Airworthiness Directives; Rolls-Royce plc RB211-524 Series Turbofan Engines, 680-684 [05-85]
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Federal Register / Vol. 70, No. 3 / Wednesday, January 5, 2005 / Rules and Regulations
section for a location to
examine the regulatory evaluation.
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 FAA 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 (AD):
I
2005–01–03 Boeing: Amendment 39–13927.
Docket No. FAA–2004–19200;
Directorate Identifier 2003–NM–195–AD.
Effective Date
(a) This AD becomes effective February 9,
2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Boeing Model 747–
100, –100B, –100B SUD, –200B, –200C,
–200F, and –300 series airplanes; and Model
747SP and 747SR series airplanes;
certificated in any category; equipped with
Pratt & Whitney JT9D–3, and –7 (except –70)
series engines or General Electric CF6–50
series engines with modified JT9D–7 inboard
struts; as listed in Boeing Alert Service
Bulletin 747–54A2219, dated September 4,
2003.
Unsafe Condition
(d) This AD was prompted by reports of
cracking in the midspar web. We are issuing
this AD to detect and correct cracking in the
midspar assembly, which could result in the
loss of the midspar assembly load path, and
could, combined with the loss of the nacelle
station 180 bulkhead load path, lead to the
separation of the engine from 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.
Compliance Times
(f) Within 18 months after the effective
date of this AD, do the actions in paragraphs
(g) and (h) of this AD, as applicable. Repeat
the actions thereafter at intervals not to
exceed 1,200 flight cycles.
Inboard Strut Midspar Inspection
(g) For Group 1 and 2 airplanes specified
in paragraph 1.A.1. of Boeing Alert Service
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Bulletin 747–54A2219, dated September 4,
2003: Perform a detailed inspection of the
midspar web of the inboard struts for
cracking, disbonding, or buckling; a detailed
inspection of the midspar stiffeners for any
crack or fracture; related investigative
actions; and any applicable corrective
actions; in accordance with ‘‘Part 1’’ of the
Work Instructions of Boeing Alert Service
Bulletin 747–54A2219, dated September 4,
2003; except as required by paragraph (i) of
this AD. Perform any related investigative
actions and any applicable corrective actions
before further flight.
Outboard Strut Midspar Inspection
(h) For Group 1 airplanes specified in
paragraph 1.A.1. of Boeing Alert Service
Bulletin 747–54A2219, dated September 4,
2003: Perform a detailed inspection of the
midspar web of the outboard struts for
cracking, disbonding, or buckling; a detailed
inspection of the midspar stiffeners for any
crack or fracture; related investigative
actions; and any applicable corrective
actions; in accordance with ‘‘Part 2’’ of the
Work Instructions of Boeing Alert Service
Bulletin 747–54A2219, dated September 4,
2003; except as required by paragraph (i) of
this AD. Perform any related investigative
actions and any applicable corrective actions
before further flight.
Contact the FAA/Designated Engineering
Representative (DER)
(i) Where Boeing Alert Service Bulletin
747–54A2219, dated September 4, 2003,
specifies to contact Boeing for appropriate
action: Before further flight, repair per a
method approved by the Manager, Seattle
Aircraft Certification Office (ACO), FAA; or
per data meeting the type certification basis
of the airplane approved by a Boeing
Company DER who has been authorized by
the Manager, Seattle ACO, to make such
findings. For a repair method to be approved,
the approval must specifically reference this
AD.
Alternative Methods of Compliance
(AMOCs)
(j)(1) The Manager, Seattle ACO, FAA, has
the authority to approve AMOCs for this AD,
if requested in accordance with the
procedures found in 14 CFR 39.19.
(2) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by a
Boeing Company DER who has been
authorized by the Manager, Seattle ACO, to
make those findings. For a repair method to
be approved, the approval must specifically
refer to this AD.
Material Incorporated by Reference
(k) You must use Boeing Alert Service
Bulletin 747–54A2219, dated September 4,
2003, to perform the actions that are required
by this AD, unless the AD specifies
otherwise. The Director of the Federal
Register approves the incorporation by
reference of this document in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51. For
copies of the service information, contact
Boeing Commercial Airplanes, P.O. Box
3707, Seattle, Washington 98124–2207. For
information on the availability of this
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material at the National Archives and
Records Administration (NARA), call (202)
741–6030, or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
You may view the AD docket at the Docket
Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW.,
room PL–401, Nassif Building, Washington,
DC.
Issued in Renton, Washington, on
December 27, 2004.
Kevin M. Mullin,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–105 Filed 1–4–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2004–NE–19–AD; Amendment
39–13917; AD 2004–26–05]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
plc RB211–524 Series Turbofan
Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD) for
certain Rolls-Royce plc (RR) RB211–524
series turbofan engines. That AD
currently requires initial and repetitive
borescope insepctions of the head
section and meterpanel assembly of the
combustion liner, and replacement, if
necessary, with serviceable parts. In
addition, that AD allows an optional
installation of a front combustion liner
with a strengthened head section as a
terminating action to the inspection
requirements. This AD requires initial
and repetitive borescope inspections of
the head section and meterpanel
assembly of the combustion liner, and
replacement if necessary with
serviceable parts. This AD also requires
reduction of the inspection intervals of
certain RB211–524 engine models that
have not been repaired to RR Field
Repair Scheme FRS5367/B, and a
mandatory terminating action to be
completed by a certain date. This AD
results from five events that are directly
attributed to combustor head breakup
and meterpanel failure which were
found at overhaul inspection. At least
one of these events resulted in a
combustion case burn-through. We are
issuing this AD to prevent engine
combustion liner deterioration, which
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can result in combustion liner breakup,
case burn-through, and engine fire.
