engine. We also estimate
that about 24 stage 5 LPT disks and about 24 stage 6 LPT disks would be
found with the arc-out condition and require replacement. Based on
these figures, we estimate the total cost of the proposed AD to U.S.
operators to be $14,409,772.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD 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.
For the reasons discussed above, I certify that the proposed
regulation:
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
[[Page 52045]]
3. Would 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 regulatory evaluation of the estimated costs to
comply with this proposed AD. See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Under the authority delegated to me by the Administrator, the
Federal Aviation Administration proposes to amend 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. The FAA amends Sec. 39.13 by removing Amendment 13773 (69 FR
50299, August 16, 2004) and by adding a new airworthiness directive,
Amendment 39-XXXXX, to read as follows:
General Electric Company: Docket No. FAA-2004-18648; Directorate
Identifier 2004-NE-26-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by October 31,
2005.
Affected ADs
(b) This AD supersedes AD 2004-15-03R1, Amendment 39-13773.
Applicability
(c) This AD applies to the following two groups of engine
models:
(1) General Electric Company (GE) CF34-3A1 and -3B1 series
turbofan engines with stage 5 low pressure turbine (LPT) disks, part
number (P/N) 6078T92P01 or stage 6 LPT disks P/N 6078T89P01, or
both, with serial numbers (SNs) listed in Figure 3 or Figure 4 of GE
Alert Service Bulletin (ASB) No. CF34-AL S/B 72-A0173, Revision 05,
dated May 24, 2005. These engines are installed on Bombardier
Canadair CL600-2B19 Regional Jet (RJ) airplanes.
(2) GE CF34-1A, -3A, -3A1, -3A2, and -3B series turbofan engines
with stage 5 LPT disks P/N 4922T16P01, 5024T53P01, 5024T53P02, or
6078T92P01 or stage 6 LPT disks P/Ns 4922T17P01, 5023T45P03,
5023T45P04, or 6078T89P01, or both, with SNs listed in Figure 3 or
Figure 4 of GE ASB No. CF34-BJ S/B 72-A0148, Revision 02, dated May
24, 2005. These engines are installed on Bombardier Canadair Models
CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A), (CL-601-3R), and (CL-
604) Business Jet (BJ) airplanes.
Unsafe Condition
(d) This AD results from the discovery of an additional
population of suspect stage 5 LPT disks and stage 6 LPT disks that
could fail due to low-cycle fatigue cracking that may start at the
site of an electrical arc-out on the disk.
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.
Initial Inspection or Replacement
(f) Using the compliance schedule in Table 1 of this AD, do the
following:
(1) For engines installed in Bombardier Canadair RJ airplanes,
if a stage 5 LPT disk or stage 6 LPT disk listed in Figure 3 of GE
ASB No. CF34-AL S/B 72-A0173, Revision 05, dated May 24, 2005 or
listed in any previous issue of ASB No. CF34-AL S/B 72-A0173 did not
complete a visual inspection and eddy current inspection (ECI) using
paragraphs 3.C.(1) through 3.D.(2) and paragraphs 3.E. through
3.E.(6) of the Accomplishment Instructions of that SB before June 1,
2005, then replace that disk at the next piece-part exposure.
Table 1.--Compliance Schedule
------------------------------------------------------------------------
Then perform the actions
defined in paragraph (f) of
On the effective date of this AD, if this AD at next piece-part
the disk has: exposure, not to exceed the
accumulation of:
------------------------------------------------------------------------
(i) 14,750 or more cycles-since-new An additional 250 cycles-in-
(CSN) and has not been fluorescent service (CIS) after the
penetrant inspected (FPI) at an effective date of this AD
earlier piece-part exposure.
(ii) 14,750 or more CSN and has been An additional 500 CIS after the
FPI at an earlier piece-part exposure.. effective date of this AD
(iii) 14,500 or more CSN but fewer than An additional 500 CIS after the
14,750 CSN. effective date of this AD.
(iv) 14,250 or more CSN but fewer than An additional 750 CIS after the
14,500 CSN. effective date of this AD.
(v) 13,000 or more CSN but fewer than An additional 1,000 CIS after
14,250 CSN. the effective date of this AD.
(vi) 2,500 or more CSN but fewer than An additional 4,000 CIS after
13,000 CSN. the effective date of this AD,
or 14,000 CSN, whichever comes
first.
(vii) Fewer than 2,500 cycles-since-new 6,500 CSN.
(CSN).
------------------------------------------------------------------------
(2) For engines installed in Bombardier Canadair BJ airplanes,
perform an initial visual inspection and ECI of stage 5 LPT disks
and stage 6 LPT disks listed in Figure 3 of GE ASB No. CF34-BJ S/B
72-A0148, Revision 02, dated May 24, 2005, before January 1, 2010.
Use paragraphs 3.C.(1) through 3.D.(2) and paragraphs 3.E. through
3.E.(6) of Accomplishment Instructions of GE ASB No. CF34-BJ S/B 72-
A0148, Revision 02, dated May 24, 2005 to do the inspections.
