Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Tay 611-8, Tay 620-15, Tay 650-15, and Tay 651-54 Series Turbofan Engines, 3936-3939 [E7-1218]
Download as PDF
<![CDATA[
3936
Federal Register / Vol. 72, No. 18 / Monday, January 29, 2007 / Rules and Regulations
by adding the following new
airworthiness directive (AD):
2007–02–24 Boeing: Amendment 39–14911.
Docket No. FAA–2006–24410;
Directorate Identifier 2005–NM–261–AD.
Effective Date
(a) This AD becomes effective March 5,
2007.
Modification
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Boeing Model
747–100, 747–100B, 747–100B SUD, 747–
200B, 747–200C, 747–200F, 747–300, 747–
400, 747–400D, 747–400F, 747SR, and 747SP
series airplanes, certificated in any category.
Unsafe Condition
(d) This AD results from analysis by the
manufacturer that the radial lap splices of the
station (STA) 2360 aft pressure bulkhead are
subject to widespread fatigue damage. We are
issuing this AD to detect and correct cracking
of the bulkhead web at multiple sites along
the radial lap splice, which could join
together to form cracks of critical length, and
result in rapid decompression and 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.
rmajette on PROD1PC67 with RULES
Repetitive Inspections
(f) Before the airplane accumulates 28,000
total flight cycles, or within 18 months after
the effective date of this AD, whichever
occurs later: Do a high-frequency eddy
current inspection for cracking of the web of
the STA 2360 aft pressure bulkhead around
the fastener heads in the critical fastener
rows in the web lap joints, from the Y-chord
to the inner ring; in accordance with Part 2,
‘‘Access and Inspection,’’ of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 747–53A2561, dated
September 22, 2005. It is not necessary to
inspect the web lap joints in the areas
common to the Y-ring outer chord. Repeat
the inspection thereafter at intervals not to
exceed 2,000 flight cycles until the
modification in paragraph (h) of this AD is
done.
Repair
(g) If any cracking is found during any
inspection required by paragraph (f) of this
AD: Before further flight, do the applicable
action in paragraph (g)(1) or (g)(2) of this AD.
(1) If the cracking is within certain limits
specified in Boeing Alert Service Bulletin
747–53A2561, dated September 22, 2005
(referencing the structural repair manual), do
the repair in accordance with the
Accomplishment Instructions of the alert
service bulletin.
(2) If the cracking is more than certain
limits specified in Boeing Alert Service
Bulletin 747–53A2561, dated September 22,
2005, or if the alert service bulletin specifies
to ask Boeing for repair data: Repair the
VerDate Aug<31>2005
14:38 Jan 26, 2007
Jkt 211001
cracking using a method approved by the
Manager, Seattle Aircraft Certification Office
(ACO), FAA. For a repair method to be
approved by the Manager, Seattle ACO, as
required by this paragraph, the Manager’s
approval letter must specifically refer to this
AD.
(h) Before the airplane accumulates 35,000
total flight cycles or within 18 months after
the effective date of this AD, whichever
occurs later: Modify the aft pressure
bulkhead using a method approved by the
Manager, Seattle ACO. For a repair method
to be approved by the Manager, Seattle ACO,
as required by this paragraph, the Manager’s
approval letter must specifically refer to this
AD. Doing this modification terminates the
repetitive inspection requirements of
paragraph (f) of this AD.
Note 1: As of the effective date of this AD,
the manufacturer has not informed us of any
intent to produce the required terminating
modification; however, the regulations do not
prevent others from doing so.
Alternative Methods of Compliance
(AMOCs)
(i)(1) The Manager, Seattle ACO, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
Material Incorporated by Reference
(j) You must use Boeing Alert Service
Bulletin 747–53A2561, dated September 22,
2005, to perform the actions that are required
by this AD, unless the AD specifies
otherwise. The Director of the Federal
Register approved the incorporation by
reference of this document in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Boeing Commercial Airplanes, P.O.