DATES: This AD becomes effective
February 9, 2005. The incorporation by
reference of RR ASB RB.211–72–AB482,
Revision 9, dated July 28, 2003; RollsRoyce Service Bulletins (SB’s) RB.211–
72–9764, Revision 3, dated January 16,
1998, RB.211–72–9670, Original Issue,
dated August 27, 1993; and RB.211–72–
9764 Supplement 1, dated January 16,
1998; are approved by the Director of
the Federal Register as of February 9,
2005.
You can get the service
information identified in this AD from
Rolls-Royce plc, P.O. Box 31, Derby,
DE24–8BJ, United Kingdom; telephone:
011–44–1332–242424; fax 011–44–
1332–249936.
You may examine the AD docket at
the FAA, New England Region, Office of
the Regional Counsel, 12 New England
Executive Park, Burlington, MA. You
may examine the service information, at
the FAA, New England Region, Office of
the Regional Counsel, 12 New England
Executive Park, Burlington, MA; or at
the National Archives and Records
Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030,
or to to https://www.archives.gov/
federal_register/
code_of_federal_regulations/
ibr_locations.html.
ADDRESSES:
FOR FURTHER INFORMATION CONTACT:
Ian
Dargin, Aerospace Engineer, Engine
Certification Office, FAA, Engine and
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803–
5299; telephone (781) 238–7178; fax
(781) 238–7199.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
a proposed AD. The proposed AD
applies to RR RB211–524 series turbofan
engines. We published the proposed AD
in the Federal Register on May 18, 2004
(69 FR 28094). That action proposed to
require initial and repetitive borescope
inspections of the head section and
meterpanel assembly of the combustion
liner and replacement if necessary, with
serviceable parts. That action also
proposed a reduction of the inspection
intervals of certain RB211–524 engine
models that have not been repaired to
RR Field Repair Scheme FRS53667/B,
and a mandatory terminating action to
be completed by a certain date.
Friday, except Federal holidays. See
for the location.
ADDRESSES
Comments
We provided the public the
opportunity to participate in the
development of this AD. We received no
comments on the proposal or on the
determination of the cost to the public.
However, we corrected RR Service
Bulletin (SB) No. RB.211–71–9670 in
Compliance paragraph (q) of this AD to
RR SB No. RB.211.–72–9670.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD with the change
described previously. We have
determined that the change will neither
increase the economic burden on any
operator nor increase the scope of the
AD.
Costs of Compliance
There are about 537 RB211–524 series
turbofan engines of the affected design
in the worldwide fleet. We estimate that
18 engines installed on airplanes of U.S.
registry will be affected by this AD. We
also estimate that it will take
approximately 2.0 work hours per
engine to perform the actions, and that
the average labor rate is $65 per work
hour. Required parts will cost about
$228,389 per engine. Based on these
figures, we estimate that total cost of the
AD to U.S. operators to be $4,113,342.
Examining the AD Docket
Authority for this Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
You may examine the AD Docket
(including any comments and service
information), by appointment, between
8 a.m. and 4:30 p.m., Monday through
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
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681
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a summary of the costs
to comply with this AD and placed it in
the AD Docket. You may get a copy of
this summary by sending a request to us
at the address listed under ADDRESSES.
Include ‘‘AD Docket No. 2004–NE–19–
AD’’ in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
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
removing Amendment 39–9978 (62 FR
16475, April 7, 1997) and by adding a
new airworthiness directive,
Amendment 39–13917, to read as
follows:
I
2004–26–05 Rolls-Royce plc: Amendment
39–13917. Docket No. 2004–NE–19–AD.
Supersedes AD 97–07–04, Amendment
39–9978.
Effective Date
(a) This AD becomes effective February 9,
2005.
Affected ADs
(b) This AD supersedes AD 97–07–04,
Amendment 39–9978.
Applicability
(c) This AD applies to Rolls-Royce plc (RR)
engine models RB211–524B–02, –524B2,
–524B3, –524B4, –524C2, and –524D4 series
engines incorporating RR Service Bulletin
(SB) No. RB.211–72–7221 or RR SB No.
RB.211–72–7998 with front combustion liner
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assembly, part number (P/N) UL16885,
UL29916, UL27107, UL28972, or UL28974
installed but not incorporating RR SB No.
RB.211–72–9670 or RR SB No. RB.211–72–
9764, and engine models RB211–524G and
–524H series engines with front combustion
liner assembly P/N UL27659, UL23992, or
UL22988 but not incorporating RR SB No.
RB.211–72–9764. These engines are installed
on, but not limited to, Boeing 747 and
Lockheed L1011 series airplanes.
