Airworthiness Directives; BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ Airplanes, 7565-7568 [E9-3400]
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Federal Register / Vol. 74, No. 31 / Wednesday, February 18, 2009 / Proposed Rules
RB211 Trent 875–17, Trent 877–17, Trent
884–17, Trent 884B–17, Trent 892–17, Trent
892B–17, and Trent 895–17 turbofan engines,
with high-pressure (HP) compressor stage 1–
4 shafts, part number (P/N) FK32580,
installed. These engines are installed on, but
not limited to, Boeing 777 series airplanes.
Reason
(d) European Aviation Safety Agency
(EASA) AD 2008–0099, dated May 21, 2008
(corrected June 12, 2008) states the unsafe
condition is as follows:
During manufacture of high-pressure (HP)
compressor stage 1 discs, a small number of
parts have been rejected due to a machining
defect that was found during inspection.
Analysis of the possibility of less severe
examples having been undetected and passed
into service has concluded that action is
required to reduce the risk of failure. It is
therefore necessary to reduce the life limit
from that currently published for the
applicable parts.
The HP compressor stage 1 disc is part of the
HP compressor stage 1–4 shaft, P/N FK32580.
We are issuing this AD to prevent
uncontained failure of the HP compressor
stage 1 disc, resulting in an in-flight engine
shutdown and possible damage to the
airplane.
Actions and Compliance
(e) Unless already done, do the following
actions.
(1) RB211 Trent 800 critical part lives may
be monitored by one of two methods:
‘‘Multiple Flight Profile Monitoring’’, or
‘‘Heavy Flight Profile’’. Information on these
profiles can be found in the RR Engine
Manual Airworthiness Limitations Section.
(2) Standard Duty Cycles (SDC) is the
product of Flight Cycles and Beta Factor.
Information on Flight Cycles and Beta Factor
can be found in the RR Engine Manual
Airworthiness Limitations Section.
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Multiple Flight Profile Monitoring Parts
(3) For RB211 Trent 800 engines being
monitored by ‘‘Multiple Flight Profile
Monitoring,’’ do the following:
(i) On the effective date of this AD, if the
life of HP compressor stage 1–4 shaft, P/N
FK32580, is equal to or over 5,580 SDC, then
the part must be withdrawn from service
before exceeding 7,780 SDC.
(ii) On the effective date of this AD, if the
life of HP compressor stage 1–4 shaft, P/N
FK32580, is between 3,380 and 5,580 SDC,
then the part must be withdrawn from
service before exceeding an additional 2,200
SDC.
(iii) On the effective date of this AD, if the
life of HP compressor stage 1–4 shaft, P/N
FK32580, is equal to or below 3,380 SDC,
then the part must be withdrawn from
service before exceeding 5,580 SDC.
Reassessment of the Revised Life Limit
(4) Operators should be aware that
reassessment of the revised life limit in
accordance with this AD (including possible
reassessment per the applicable
subparagraph (e)(3)(i), (e)(3)(ii), or (e)(3)(iii)
of this AD, will be necessary if, at some time
in the future, the operator changes the flight
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profile that was applicable before the
Effective Date of this AD, such that parts
which are the subject of this AD are affected.
To recalculate the revised life limit, the life
of the part in SDC at the Effective Date of this
AD, must be recalculated from the part’s
entry into service (zero life), and must use
the Beta Factor(s) for the new Flight
Profile(s).
DEPARTMENT OF TRANSPORTATION
Heavy Flight Profile Parts
Airworthiness Directives; BAE
Systems (Operations) Limited Model
BAe 146 and Avro 146–RJ Airplanes
(5) For RB211 Trent 800 engines being
monitored by ‘‘Heavy Flight Profile,’’ do the
following:
(i) On the effective date of this AD, if the
life of HP compressor stage 1–4 shaft, P/N
FK32580, is equal to or over 5,280 flight
cycles, then the part must be withdrawn from
service before exceeding 7,480 flight cycles.