Box 3707, Seattle, Washington 98124–2207,
for a copy of this service information. You
may review copies at the Docket Management
Facility, U.S. Department of Transportation,
400 Seventh Street, SW., Room PL–401,
Nassif Building, Washington, DC; on the
Internet at https://dms.dot.gov; or at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at the NARA,
call (202) 741–6030, or go to https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on January
19, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–1212 Filed 1–26–07; 8:45 am]
BILLING CODE 4910–13–P
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–24777; Directorate
Identifier 2006–NE–19–AD; Amendment
39–14913; AD 2007–03–02]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
Deutschland Ltd & Co KG Tay 611–8,
Tay 620–15, Tay 650–15, and Tay
651–54 Series Turbofan Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for RollsRoyce Deutschland Ltd & Co KG (RRD)
Tay 611–8, Tay 620–15, Tay 650–15,
and Tay 651–54 series turbofan engines,
with certain low pressure (LP)
compressor modules installed. This AD
requires an ultrasonic inspection (UI) of
LP compressor fan blades for cracks,
within 30 days after the effective date of
the AD on certain serial number (SN)
Tay 650–15 engines. This AD also
requires initial and repetitive UIs of LP
compressor fan blades on all engines.
This AD also requires, for Tay 650–15
and Tay 651–54 engines, UIs of LP
compressor fan blades whenever the
blade set is removed from one engine
and installed on a different engine. This
AD results from a report that a set of LP
compressor fan blades failed before
reaching the LP compressor fan blade
full published life limit. We are issuing
this AD to prevent LP compressor fan
blades from failing due to blade root
cracks, leading to uncontained engine
failure and damage to the airplane.
DATES: This AD becomes effective
March 5, 2007. The Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in the regulations as
of March 5, 2007.
ADDRESSES: You can get the service
information identified in this AD from
Rolls-Royce Deutschland Ltd & Co KG,
Eschenweg 11, D–15827 Dahlewitz,
Germany; telephone 49 (0) 33–7086–
1768; fax 49 (0) 33–7086–3356.
You may examine the AD docket on
the Internet at https://dms.dot.gov or in
Room PL–401 on the plaza level of the
Nassif Building, 400 Seventh Street,
SW., Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Jason Yang, Aerospace Engineer, Engine
Certification Office, FAA, Engine and
Propeller Directorate, 12 New England
E:\FR\FM\29JAR1.SGM
29JAR1
Federal Register / Vol. 72, No. 18 / Monday, January 29, 2007 / Rules and Regulations
Executive Park, Burlington, MA 01803;
telephone (781) 238–7747; fax (781)
238–7199.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
a proposed AD. The proposed AD
applies to RRD Tay 611–8, Tay 620–15,
Tay 650–15, and Tay 651–54 series
turbofan engines, with certain low
pressure (LP) compressor modules
installed. We published the proposed
AD in the Federal Register on June 27,
2006 (71 FR 36493). That action
proposed to require a UI of LP
compressor fan blades for cracks, within
30 days after the effective date of the AD
on certain serial number (SN) Tay 650–
15 engines. That action also proposed to
require repetitive UIs of LP compressor
fan blades on all engines. That action
also proposed to require, for Tay 650–
15 and Tay 651–54 engines, UIs of LP
compressor fan blades whenever the
blade set is removed from one engine
and installed on a different engine.
Examining the AD Docket
You may examine the docket that
contains the AD, any comments
received, and any final disposition in
person at the Docket Management
Facility 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.
rmajette on PROD1PC67 with RULES
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
RRD Request To Change Compliance
Paragraphs (h)(1) and (h)(2)
RRD requests that we change the
compliance schedule for Tay 650–15
and Tay 651–54 engines in proposed AD
paragraph (h)(1), from ‘‘at every shop
visit for any reason or before reaching
every 4,000 flight hours-since-last fan
blade UI, whichever occurs first’’ to ‘‘at
every engine shop visit for any reason
or before reaching every 10,000 flight
hours-since-last fan blade UI, whichever
occurs first.’’
RRD also requests that we change the
compliance schedule for Tay 620–15
engines in proposed AD paragraph
(h)(2) from ‘‘before reaching every 8,000
flight hours but no later than every 10
years since-last-fan-blade UI, whichever
occurs first’’ to ‘‘before reaching every
10,000 flight hours for airline operation,
VerDate Aug<31>2005
14:38 Jan 26, 2007
Jkt 211001
and before reaching 8,000 flight hours
but no later than every 10 years sincelast-fan-blade UI, whichever occurs first,
for non-airline operation.’’ RRD bases
these changes on their Engine
Management Program.