Unsafe Condition
(d) This AD results from five events that
are directly attributed to combustor head
breakup and meterpanel failure which were
found at overhaul inspection. At least one of
these events resulted in a combustion case
burn-through. The actions specified in this
AD are intended to prevent engine
combustion liner deterioration, which can
result in combustion liner breakup, case
burn-through, and engine fire.
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. Engine
inspections previously made to RR Service
Bulletin No. RB.211–72–B482, Revision 8,
can be credited for counting cycles since last
inspection.
Inspections of Combustion Liner Head
Sections—Not Previously Repaired
(f) Borescope-inspect combustion liner
head sections that have not been previously
repaired. Use paragraphs 3.A.(1) through
3.A.(5) of the Accomplishment Instructions
of RR Alert Service Bulletin (ASB) No.
RB.211–72–AB482, Revision 9, dated July 28,
2003, and the compliance thresholds in Table
1 of this AD.
TABLE 1.—COMBUSTOR HEAD SECTION—NOT PREVIOUSLY REPAIRED
Initial inspection (cycles since-new
(CSN))
Repetitive inspection (cyclessince-last-inspection (CSLI))
Parts exceeding initial inspection
cycles (cycles-in-service (CIS))
–524D4,
Within 1,400 to 1,600 CSN ..........
Within 200 CSLI ...........................
–524B,
Within 3,000 to 3,200 CSN ..........
Within 200 CSLI ...........................
Within 100 CIS after the effective
date of this AD.
Within 200 CIS after the effective
date of this AD.
Engine series
(1)
RB211–524C2,
–524G, and –524H.
(2)
RB211–524B–02,
–524B3, and –524B4.
Inspections of Combustion Head Sections—
Previously Repaired Using RR Field Repair
Scheme FRS5367/B
(g) Borescope-inspect combustion liner
head sections previously repaired using RR
Field Repair Scheme FRS5367/B. Use
paragraphs 3.A.(1) through 3.A.(5) of the
Accomplishment Instructions of RR ASB No.
RB.211–72–AB482, Revision 9, dated July 28,
2003, and the compliance thresholds in Table
2 of this AD.
TABLE 2.—COMBUSTOR HEAD SECTION—PREVIOUSLY REPAIRED USING RR FIELD REPAIR SCHEME FRS5367/B
Initial inspection (cycles-sincelast-repair (CSLR))
Repetitive inspection (cyclessince-last-inspection (CSLI))
Parts exceeding initial inspection
cycles (cycles-in-service (CIS))
–524D4,
Within 1,800 to 2,200 CSLR ........
Within 400 CSLI ...........................
–524B2,
Within 3,000 to 3,200 CSLR ........
Within 400 CSLI ...........................
Within 200 CIS after the effective
date of this AD.
Within 200 CIS after the effective
date of this AD.
Engine series
(1)
RB211–524C2,
–524G, and –524H.
(2) RB211–524B–02,
–524B3, and –524B4.
Inspections of Combustion Head Sections
That Have Been Repaired But Did Not Use
RR Field Repair Scheme FRS5367/B
(h) Borescope-inspect combustion liner
sections that have been repaired using a
method other than RR Field Repair Scheme
FRS5367/B. Use paragraphs 3.A.(1) through
3.A.(5) of the Accomplishment Instructions
of RR ASB No. RB.211–72–AB482, Revision
9, dated July 28, 2003, and the compliance
thresholds in Table 3 of this AD.
TABLE 3.—COMBUSTOR HEAD SECTION—REPAIRED, BUT DID NOT USE RR FIELD REPAIR SCHEME FRS5367/B
Initial inspection cycles (cyclessince-last-repair (CSLR))
Repetitive inspection cycles (cycles-since-last-inspection (CSLI))
Parts exceeding initial inspection
cycles (cycles-in-service (CIS))
–524D4,
Within 500 to 700 CSLR ..............
Within 200 CSLI ...........................
–524B2,
Within 2,000 to 2,200 CSLR ........
Within 200 CSLI ...........................
Within 100 CIS after the effective
date of this AD.
Within 200 CIS after the effective
date of this AD.
Engine series
(1)
RB211–524C2,
–524G, and –524H.
(2) RB211–524B–02,
–524B3, and –524B4.
Note 1: For an installed front combustion
liner that is subject to RR ASB No. RB.211–
72–AB482, Revision 9, dated July 28, 2003:
If the operator can confirm with the relevant
overhaul base or repair vendor that the
nicrobraze repair RR Field Repair Scheme
FRS5367 has been applied to all 18 struts,
then this is equivalent to compliance with RR
Field Repair Scheme FRS5367/B.
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Note 2: Head sections repaired by
replacement of all 18 struts using RR Field
Repair Scheme FRS6548 are considered as
equivalent to fitting a new head section for
inspection purposes.
Inspections of Meterpanel Assemblies—Not
Repaired
(SB) No. RB.211–72–7998, that have not been
previously repaired. Using Paragraphs 3.B.(1)
through 3.B.(7) of the Accomplishment
Instructions of RR ASB No. RB.211–72–
AB482, Revisions 9, dated July 28, 2003, and
the compliance thresholds in Table 4 of this
AD.