(ii) On the effective date of this AD, if the
life of HP compressor stage 1–4 shaft, P/N
FK32580, is between 3,080 flight cycles and
5,280 flight cycles, then the part must be
withdrawn from service before exceeding an
additional 2,200 flight cycles.
(iii) On the effective date of this AD, if the
life of HP compressor stage 1–4 shaft, P/N
FK32580, is equal to or below 3,080 flight
cycles, then the part must be withdrawn from
service before exceeding 5,280 flight cycles.
Alternative Methods of Compliance
(AMOCs)
(f) The Manager, Engine Certification
Office, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19.
Related Information
(g) Refer to EASA Airworthiness Directive
2008–0099, dated May 21, 2008 (corrected
June 12, 2008), and Rolls-Royce plc Alert
Service Bulletin No. RB.211–72–AF825,
Revision 1, dated September 8, 2008, for
related information. Contact Rolls-Royce plc,
PO Box 31, Derby, England, DE248BJ;
telephone: 011–44–1332–242424; fax: 011–
44–1332–245418, for a copy of this service
information.
(h) Contact James Lawrence, Aerospace
Engineer, Engine Certification Office, FAA,
Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: james.lawrence@faa.gov;
telephone (781) 238–7176; fax (781) 238–
7199, for more information about this AD.
Issued in Burlington, Massachusetts, on
February 10, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E9–3358 Filed 2–17–09; 8:45 am]
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0133; Directorate
Identifier 2008–NM–107–AD]
RIN 2120–AA64
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to all BAE
Systems (Operations) Limited Model
BAe 146 and Avro 146–RJ airplanes.
The existing AD currently requires
repetitive inspections for corrosion of
frames 15, 18, 41, and 43 and applicable
related investigative and corrective
actions. The existing AD also provides
an optional action that would extend
the repetitive inspection interval. This
proposed AD would add a high
frequency eddy current inspection for
corrosion of the outer frame flanges and
door hinge bosses of frames 15, 18, 41,
and 43. This proposed AD results from
a report indicating that corrosion has
been detected in the outer frame flanges
and door hinge bosses during scheduled
maintenance. We are proposing this AD
to prevent reduced structural integrity
of the airplane.
DATES: We must receive comments on
this proposed AD by March 20, 2009.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
For service information identified in
this proposed AD, contact BAE Systems
Regional Aircraft, 13850 McLearen
Road, Herndon, Virginia 20171;
telephone 703–736–1080; e-mail
raebusiness@baesystems.com; Internet
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Federal Register / Vol. 74, No. 31 / Wednesday, February 18, 2009 / Proposed Rules
https://www.baesystems.com/Businesses/
RegionalAircraft/index.htm. You may
review copies of the referenced service
information at the FAA, Transport
Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington. For
information on the availability of this
material at the FAA, call 425–227–1221
or 425–227–1152.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1175; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2009–0133; Directorate Identifier
2008–NM–107–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
On May 31, 2006, we issued AD
2006–12–09, amendment 39–14634 (71
FR 33602, June 12, 2006), for certain
BAE Systems (Operations) Limited
Model BAe 146 and Avro 146–RJ
airplanes. That AD requires repetitive
inspections for corrosion of frames 15,
18, 41, and 43 and applicable related
investigative and corrective actions.
That AD also provides an optional
action that would extend the repetitive
inspection interval. That AD resulted
from a report indicating that in some
cases the inspections required by an
existing AD revealed no damage, yet
frame corrosion and cracking were later
found during scheduled maintenance in
the two forward fuselage frames 15 and
18. We issued that AD to prevent
reduced structural integrity of the
airplane.
Actions Since Existing AD Was Issued
Since we issued AD 2006–12–09, we
have received a report indicating that
corrosion has been detected in the outer
frame flanges and door hinge bosses
during scheduled maintenance.