We agree with the intent of the
requested changes to proposed AD
paragraph (h)(1). We changed that
paragraph, and added subparagraphs to
clarify the initial inspection
requirements in the AD. Regarding
paragraph (h)(2), we do not agree with
having different inspection schedules
for airline and non-airline operations.
However, we changed paragraph (h)(2)
to paragraph (h)(2)(iii), to read ‘‘before
reaching every 10,000 flight hours but
no later than every 10 years since-lastfan-blade UI, whichever occurs first’’.
We feel that this drawdown schedule
will take care of both low- and highutilization of Tay 620–15 engines.
Air Transport Association Request To
Change Compliance Paragraph (h)(1)
Air Transport Association (ATA)
requests that we change the compliance
schedule in paragraph (h)(1) from ‘‘at
every engine shop visit for any reason
or before reaching every 4,000 flight
hours-since-last fan blade UI, whichever
occurs first’’ to ‘‘at every engine shop
visit for any reason or before reaching
every 12 years or 15,000 flight hourssince-last fan blade UI, whichever
occurs first’’. ATA states that this
schedule is described in the Engine
Management Program for Tay 651–54
engines installed in the Boeing 727
airplanes. We do not agree. The intent
of proposed AD paragraph (h)(1) is to UI
Tay 650–15 and Tay 651–54 engines at
all scheduled and unscheduled shop
visits, using RRD SB No. TAY–72–1442,
Revision 3, dated November 26, 2003.
Also, the intent of the paragraph is to
parallel the SB requirement of an initial
UI within 3 months after the SB issue
date. We did change paragraph (h) and
added subparagraphs as described
under the first comment above.
Request To Change Compliance
Paragraph (h)(3)
One commenter requests that we
change the Tay 611–8 compliance
schedule in proposed AD paragraph
(h)(3). The commenter requests that we
call out an initial UI inspection to be
done at the next engine mid-life or
overhaul inspection after the effective
date of this AD. The commenter also
requests that we call out repetitive UI
inspections to be done before reaching
every 8,000 flight hours but no later
than every 10 years since-last-fan blade
UI, whichever occurs first. These
changes would prevent many airplanes
PO 00000
Frm 00013
Fmt 4700
Sfmt 4700
3937
from being immediately grounded, upon
issuance of the AD. We agree with the
commenter’s intent. We changed and
added paragraphs (h) through (h)(2)(iii)
to clarify the initial inspection
requirements in the AD, and to
incorporate the compliance schedule
changes.
Request To Add LP Compressor Fan
Blade Part Numbers
ATA requests that we include LP
compressor fan blade part numbers in
the AD. We agree and added the part
numbers to the AD.
Incorrect Supplemental Type
Certificate (STC) Number
In paragraph (c) of the proposed AD,
STC number SA842SW is incorrect.
That STC applies to a Cessna Model 414
airplane. We corrected the STC No. in
paragraph (c) of this AD to SA8472SW,
which applies to a Boeing 727 airplane.
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
We estimate that this AD will affect
about 1,000 RRD Tay 611–8, Tay 620–
15, Tay 650–15, and Tay 651–54 series
turbofan engines installed on airplanes
of U.S. registry. We also estimate that it
will take about 4 work-hours per engine
to perform an inspection, and that the
average labor rate is $80 per work-hour.
Required parts will cost about $95,000
per LP compressor fan disk and
$140,000 per set of LP compressor fan
blades. We estimate that 5 percent or 50
engines will require replacing the LP
compressor fan disc and LP compressor
fan blade set. Based on these figures, we
estimate the total cost of the AD to U.S.
operators to be $11,750,000.
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
E:\FR\FM\29JAR1.SGM
29JAR1
3938
Federal Register / Vol. 72, No. 18 / Monday, January 29, 2007 / Rules and Regulations
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 at the address listed
under ADDRESSES.
List of Subjects in 14 CFR Part 39
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
PART 39—AIRWORTHINESS
DIRECTIVES
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 adding
the following new airworthiness
directive:
I
JR30649 ..............................................................................................................................................
JR31702 ..............................................................................................................................................
JR31983 ..............................................................................................................................................