(i) Borescope-inspect meterpanel
assemblies, incorporating Service Bulletin
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683
TABLE 4.—METERPANEL ASSEMBLY—NOT REPAIRED
Initial inspection cycles-since-new
(CSN)
Repetitive inspection cycles (cycles-since-last-inspection (CSLI))
(1) RB211–524D4, –524G, and Within 1,000 to 1,200 CSN ..........
–524H.
(2) RB211–524D4, –524G, and Within 1,800 to 2,000 CSN ..........
–524H that have not used
RB211–524H ratings at any time.
Within 400 CSLI ...........................
Engine series
Inspections of Meterpanel Assemblies—
Repaired
(J) Borescope-inspect meterpanel
assemblies, incorporating Service Bulletin
Within 400 CSLI ...........................
(SB) No. RB.211–72–7998, that have been
previously repaired. Use paragraphs 3.B.(1)
through 3.B.(7) of the Accomplishment
Instructions of RR ASB No. RB.211–72–
Parts exceeding initial inspection
cycles (cycles-in-service (CIS))
Within
date
Within
date
50 CIS after the effective
of this AD.
50 CIS after the effective
of this AD.
AB482, Revision 9, dated July 28, 2003, and
the compliance thresholds in Table 5 of this
AD.
TABLE 5.—METERPANEL ASSEMBLY—REPAIRED
Engine series
Initial inspection cycles (cyclessince-last-repair (CSLR))
Repetitive inspection cycles (cycles-since-last-inspection (CSLI))
Parts exceeding initial inspection
cycles (cycles-in-service (CIS))
(1) RB211–524D4, –524G, and
–524H.
Within 500 to 700 CSLR ..............
Within 400 CSLI ...........................
Within 50 CIS after the effective
date of this AD.
Note 3: There is no requirement to inspect
meter panels for combustors to a pre-RR SB
No. RB.211–72–7998 standard.
Reject Parts
(k) Replace parts that exceed the
acceptance criteria. Information about the
acceptance criteria can be found in the
Aircraft Maintenance Manual, 72–00–00,
Inspection/Check.
Mandatory Terminating Action
(l) Replace any front combustion liner
assembly that has a P/N listed in paragraph
(c) of this AD at the next shop visit or within
10,000 CSN but no later than December 31,
2012.
(m) Replacement of the front combustion
liner assembly with a front combustion liner
assembly that incorporates the modifications
in RR SB No. RB.211–72–9670 or RR SB No.
RB.211–72–9764 in the RB211–524B02,
–524B2, –524B3, –524B4, –524C2 and
–524D4 engines constitutes terminating
action to the repetitive inspections in
paragraphs (f), (g), (h), (i), and (j), of this AD.
(n) Replacement of the front combustion
liner assembly with a front combustion liner
assembly that incorporates the modifications
in RR SB No. RB.211–72–9764 in the RB211–
524G and –524H engines constitutes
terminating action to the repetitive
inspections in paragraphs (f), (g), (h), (i), and
(j) of this AD.
Definition of Shop Visit
(o) For the purpose of this AD, a shop visit
is defined as any time that the 04 module is
removed for refurbishment or overhaul.
Alternative Methods of Compliance
(p) The Manager, Engine Certification
Office, has the authority to approve
alternative methods of compliance for this
AD if requested using the procedures found
in 14 CFR 39.19.
Material Incorporated by Reference
(q) You must use the Rolls-Royce plc (RR)
Alert Service Bulletin (ASB) and Service
Bulletins (SB’s) listed in Table 6 of this AD
to do the inspections and replacements
required by this AD. The Director of the
Federal Register approved the incorporation
by reference of RR ASB No. RB.211–72–
AB482, Revision 9, dated July 28, 2003; SB’s
No. RB.211–72–9764, Revision 3, dated
January 16, 1998, No. RB.211–72–9670,
Original Issue, dated August 27, 1993; and
SB No. RB.211–72–9764 Supplement,
Revision 1, dated January 16, 1998; in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. You can get copies at the FAA, New
England Region, Office of the Regional
Counsel, 12 New England Executive Park,
Burlington, MA; or at the National Archives
and Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030; or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html. Table 6 follows:
TABLE 6.—INCORPORATION BY REFERENCE
Service bulletin
Page number(s) shown on the
page
Revision level shown on the page
RB.211–72–AB482, ...................................................
Total Pages: 12
RB.211–72–9670, ......................................................
Total Pages: 49
RB.211–72–9764 .......................................................
All ..................................................
9 ....................................................
July 28, 2003.
All ..................................................
Original ..........................................
Aug. 27, 1993.
1 ....................................................
2 ....................................................
3, 4 ................................................
5 ....................................................
6 ....................................................
7–10 ..............................................
11 ..................................................
12–30 ............................................
3 ....................................................
Original ..........................................
3 ....................................................
1 ....................................................
3 ....................................................
Original ..........................................
3 ....................................................
Original ..........................................
Jan. 16, 1998.
Aug. 20, 1993.
Jan. 16, 1998.
Aug. 25, 1995.
Jan. 16, 1998.
Aug. 20, 1993.
Jan. 16, 1998.
Aug. 20, 1993.
1 ....................................................
1 ....................................................