Relevant Service Information
BAE Systems (Operations) Limited
has issued Inspection Service Bulletin
ISB.53–182, Revision 1, dated August 6,
2007. We referred to BAE Systems
(Operations) Limited Inspection Service
Bulletin ISB.53–182, dated March 16,
2005, as the appropriate source of
service information for accomplishing
the required actions of AD 2006–12–09.
The procedures in Revision 1 are
essentially the same as the original issue
of the service bulletin, except Revision
1 of the service bulletin adds procedures
for doing a high frequency eddy current
(HFEC) inspection for corrosion of the
outer frame flanges and door hinge
bosses of frames 15, 18, 41, and 43.
Accomplishing the actions specified in
the service information is intended to
adequately address the unsafe
condition. The European Aviation
Safety Agency mandated the service
information and issued airworthiness
directive 2008–0092 R1, dated May 15,
2008 (referred to after this as ‘‘the
MCAI’’), to ensure the continued
airworthiness of these airplanes in the
European Union. The compliance times
for the new actions are the same as for
the existing actions.
FAA’s Determination and Requirements
of the Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
This proposed AD would supersede
AD 2006–12–09 and would retain the
requirements of the existing AD. This
proposed AD would also require
accomplishing the additional inspection
specified in the service bulletin
described previously.
Change to Existing AD
This proposed AD would retain all
requirements of AD 2006–12–09. Since
AD 2006–12–09 was issued, the AD
format has been revised, and certain
paragraphs have been rearranged. As a
result, the corresponding paragraph
identifiers have changed in this
proposed AD, as listed in the following
table:
REVISED PARAGRAPH IDENTIFIERS
Requirement in AD
2006–12–09
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
(f) .............
(g) ............
(h) ............
(i) .............
(j) .............
Corresponding
requirement in this
proposed AD
Paragraph
Paragraph
Paragraph
Paragraph
Paragraph
(g).
(h).
(i).
(p).
(j).
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this proposed AD.
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ESTIMATED COSTS
Action
HFEC inspection, per inspection cycle (required by AD
2006–12–09) ....................................................................
Detailed Inspection, per inspection cycle (required by AD
2006–12–09) ....................................................................
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Average labor
rate per hour
Work hours
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Cost per
airplane
Number of
U.S.-registered
airplanes
Fleet cost
5
$400
1
$400
3
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$80
80
240
1
240
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ESTIMATED COSTS—Continued
Action
HFEC inspection, per inspection cycle (new proposed action) ...................................................................................
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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
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket. See the ADDRESSES section
for a location to examine the regulatory
evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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Work hours
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80
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–14634 (71
FR 33602, June 12, 2006) and adding the
following new airworthiness directive
(AD):
BAE Systems (Operations) Limited
(Formerly British Aerospace Regional
Aircraft): Docket No. FAA–2009–0133;
Directorate Identifier 2008–NM–107–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by March 20, 2009.
Affected ADs
(b) This AD supersedes AD 2006–12–09.
Applicability
(c) This AD applies to all BAE Systems
(Operations) Limited Model BAe 146–100A,
–200A, and –300A series airplanes; and
Model Avro 146–RJ70A, 146–RJ85A, and
146–RJ100A airplanes; certificated in any
category.
Subject
(d) Air Transport Association (ATA) of
America Code 53: Fuselage.
Unsafe Condition
(e) This AD results from a report indicating
that corrosion has been detected in the outer
frame flanges and door hinge bosses during
scheduled maintenance. We are issuing this
AD to prevent reduced structural integrity of
the airplane.