(d) This AD results from a report that a set
of LP compressor fan blades failed before
reaching the LP compressor fan blade full
published life limit. We are issuing this AD
to prevent LP compressor fan blades from
failing due to blade root cracks, leading to
uncontained engine failure and damage to
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.
rmajette on PROD1PC67 with RULES
Ultrasonic Inspection (UI) of LP Compressor
Fan Blades for Certain Tay 650–15 Engines
That Have Not Yet Had UI of the LP
Compressor Fan Blades
(f) For Tay 650–15 engines, serial numbers
17201, 17202, 17226, 17253, 17341, 17356,
17428, 17450, 17457, 17458, 17497, 17530,
17622, 17643, 17655, 17678, 17709, 17751,
17755, 17805, and 17806 that have not yet
had UI of the LP compressor fan blades:
VerDate Aug<31>2005
14:38 Jan 26, 2007
Jkt 211001
Effective Date
(a) This airworthiness directive (AD)
becomes effective March 5, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Rolls-Royce
Deutschland Ltd & Co KG (RRD) Tay 611–8
and Tay 620–15 turbofan engines with low
pressure (LP) compressor module part
number (P/N) MO1100AA or P/N MO1100AB
installed, and Tay 650–15 and Tay 651–54
turbofan engines with LP compressor module
P/N MO1300AA or P/N MO1300AB
installed. These engines are installed on, but
not limited to, Fokker F.28 Mark 0070 and
0100 airplanes, Boeing 727 airplanes
modified in accordance with Supplemental
Type Certificate No. SA8472SW, and
Gulfstream G–IV airplanes. The following
P/N LP compressor fan blades are installed
in these modules:
Tay 620–15
LP compressor fan
blade P/Ns
Tay 611–8 LP compressor fan blade P/Ns
Unsafe Condition
2007–03–02 Rolls-Royce Deutschland Ltd &
Co KG (formerly Rolls-Royce plc):
Amendment 39–14913. Docket No.
FAA–2006–24777; Directorate Identifier
2006–NE–19–AD.
Tay 650–15
LP compressor fan
blade P/Ns
Tay 651–54
LP compressor fan
blade P/Ns
JR30649 ......
JR31702 ......
JR31983 ......
JR33863 ......
JR33864 ......
.....................
JR31911 ......
JR31912 ......
JR35120 ......
JR35121 ......
JR33865.
JR33866.
JR31911.
JR31912.
JR35120.
JR35121.
UI of LP Compressor Fan Blades for All Tay
Engines
(i) Initial UI at next shop visit for any
reason but no later than 6 months after the
effective date of this AD, whichever occurs
first.
(ii) Repetitive UIs at every engine shop
visit for any reason but before reaching every
10,000 flight hours-since-last fan blade UI,
whichever occurs first.
(2) For Tay 611–8 and Tay 620–15 engines:
(i) Initial UI at next shop visit for engine
mid-life inspection or overhaul, but no later
than 12 months after the effective date of this
AD, whichever occurs first.
(ii) For Tay 611–8 engines, repetitive UIs
before reaching every 8,000 flight hours but
no later than every 10 years since-last-fanblade UI, whichever occurs first.
(iii) For Tay 620–15 engines, repetitive UIs
before reaching every 10,000 flight hours but
no later than every 10 years since-last-fanblade UI, whichever occurs first.
(h) Perform UI of the LP compressor fan
blades for cracks, using Part 2 of RRD SB No.
TAY–72–1442, Revision 3, dated November
26, 2003, at the following:
(1) For Tay 650–15 and Tay 651–54
engines:
LP Compressor Fan Blades That Are
Cracked
(i) If any LP compressor fan blade is
cracked, then remove the complete LP
compressor fan blade set and the LP
compressor fan disc from service.
(1) Within 30 days after the effective date
of this AD, perform UI of the LP compressor
fan blades for cracks.
(2) Use Part 1 of RRD Service Bulletin (SB)
No. TAY–72–1591, dated May 8, 2003, to do
the inspection.
UI of LP Compressor Fan Blades Being
Installed in a Different Engine; Tay 650–15
and Tay 651–54 Engines
(g) For Tay 650–15 and Tay 651–54
engines, whenever LP compressor fan blades
are removed and are being installed in a
different engine:
(1) Perform UI of the LP compressor fan
blades for cracks.
(2) Use Part 1 of RRD SB No. TAY–72–
1442, Revision 3, dated November 26, 2003,
to do the inspection.