Jan. 16, 1998.
Total Pages: 30
RB.211–72–9764 Supplement ..................................
Total Pages: 1
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Related Information
(r) Civil Aviation Authority airworthiness
directive AD G–2003–0011, dated October 1,
2003, (previously 005–07–95, dated
November 15, 2001), also addresses the
subject of this AD. Aircraft Maintenance
Manual 72–00–00 also addresses the subject
of this AD.
oil leaks from the oil pump of the power
control unit due to a malfunction of the
pressure regulating valve. We are
issuing this AD to prevent fracturing of
the pump body, which could result in
loss of engine oil, and consequent
inability to maintain engine oil pressure
and to feather the propeller.
DATES: This AD becomes effective
February 9, 2005.
The incorporation by reference of
certain publications listed in the AD is
approved by the Director of the Federal
Register as of February 9, 2005.
ADDRESSES: For service information
identified in this AD, contact
Bombardier, Inc., Canadair, Aerospace
Group, P.O. Box 6087, Station Centreville, Montreal, Quebec H3C 3G9,
Canada. You can examine this
information at the National Archives
and Records Administration (NARA).
For information on the availability of
this material at NARA, call (202) 741–
6030, or go to: https://www.archives.gov/
federal_register/
code_of_federal_regulations/
ibr_locations.html.
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–2004–
19496; the directorate identifier for this
docket is 2003–NM–181–AD.
FOR FURTHER INFORMATION CONTACT:
Richard Fiesel, Aerospace Engineer,
Airframe and Propulsion Branch, ANE–
171, FAA, New York Aircraft
Certification Office, 1600 Stewart
Avenue, Suite 410, Westbury, New York
11590; telephone (516) 228–7304; fax
(516) 794–5531.
Issued in Burlington, Massachusetts, on
December 20, 2004.
Francis A. Favara,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 05–85 Filed 1–4–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2004–19496; Directorate
Identifier 2003–NM–181–AD; Amendment
39–13920; AD 2004–26–08]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model CL–215–6B11 (CL215T Variant)
and CL–215–6B11 (CL415 Variant)
Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Bombardier Model CL–215–6B11
(CL215T variant) and CL–215–6B11
(CL415 variant) series airplanes. This
AD requires replacing the mounting pad
studs of the auxiliary feather pump with
new, longer studs, and installing a
pressure relief valve. This AD is
prompted by a few incidents of external
SUMMARY:
Examining the Docket
The AD docket contains the proposed
AD, comments, and any final
disposition. You can examine the 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 DOT street address stated in the
ADDRESSES section.
The FAA
proposed to amend 14 CFR part 39 with
an AD for certain Bombardier Model
CL–215–6B11 (CL215T variant) and CL–
215–6B11 (CL415 variant) series
airplanes. That action, published in the
Federal Register on November 3, 2004
(69 FR 63968), proposed to require
replacing the mounting pad studs of the
auxiliary feather pump with new, longer
studs, and installing a pressure relief
valve.
SUPPLEMENTARY INFORMATION:
Comments
We provided the public the
opportunity to participate in the
development of this AD. No comments
have been submitted on the proposed
AD or on the determination of the cost
to the public.
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD as proposed.
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this AD.
ESTIMATED COSTS
Replacement .....................................
Installation .........................................
2
4
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.
VerDate jul<14>2003
16:19 Jan 04, 2005
Average
labor rate
per hour
Work
hours
Action
Jkt 205001
$65
65
Free ..................................................
Free ..................................................
We are issuing this rulemaking under
the authority described in subtitle VII,
part A, subpart III, section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
PO 00000
Frm 00024
Cost per
airplane
Parts
Fmt 4700
Sfmt 4700
Number
of U.S.registered
airplanes
$130
260
Fleet cost
3
3
$390
780
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
E:\FR\FM\05JAR1.SGM
05JAR1
]]>Agencies
[Federal Register Volume 70, Number 3 (Wednesday, January 5, 2005)]
[Rules and Regulations]
[Pages 680-684]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-85]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2004-NE-19-AD; Amendment 39-13917; AD 2004-26-05]
RIN 2120-AA64
Airworthiness Directives; Rolls-Royce plc RB211-524 Series
Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for certain Rolls-Royce plc (RR) RB211-524 series turbofan
engines. That AD currently requires initial and repetitive borescope
insepctions of the head section and meterpanel assembly of the
combustion liner, and replacement, if necessary, with serviceable
parts. In addition, that AD allows an optional installation of a front
combustion liner with a strengthened head section as a terminating
action to the inspection requirements. This AD requires initial and
repetitive borescope inspections of the head section and meterpanel
assembly of the combustion liner, and replacement if necessary with
serviceable parts. This AD also requires reduction of the inspection
intervals of certain RB211-524 engine models that have not been
repaired to RR Field Repair Scheme FRS5367/B, and a mandatory
terminating action to be completed by a certain date. This AD results
from five events that are directly attributed to combustor head breakup
and meterpanel failure which were found at overhaul inspection. At
least one of these events resulted in a combustion case burn-through.
We are issuing this AD to prevent engine combustion liner
deterioration, which
[[Page 681]]
can result in combustion liner breakup, case burn-through, and engine
fire.