Repetitive Inspections
(g) For engines installed in Bombardier Canadair RJ airplanes
with stage 5 LPT disks and stage 6 LPT disks listed in Figure 3 of
GE ASB No. CF34-AL S/B 72-A0173, Revision 05, dated May 24, 2005,
that were initially visually inspected and ECI'ed before June 1,
2005, do the following:
(1) Perform repetitive visual inspections and ECIs within every
3,100 cycles-since-last-inspection (CSLI), until the life limit of
the disk is reached.
(2) Use paragraphs 3.C.(1) through 3.D.(2) and paragraphs 3.E.
through 3.E.(6) of Accomplishment Instructions of GE ASB No. CF34-AL
S/B 72-A0173, Revision 05, dated May 24, 2005 to do the inspections.
(h) For engines installed in Bombardier Canadair BJ airplanes,
with stage 5 LPT disks and stage 6 LPT disks initially inspected as
specified in paragraph (f)(2) of this AD, do the following:
(1) Perform repetitive visual inspections and ECIs within every
3,100
CSLI, until the life limit of the disk is reached.
(2) Use paragraphs 3.C.(1) through 3.D.(2) and paragraphs 3.E.
through 3.E.(6) of Accomplishment Instructions of GE ASB No. CF34-BJ
S/B 72-A0148, Revision 02, dated May 24, 2005, to do the
inspections.
Disks That Pass Inspection
(i) Reinstall disks that pass the inspections in paragraphs (f),
(g), and (h) of this AD into the same LPT module from which they
were removed.
LPT Stage 5 and Stage 6 Disk Removal
(j) Remove any disk from service if there is an arc-out found on
that disk.
(k) At the next piece-part exposure for engines installed in
Bombardier Canadair RJ airplanes, remove from service stage 5 LPT
disks and stage 6 LPT disks listed in Figure 4 of GE ASB No. CF34-AL
S/B 72-A0173, Revision 05, dated May 24, 2005.
(l) At the next piece-part exposure for engines installed in
Bombardier Canadair BJ
[[Page 52046]]
airplanes, remove from service stage 5 LPT disks and stage 6 LPT
disks listed in Figure 4 of GE ASB No. CF34-BJ S/B 72-A0148 Revision
02, dated May 24, 2005.
Optional Terminating Action
(m) Replacement of an affected stage 5 LPT disk or affected
stage 6 LPT disk, with a disk not listed in Figure 3 or Figure 4 of
GE ASB No. CF34-AL S/B 72-A0173 Revision 05, dated May 24, 2005 or
not listed in Figure 3 or Figure 4 of GE ASB No. CF34-BJ S/B 72-
A0148, Revision 02, dated May 24, 2005 is terminating action to the
repetitive inspections and removals required by this AD for that
disk.
Terminating Action
(n) As terminating action to the repetitive inspections and
removals in this AD, replace all disks by January 1, 2013 that are
listed in Figure 3 and Figure 4 of GE ASB No. CF34-AL S/B 72-A0173,
Revision 05, dated May 24, 2005, and that are listed in Figure 3 and
Figure 4 of GE ASB No. CF34-BJ 72-A0148, Revision 02, dated May 24,
2005.
Actions Completed Per Previous Releases of Alert Service Bulletins
(o) Actions completed before the effective date of this AD using
GE ASB No. CF34-AL S/B 72-A0173, dated April 2, 2004; or Revision
01, dated May 20, 2004; or Revision 02, dated June 22, 2004; or
Revision 03, dated July 20, 2004; or Revision 04, dated February 7,
2005; or GE ASB No. CF34-BJ S/B 72-A0148, dated September 2, 2004;
or Revision 01, dated March 10, 2005, are considered acceptable for
compliance with the corresponding action in this AD.
Serviceable LPT Disk Definition
(p) For the purpose of this AD, a serviceable LPT disk is a disk
not listed in Figure 3 or Figure 4 of GE ASB No. CF34-AL S/B 72-
A0173 Revision 05, dated May 24, 2005, or Figure 3 or Figure 4 of GE
ASB No. CF34-BJ 72-A0148, Revision 02, dated May 24, 2005.
Piece-Part Exposure Definitions
(q) For the purpose of this AD, the definition of piece part
exposure for the stage 5 LPT disk is when the disk is separated from
the forward and aft bolted joints.
(r) For the purpose of this AD, the definition of piece part
exposure for the stage 6 LPT disk is when the disk is separated from
the forward bolted joint.
Replacement Engine or Replacement LPT Module Definition
(s) For the purpose of this AD, the definition of a replacement
engine or replacement LPT module is an engine or LPT module that
does not have installed any of the suspect disks listed in Figure 3
or Figure 4 of GE ASB No. CF34-AL S/B 72-A0173 Revision 05, dated
May 24, 2005, or Figure 3 or Figure 4 of GE ASB No. CF34-BJ 72-
A0148, Revision 02, dated May 24, 2005.
Alternative Methods of Compliance
(t) 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.
Related Information
(u) GE ASB No. CF34-AL S/B 72-A0178 and ASB No. CF34-BJ S/B 72-
A0152 contain the information necessary to identify and inspect the
suspect disks that are the subject of this AD.
Issued in Burlington, Massachusetts, on August 26, 2005.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 05-17400 Filed 8-31-05; 8:45 am]
BILLING CODE 4910-13-P