PO 00000
Frm 00014
Fmt 4700
Sfmt 4700
E:\FR\FM\29JAR1.SGM
29JAR1
3939
Federal Register / Vol. 72, No. 18 / Monday, January 29, 2007 / Rules and Regulations
Alternative Methods of Compliance
(j) 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
(k) Luftfahrt-Bundesamt airworthiness
directive D–1998–055R3, dated December 15,
2003, which was approved by EASA under
approval No. 1869 on December 15, 2003,
also addresses the subject of this AD.
(l) Contact Jason Yang, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; telephone (781) 238–7747, fax (781)
238–7199; e-mail: jason.yang@faa.gov for
more information about this AD.
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. Contact RollsRoyce Deutschland Ltd & Co KG, Eschenweg
11, D–15827 Dahlewitz, Germany; telephone
49 (0) 33–7086–1768; fax 49 (0) 33–7086–
3356 for a copy of this service information.
You may review copies 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/federalregister/cfr/ibr-locations.html.
Material Incorporated by Reference
(m) You must use the Rolls-Royce
Deutschland Ltd & Co KG service information
specified in Table 1 to perform the actions
required by this AD. The Director of the
Federal Register approved the incorporation
TABLE 1.—INCORPORATION BY REFERENCE
Service Bulletin No.
Page
Revision
TAY–72–1591, Total Pages: 8 ..................................................................................................
TAY–72–1442, Total Pages: 11 ................................................................................................
Appendix 1 of TAY–72–1442, Total Pages: 4 ...........................................................................
All ............
All .............
All .............
Original ....
3 ..............
3 ...............
Issued in Burlington, Massachusetts, on
January 22, 2007.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E7–1218 Filed 1–26–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25642; Directorate
Identifier 2006–NM–121–AD; Amendment
39–14912; AD 2007–03–01]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 757 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
rmajette on PROD1PC67 with RULES
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Boeing Model 757 airplanes. This AD
requires inspecting certain power feeder
wire bundles for damage, inspecting the
support clamps for these wire bundles
to determine whether the clamps are
properly installed, and performing
corrective actions if necessary. This AD
results from a report that a power feeder
wire bundle chafed against the number
six auxiliary slat track, causing
electrical wires in the bundle to arc,
which damaged both the auxiliary slat
track and power feeder wires. We are
issuing this AD to prevent arcing that
could be a possible ignition source for
leaked flammable fluids, which could
result in a fire. Arcing could also result
in a loss of power from the generator
VerDate Aug<31>2005
14:38 Jan 26, 2007
Jkt 211001
connected to the power feeder wire
bundle, and consequent loss of systems,
which could reduce controllability of
the airplane.
DATES: This AD becomes effective
March 5, 2007.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of March 5, 2007.
ADDRESSES: You may examine the 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., Nassif Building, Room PL–401,
Washington, DC.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for the service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Philip Sheridan, Aerospace Engineer,
Systems and Equipment Branch, ANM–
130S, FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6441; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
Date
May 8, 2003.
November 26, 2003.
November 26, 2003.
part 39 to include an AD that would
apply to certain Boeing Model 757
airplanes. That NPRM was published in
the Federal Register on August 21, 2006
(71 FR 48493). That NPRM proposed to
require inspecting certain power feeder
wire bundles for damage, inspecting the
support clamps for these wire bundles
to determine whether the clamps are
properly installed, and performing
corrective actions if necessary.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Request To Clarify Scope of Service
Information
Northwest Airlines (NWA) states that
the service bulletins referred to in the
NPRM indicate that Boeing technical
publication revisions are not required to
support the referenced modification.
NWA adds that, typically, wire bundle
installations are not detailed in Boeing
technical publications; wire bundles are
installed and maintained in accordance
with the Boeing standard wiring
practices manual (SWPM). NWA notes
that the addition of spacers and rivets to
wire bundle support brackets is not
supported by Boeing technical
publications. NWA adds that this
burdens operators with the cost of
developing their own system of
maintaining the required configuration
for continued compliance with the AD.
We infer that the commenter is asking
for clarification of the scope of the
referenced service information regarding
related technical publications.