DATES: This AD becomes effective February 9, 2005. The incorporation by
reference of RR ASB RB.211-72-AB482, Revision 9, dated July 28, 2003;
Rolls-Royce Service Bulletins (SB's) RB.211-72-9764, Revision 3, dated
January 16, 1998, RB.211-72-9670, Original Issue, dated August 27,
1993; and RB.211-72-9764 Supplement 1, dated January 16, 1998; are
approved by the Director of the Federal Register as of February 9,
2005.
ADDRESSES: You can get the service information identified in this AD
from Rolls-Royce plc, P.O. Box 31, Derby, DE24-8BJ, United Kingdom;
telephone: 011-44-1332-242424; fax 011-44-1332-249936.
You may examine the AD docket at the FAA, New England Region,
Office of the Regional Counsel, 12 New England Executive Park,
Burlington, MA. You may examine the service information, at the FAA,
New England Region, Office of the Regional Counsel, 12 New England
Executive Park, Burlington, MA; or at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or to to https://www.archives.gov/
federal_register/code_of_federal_regulations/ibr_locations.html.
FOR FURTHER INFORMATION CONTACT: Ian Dargin, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7178; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with a proposed AD. The proposed AD applies to RR RB211-524 series
turbofan engines. We published the proposed AD in the Federal Register
on May 18, 2004 (69 FR 28094). That action proposed to require initial
and repetitive borescope inspections of the head section and meterpanel
assembly of the combustion liner and replacement if necessary, with
serviceable parts. That action also proposed a reduction of the
inspection intervals of certain RB211-524 engine models that have not
been repaired to RR Field Repair Scheme FRS53667/B, and a mandatory
terminating action to be completed by a certain date.
Examining the AD Docket
You may examine the AD Docket (including any comments and service
information), by appointment, between 8 a.m. and 4:30 p.m., Monday
through Friday, except Federal holidays. See ADDRESSES for the
location.
Comments
We provided the public the opportunity to participate in the
development of this AD. We received no comments on the proposal or on
the determination of the cost to the public. However, we corrected RR
Service Bulletin (SB) No. RB.211-71-9670 in Compliance paragraph (q) of
this AD to RR SB No. RB.211.-72-9670.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD with the
change described previously. We have determined that the change will
neither increase the economic burden on any operator nor increase the
scope of the AD.
Costs of Compliance
There are about 537 RB211-524 series turbofan engines of the
affected design in the worldwide fleet. We estimate that 18 engines
installed on airplanes of U.S. registry will be affected by this AD. We
also estimate that it will take approximately 2.0 work hours per engine
to perform the actions, and that the average labor rate is $65 per work
hour. Required parts will cost about $228,389 per engine. Based on
these figures, we estimate that total cost of the AD to U.S. operators
to be $4,113,342.
Authority for this Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary by
sending a request to us at the address listed under ADDRESSES. Include
``AD Docket No. 2004-NE-19-AD'' in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Amendment 39-9978 (62 FR
16475, April 7, 1997) and by adding a new airworthiness directive,
Amendment 39-13917, to read as follows:
2004-26-05 Rolls-Royce plc: Amendment 39-13917. Docket No. 2004-NE-
19-AD. Supersedes AD 97-07-04, Amendment 39-9978.
Effective Date
(a) This AD becomes effective February 9, 2005.
Affected ADs
(b) This AD supersedes AD 97-07-04, Amendment 39-9978.
Applicability
(c) This AD applies to Rolls-Royce plc (RR) engine models RB211-
524B-02, -524B2, -524B3, -524B4, -524C2, and -524D4 series engines
incorporating RR Service Bulletin (SB) No. RB.211-72-7221 or RR SB
No. RB.211-72-7998 with front combustion liner
[[Page 682]]
assembly, part number (P/N) UL16885, UL29916, UL27107, UL28972, or
UL28974 installed but not incorporating RR SB No. RB.211-72-9670 or
RR SB No. RB.211-72-9764, and engine models RB211-524G and -524H
series engines with front combustion liner assembly P/N UL27659,
UL23992, or UL22988 but not incorporating RR SB No. RB.211-72-9764.
These engines are installed on, but not limited to, Boeing 747 and
Lockheed L1011 series airplanes.
Unsafe Condition
(d) This AD results from five events that are directly
attributed to combustor head breakup and meterpanel failure which
were found at overhaul inspection. At least one of these events
resulted in a combustion case burn-through. The actions specified in
this AD are intended to prevent engine combustion liner
deterioration, which can result in combustion liner breakup, case
burn-through, and engine fire.
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. Engine inspections previously made
to RR Service Bulletin No. RB.211-72-B482, Revision 8, can be
credited for counting cycles since last inspection.
Inspections of Combustion Liner Head Sections--Not Previously Repaired
(f) Borescope-inspect combustion liner head sections that have
not been previously repaired. Use paragraphs 3.A.(1) through 3.A.(5)
of the Accomplishment Instructions of RR Alert Service Bulletin
(ASB) No. RB.211-72-AB482, Revision 9, dated July 28, 2003, and the
compliance thresholds in Table 1 of this AD.