Regarding the comment on adding
spacers and rivets, the spacers should
already have been installed, and the
purpose of the rivets is to ensure that
E:\FR\FM\29JAR1.SGM
29JAR1
]]>Agencies
[Federal Register Volume 72, Number 18 (Monday, January 29, 2007)]
[Rules and Regulations]
[Pages 3936-3939]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-1218]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24777; Directorate Identifier 2006-NE-19-AD;
Amendment 39-14913; AD 2007-03-02]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Tay
611-8, Tay 620-15, Tay 650-15, and Tay 651-54 Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
Rolls-Royce Deutschland Ltd & Co KG (RRD) Tay 611-8, Tay 620-15, Tay
650-15, and Tay 651-54 series turbofan engines, with certain low
pressure (LP) compressor modules installed. This AD requires an
ultrasonic inspection (UI) of LP compressor fan blades for cracks,
within 30 days after the effective date of the AD on certain serial
number (SN) Tay 650-15 engines. This AD also requires initial and
repetitive UIs of LP compressor fan blades on all engines. This AD also
requires, for Tay 650-15 and Tay 651-54 engines, UIs of LP compressor
fan blades whenever the blade set is removed from one engine and
installed on a different engine. This AD results from a report that a
set of LP compressor fan blades failed before reaching the LP
compressor fan blade full published life limit. We are issuing this AD
to prevent LP compressor fan blades from failing due to blade root
cracks, leading to uncontained engine failure and damage to the
airplane.
DATES: This AD becomes effective March 5, 2007. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of March 5, 2007.
ADDRESSES: You can get the service information identified in this AD
from Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, D-15827
Dahlewitz, Germany; telephone 49 (0) 33-7086-1768; fax 49 (0) 33-7086-
3356.
You may examine the AD docket on the Internet at https://dms.dot.gov
or in Room PL-401 on the plaza level of the Nassif Building, 400
Seventh Street, SW., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Jason Yang, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England
[[Page 3937]]
Executive Park, Burlington, MA 01803; telephone (781) 238-7747; fax
(781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with a proposed AD. The proposed AD applies to RRD Tay 611-8, Tay 620-
15, Tay 650-15, and Tay 651-54 series turbofan engines, with certain
low pressure (LP) compressor modules installed. We published the
proposed AD in the Federal Register on June 27, 2006 (71 FR 36493).
That action proposed to require a UI of LP compressor fan blades for
cracks, within 30 days after the effective date of the AD on certain
serial number (SN) Tay 650-15 engines. That action also proposed to
require repetitive UIs of LP compressor fan blades on all engines. That
action also proposed to require, for Tay 650-15 and Tay 651-54 engines,
UIs of LP compressor fan blades whenever the blade set is removed from
one engine and installed on a different engine.
Examining the AD Docket
You may examine the docket that contains the AD, any comments
received, and any final disposition in person at the Docket Management
Facility 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.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
RRD Request To Change Compliance Paragraphs (h)(1) and (h)(2)
RRD requests that we change the compliance schedule for Tay 650-15
and Tay 651-54 engines in proposed AD paragraph (h)(1), from ``at every
shop visit for any reason or before reaching every 4,000 flight hours-
since-last fan blade UI, whichever occurs first'' to ``at every engine
shop visit for any reason or before reaching every 10,000 flight hours-
since-last fan blade UI, whichever occurs first.''
RRD also requests that we change the compliance schedule for Tay
620-15 engines in proposed AD paragraph (h)(2) from ``before reaching
every 8,000 flight hours but no later than every 10 years since-last-
fan-blade UI, whichever occurs first'' to ``before reaching every
10,000 flight hours for airline operation, and before reaching 8,000
flight hours but no later than every 10 years since-last-fan-blade UI,
whichever occurs first, for non-airline operation.'' RRD bases these
changes on their Engine Management Program.
We agree with the intent of the requested changes to proposed AD
paragraph (h)(1). We changed that paragraph, and added subparagraphs to
clarify the initial inspection requirements in the AD. Regarding
paragraph (h)(2), we do not agree with having different inspection
schedules for airline and non-airline operations. However, we changed
paragraph (h)(2) to paragraph (h)(2)(iii), to read ``before reaching
every 10,000 flight hours but no later than every 10 years since-last-
fan-blade UI, whichever occurs first''. We feel that this drawdown
schedule will take care of both low- and high-utilization of Tay 620-15
engines.