Table 1.--Combustor Head Section--Not Previously Repaired
----------------------------------------------------------------------------------------------------------------
Parts exceeding initial
Initial inspection Repetitive inspection inspection cycles
Engine series (cycles since-new (cycles-since-last- (cycles-in-service
(CSN)) inspection (CSLI)) (CIS))
----------------------------------------------------------------------------------------------------------------
(1) RB211-524C2, -524D4, -524G, and - Within 1,400 to 1,600 Within 200 CSLI........ Within 100 CIS after
524H. CSN. the effective date of
this AD.
(2) RB211-524B-02, -524B, -524B3, and Within 3,000 to 3,200 Within 200 CSLI........ Within 200 CIS after
-524B4. CSN. the effective date of
this AD.
----------------------------------------------------------------------------------------------------------------
Inspections of Combustion Head Sections--Previously Repaired Using RR
Field Repair Scheme FRS5367/B
(g) Borescope-inspect combustion liner head sections previously
repaired using RR Field Repair Scheme FRS5367/B. Use paragraphs
3.A.(1) through 3.A.(5) of the Accomplishment Instructions of RR ASB
No. RB.211-72-AB482, Revision 9, dated July 28, 2003, and the
compliance thresholds in Table 2 of this AD.
Table 2.--Combustor Head Section--Previously Repaired Using RR Field Repair Scheme FRS5367/B
----------------------------------------------------------------------------------------------------------------
Parts exceeding initial
Initial inspection Repetitive inspection inspection cycles
Engine series (cycles-since-last- (cycles-since-last- (cycles-in-service
repair (CSLR)) inspection (CSLI)) (CIS))
----------------------------------------------------------------------------------------------------------------
(1) RB211-524C2, -524D4, -524G, and - Within 1,800 to 2,200 Within 400 CSLI........ Within 200 CIS after
524H. CSLR. the effective date of
this AD.
(2) RB211-524B-02, -524B2, -524B3, Within 3,000 to 3,200 Within 400 CSLI........ Within 200 CIS after
and -524B4. CSLR. the effective date of
this AD.
----------------------------------------------------------------------------------------------------------------
Inspections of Combustion Head Sections That Have Been Repaired But Did
Not Use RR Field Repair Scheme FRS5367/B
(h) Borescope-inspect combustion liner sections that have been
repaired using a method other than RR Field Repair Scheme FRS5367/B.
Use paragraphs 3.A.(1) through 3.A.(5) of the Accomplishment
Instructions of RR ASB No. RB.211-72-AB482, Revision 9, dated July
28, 2003, and the compliance thresholds in Table 3 of this AD.
Table 3.--Combustor Head Section--Repaired, But Did Not Use RR Field Repair Scheme FRS5367/B
----------------------------------------------------------------------------------------------------------------
Parts exceeding initial
Initial inspection Repetitive inspection inspection cycles
Engine series cycles (cycles-since- cycles (cycles-since- (cycles-in-service
last-repair (CSLR)) last-inspection (CSLI)) (CIS))
----------------------------------------------------------------------------------------------------------------
(1) RB211-524C2, -524D4, -524G, and - Within 500 to 700 CSLR. Within 200 CSLI........ Within 100 CIS after
524H. the effective date of
this AD.
(2) RB211-524B-02, -524B2, -524B3, Within 2,000 to 2,200 Within 200 CSLI........ Within 200 CIS after
and -524B4. CSLR. the effective date of
this AD.
----------------------------------------------------------------------------------------------------------------
Note 1: For an installed front combustion liner that is subject
to RR ASB No. RB.211-72-AB482, Revision 9, dated July 28, 2003: If
the operator can confirm with the relevant overhaul base or repair
vendor that the nicrobraze repair RR Field Repair Scheme FRS5367 has
been applied to all 18 struts, then this is equivalent to compliance
with RR Field Repair Scheme FRS5367/B.
Note 2: Head sections repaired by replacement of all 18 struts
using RR Field Repair Scheme FRS6548 are considered as equivalent to
fitting a new head section for inspection purposes.
Inspections of Meterpanel Assemblies--Not Repaired
(i) Borescope-inspect meterpanel assemblies, incorporating
Service Bulletin (SB) No. RB.211-72-7998, that have not been
previously repaired. Using Paragraphs 3.B.(1) through 3.B.(7) of the
Accomplishment Instructions of RR ASB No. RB.211-72-AB482, Revisions
9, dated July 28, 2003, and the compliance thresholds in Table 4 of
this AD.
[[Page 683]]
Table 4.--Meterpanel Assembly--Not Repaired
----------------------------------------------------------------------------------------------------------------
Parts exceeding initial
Initial inspection Repetitive inspection inspection cycles
Engine series cycles-since-new (CSN) cycles (cycles-since- (cycles-in-service
last-inspection (CSLI)) (CIS))
----------------------------------------------------------------------------------------------------------------
(1) RB211-524D4, -524G, and -524H.... Within 1,000 to 1,200 Within 400 CSLI........ Within 50 CIS after the
CSN. effective date of this
AD.
(2) RB211-524D4, -524G, and -524H Within 1,800 to 2,000 Within 400 CSLI........ Within 50 CIS after the
that have not used RB211-524H CSN. effective date of this
ratings at any time. AD.