Air Transport Association Request To Change Compliance Paragraph (h)(1)
Air Transport Association (ATA) requests that we change the
compliance schedule in paragraph (h)(1) from ``at every engine shop
visit for any reason or before reaching every 4,000 flight hours-since-
last fan blade UI, whichever occurs first'' to ``at every engine shop
visit for any reason or before reaching every 12 years or 15,000 flight
hours-since-last fan blade UI, whichever occurs first''. ATA states
that this schedule is described in the Engine Management Program for
Tay 651-54 engines installed in the Boeing 727 airplanes. We do not
agree. The intent of proposed AD paragraph (h)(1) is to UI Tay 650-15
and Tay 651-54 engines at all scheduled and unscheduled shop visits,
using RRD SB No. TAY-72-1442, Revision 3, dated November 26, 2003.
Also, the intent of the paragraph is to parallel the SB requirement of
an initial UI within 3 months after the SB issue date. We did change
paragraph (h) and added subparagraphs as described under the first
comment above.
Request To Change Compliance Paragraph (h)(3)
One commenter requests that we change the Tay 611-8 compliance
schedule in proposed AD paragraph (h)(3). The commenter requests that
we call out an initial UI inspection to be done at the next engine mid-
life or overhaul inspection after the effective date of this AD. The
commenter also requests that we call out repetitive UI inspections to
be done before reaching every 8,000 flight hours but no later than
every 10 years since-last-fan blade UI, whichever occurs first. These
changes would prevent many airplanes from being immediately grounded,
upon issuance of the AD. We agree with the commenter's intent. We
changed and added paragraphs (h) through (h)(2)(iii) to clarify the
initial inspection requirements in the AD, and to incorporate the
compliance schedule changes.
Request To Add LP Compressor Fan Blade Part Numbers
ATA requests that we include LP compressor fan blade part numbers
in the AD. We agree and added the part numbers to the AD.
Incorrect Supplemental Type Certificate (STC) Number
In paragraph (c) of the proposed AD, STC number SA842SW is
incorrect. That STC applies to a Cessna Model 414 airplane. We
corrected the STC No. in paragraph (c) of this AD to SA8472SW, which
applies to a Boeing 727 airplane.
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
We estimate that this AD will affect about 1,000 RRD Tay 611-8, Tay
620-15, Tay 650-15, and Tay 651-54 series turbofan engines installed on
airplanes of U.S. registry. We also estimate that it will take about 4
work-hours per engine to perform an inspection, and that the average
labor rate is $80 per work-hour. Required parts will cost about $95,000
per LP compressor fan disk and $140,000 per set of LP compressor fan
blades. We estimate that 5 percent or 50 engines will require replacing
the LP compressor fan disc and LP compressor fan blade set. Based on
these figures, we estimate the total cost of the AD to U.S. operators
to be $11,750,000.
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
[[Page 3938]]
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 at the
address listed under ADDRESSES.
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 adding the following new airworthiness
directive:
2007-03-02 Rolls-Royce Deutschland Ltd & Co KG (formerly Rolls-Royce
plc): Amendment 39-14913. Docket No. FAA-2006-24777; Directorate
Identifier 2006-NE-19-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective March 5,
2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Rolls-Royce Deutschland Ltd & Co KG (RRD)
Tay 611-8 and Tay 620-15 turbofan engines with low pressure (LP)
compressor module part number (P/N) MO1100AA or P/N MO1100AB
installed, and Tay 650-15 and Tay 651-54 turbofan engines with LP
compressor module P/N MO1300AA or P/N MO1300AB installed. These
engines are installed on, but not limited to, Fokker F.28 Mark 0070
and 0100 airplanes, Boeing 727 airplanes modified in accordance with
Supplemental Type Certificate No. SA8472SW, and Gulfstream G-IV
airplanes. The following P/N LP compressor fan blades are installed
in these modules:
----------------------------------------------------------------------------------------------------------------
Tay 650-15 LP Tay 651-54 LP
Tay 611-8 LP compressor fan blade P/ Tay 620-15 LP compressor compressor fan blade P/ compressor fan blade P/
Ns fan blade P/Ns Ns Ns
----------------------------------------------------------------------------------------------------------------
JR30649............................. JR30649................. JR31911................ JR31911.
JR31702............................. JR31702................. JR31912................ JR31912.
JR31983............................. JR31983................. JR35120................ JR35120.
JR33863................. JR35121................ JR35121.
JR33864................. JR33865................
........................ JR33866................