----------------------------------------------------------------------------------------------------------------
Inspections of Meterpanel Assemblies--Repaired
(J) Borescope-inspect meterpanel assemblies, incorporating
Service Bulletin (SB) No. RB.211-72-7998, that have been previously
repaired. Use paragraphs 3.B.(1) through 3.B.(7) of the
Accomplishment Instructions of RR ASB No. RB.211-72-AB482, Revision
9, dated July 28, 2003, and the compliance thresholds in Table 5 of
this AD.
Table 5.--Meterpanel Assembly--Repaired
----------------------------------------------------------------------------------------------------------------
Parts exceeding initial
Initial inspection Repetitive inspection inspection cycles
Engine series cycles (cycles-since- cycles (cycles-since- (cycles-in-service
last-repair (CSLR)) last-inspection (CSLI)) (CIS))
----------------------------------------------------------------------------------------------------------------
(1) RB211-524D4, -524G, and -524H.... Within 500 to 700 CSLR. Within 400 CSLI........ Within 50 CIS after the
effective date of this
AD.
----------------------------------------------------------------------------------------------------------------
Note 3: There is no requirement to inspect meter panels for
combustors to a pre-RR SB No. RB.211-72-7998 standard.
Reject Parts
(k) Replace parts that exceed the acceptance criteria.
Information about the acceptance criteria can be found in the
Aircraft Maintenance Manual, 72-00-00, Inspection/Check.
Mandatory Terminating Action
(l) Replace any front combustion liner assembly that has a P/N
listed in paragraph (c) of this AD at the next shop visit or within
10,000 CSN but no later than December 31, 2012.
(m) Replacement of the front combustion liner assembly with a
front combustion liner assembly that incorporates the modifications
in RR SB No. RB.211-72-9670 or RR SB No. RB.211-72-9764 in the
RB211-524B02, -524B2, -524B3, -524B4, -524C2 and -524D4 engines
constitutes terminating action to the repetitive inspections in
paragraphs (f), (g), (h), (i), and (j), of this AD.
(n) Replacement of the front combustion liner assembly with a
front combustion liner assembly that incorporates the modifications
in RR SB No. RB.211-72-9764 in the RB211-524G and -524H engines
constitutes terminating action to the repetitive inspections in
paragraphs (f), (g), (h), (i), and (j) of this AD.
Definition of Shop Visit
(o) For the purpose of this AD, a shop visit is defined as any
time that the 04 module is removed for refurbishment or overhaul.
Alternative Methods of Compliance
(p) The Manager, Engine Certification Office, has the authority
to approve alternative methods of compliance for this AD if
requested using the procedures found in 14 CFR 39.19.
Material Incorporated by Reference
(q) You must use the Rolls-Royce plc (RR) Alert Service Bulletin
(ASB) and Service Bulletins (SB's) listed in Table 6 of this AD to
do the inspections and replacements required by this AD. The
Director of the Federal Register approved the incorporation by
reference of RR ASB No. RB.211-72-AB482, Revision 9, dated July 28,
2003; SB's No. RB.211-72-9764, Revision 3, dated January 16, 1998,
No. RB.211-72-9670, Original Issue, dated August 27, 1993; and SB
No. RB.211-72-9764 Supplement, Revision 1, dated January 16, 1998;
in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You can get
copies at the FAA, New England Region, Office of the Regional
Counsel, 12 New England Executive Park, Burlington, MA; or at the
National Archives and Records Administration (NARA). For information
on the availability of this material at NARA, call 202-741-6030; or
go to: https://www.archives.gov/federal_register/code_of_
federal_regulations/ibr_locations.html. Table 6 follows:
Table 6.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
Page number(s) shown Revision level shown
Service bulletin on the page on the page Date shown on the page
----------------------------------------------------------------------------------------------------------------
RB.211-72-AB482,................... All................... 9..................... July 28, 2003.
Total Pages: 12
RB.211-72-9670,.................... All................... Original.............. Aug. 27, 1993.
Total Pages: 49
RB.211-72-9764..................... 1..................... 3..................... Jan. 16, 1998.
2..................... Original.............. Aug. 20, 1993.
3, 4.................. 3..................... Jan. 16, 1998.
5..................... 1..................... Aug. 25, 1995.
6..................... 3..................... Jan. 16, 1998.
7-10.................. Original.............. Aug. 20, 1993.
11.................... 3..................... Jan. 16, 1998.
12-30................. Original.............. Aug. 20, 1993.
Total Pages: 30
RB.211-72-9764 Supplement.......... 1..................... 1..................... Jan. 16, 1998.
Total Pages: 1
----------------------------------------------------------------------------------------------------------------
[[Page 684]]
Related Information
(r) Civil Aviation Authority airworthiness directive AD G-2003-
0011, dated October 1, 2003, (previously 005-07-95, dated November
15, 2001), also addresses the subject of this AD. Aircraft
Maintenance Manual 72-00-00 also addresses the subject of this AD.
Issued in Burlington, Massachusetts, on December 20, 2004.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 05-85 Filed 1-4-05; 8:45 am]
BILLING CODE 4910-13-P