----------------------------------------------------------------------------------------------------------------
Unsafe Condition
(d) This AD results from a report that a set of LP compressor
fan blades failed before reaching the LP compressor fan blade full
published life limit. We are issuing this AD to prevent LP
compressor fan blades from failing due to blade root cracks, leading
to uncontained engine failure and damage to 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.
Ultrasonic Inspection (UI) of LP Compressor Fan Blades for Certain Tay
650-15 Engines That Have Not Yet Had UI of the LP Compressor Fan Blades
(f) For Tay 650-15 engines, serial numbers 17201, 17202, 17226,
17253, 17341, 17356, 17428, 17450, 17457, 17458, 17497, 17530,
17622, 17643, 17655, 17678, 17709, 17751, 17755, 17805, and 17806
that have not yet had UI of the LP compressor fan blades:
(1) Within 30 days after the effective date of this AD, perform
UI of the LP compressor fan blades for cracks.
(2) Use Part 1 of RRD Service Bulletin (SB) No. TAY-72-1591,
dated May 8, 2003, to do the inspection.
UI of LP Compressor Fan Blades Being Installed in a Different Engine;
Tay 650-15 and Tay 651-54 Engines
(g) For Tay 650-15 and Tay 651-54 engines, whenever LP
compressor fan blades are removed and are being installed in a
different engine:
(1) Perform UI of the LP compressor fan blades for cracks.
(2) Use Part 1 of RRD SB No. TAY-72-1442, Revision 3, dated
November 26, 2003, to do the inspection.
UI of LP Compressor Fan Blades for All Tay Engines
(h) Perform UI of the LP compressor fan blades for cracks, using
Part 2 of RRD SB No. TAY-72-1442, Revision 3, dated November 26,
2003, at the following:
(1) For Tay 650-15 and Tay 651-54 engines:
(i) Initial UI at next shop visit for any reason but no later
than 6 months after the effective date of this AD, whichever occurs
first.
(ii) Repetitive UIs at every engine shop visit for any reason
but before reaching every 10,000 flight hours-since-last fan blade
UI, whichever occurs first.
(2) For Tay 611-8 and Tay 620-15 engines:
(i) Initial UI at next shop visit for engine mid-life inspection
or overhaul, but no later than 12 months after the effective date of
this AD, whichever occurs first.
(ii) For Tay 611-8 engines, repetitive UIs before reaching every
8,000 flight hours but no later than every 10 years since-last-fan-
blade UI, whichever occurs first.
(iii) For Tay 620-15 engines, repetitive UIs before reaching
every 10,000 flight hours but no later than every 10 years since-
last-fan-blade UI, whichever occurs first.
LP Compressor Fan Blades That Are Cracked
(i) If any LP compressor fan blade is cracked, then remove the
complete LP compressor fan blade set and the LP compressor fan disc
from service.
[[Page 3939]]
Alternative Methods of Compliance
(j) 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
(k) Luftfahrt-Bundesamt airworthiness directive D-1998-055R3,
dated December 15, 2003, which was approved by EASA under approval
No. 1869 on December 15, 2003, also addresses the subject of this
AD.
(l) Contact Jason Yang, Aerospace Engineer, Engine Certification
Office, FAA, Engine and Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803; telephone (781) 238-7747, fax
(781) 238-7199; e-mail: jason.yang@faa.gov for more information
about this AD.
Material Incorporated by Reference
(m) You must use the Rolls-Royce Deutschland Ltd & Co KG service
information specified in Table 1 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.
Contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, D-15827
Dahlewitz, Germany; telephone 49 (0) 33-7086-1768; fax 49 (0) 33-
7086-3356 for a copy of this service information. You may review
copies 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/
cfr/ibr-locations.html.
Table 1.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
Service Bulletin No. Page Revision Date
----------------------------------------------------------------------------------------------------------------
TAY-72-1591, Total Pages: 8....... All................ Original........... May 8, 2003.
TAY-72-1442, Total Pages: 11...... All................ 3.................. November 26, 2003.
Appendix 1 of TAY-72-1442, Total All................ 3.................. November 26, 2003.
Pages: 4.
----------------------------------------------------------------------------------------------------------------
Issued in Burlington, Massachusetts, on January 22, 2007.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E7-1218 Filed 1-26-07; 8:45 am]
BILLING CODE 4910-13-P