Compliance
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2006–
12–09
Repetitive Inspections
(g) Use high-frequency eddy current
(HFEC) and detailed methods to inspect for
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Cost per
airplane
400
Number of
U.S.-registered
airplanes
1
Fleet cost
400
signs of corrosion (including cracks,
blistering, or flaking paint) of frames 15, 18,
41, and 43, in accordance with the
Accomplishment Instructions of BAE
Systems (Operations) Limited Inspection
Service Bulletin ISB.53–182, dated March 16,
2005, except as required by paragraph (k) of
this AD. Inspect at the applicable time
specified in 1.D. ‘‘Compliance’’ of BAE
Systems (Operations) Limited Inspection
Service Bulletin ISB.53–182, dated March 16,
2005. Application of corrosion-preventive
treatment, in accordance with BAE Systems
(Operations) Limited Inspection Service
Bulletin ISB.53–182, dated March 16, 2005;
or Revision 1, dated August 6, 2007; extends
the repetitive inspection interval, as specified
in Table 2 in 1.D. ‘‘Compliance’’ of BAE
Systems (Operations) Limited Inspection
Service Bulletin ISB.53–182, dated March 16,
2005.
Note 1: For the purposes of this AD, a
detailed inspection is: ‘‘An intensive
examination of a specific item, installation,
or assembly to detect damage, failure, or
irregularity. Available lighting is normally
supplemented with a direct source of good
lighting at an intensity deemed appropriate.
Inspection aids such as mirror, magnifying
lenses, etc., may be necessary. Surface
cleaning and elaborate procedures may be
required.’’
Corrective Action
(h) If any discrepancy is found during any
inspection required by paragraph (g) of this
AD: Before further flight, perform applicable
related investigative/corrective actions in
accordance with the Accomplishment
Instructions of BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.53–
182, dated March 16, 2005, except as
required by paragraphs (i) and (k) of this AD.
Exceptions to Service Bulletin Specifications
(i) If BAE Systems (Operations) Limited
Inspection Service Bulletin ISB.53–182,
dated March 16, 2005, specifies to contact the
manufacturer for appropriate action, before
further flight, repair per a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the Civil Aviation Authority (or its delegated
agent); or European Aviation Safety Agency
(EASA) (or its delegated agent).
(j) Where BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.53–
182, dated March 16, 2005, specifies a
compliance time after the issuance of the
service bulletin, this AD requires compliance
within the specified compliance time after
July 17, 2006 (the effective date of AD 2006–
12–09). Where BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.53–
182, dated March 16, 2005, specifies a
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compliance time ‘‘since date of construction’’
of the airplane, this AD requires compliance
since the date of issuance of the original
standard airworthiness certificate or the date
of issuance of the original export certificate
of airworthiness.
New Requirements of This AD
New Service Bulletin
(k) As of the effective date of this AD: Do
the actions required by paragraphs (g) and (h)
of this AD in accordance with the
Accomplishment Instructions of BAE
Systems (Operations) Limited Inspection
Service Bulletin ISB.53–182, Revision 1,
dated August 6, 2007, except as required by
paragraph (n) of this AD.
Additional Inspection Areas
(l) At the applicable compliance time
specified in paragraph (g) of this AD, except
as provided by paragraph (o) of this AD; or
within six months after the effective date of
this AD; whichever occurs later: Do an HFEC
inspection for corrosion of the outer frame
flanges and door hinge bosses of frames 15,
18, 41, and 43, in accordance with the
Accomplishment Instructions of BAE
Systems (Operations) Limited Inspection
Service Bulletin ISB.53–182, Revision 1,
dated August 6, 2007 (‘‘the service bulletin’’).
Repeat the inspection thereafter at the
applicable time specified in paragraph 1.D.,
‘‘Compliance,’’ of the service bulletin.
Application of corrosion-preventive
treatment, in accordance with the
Accomplishment Instructions of the service
bulletin, extends the repetitive inspection
interval, as specified in Table 2 in paragraph
1.D., ‘‘Compliance,’’ of the service bulletin.
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Corrective Action for Additional Inspection
(m) If any discrepancy is found during any
inspection required by paragraph (l) of this
AD: Before further flight, perform applicable
related investigative/corrective actions in
accordance with the Accomplishment
Instructions of BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.53–
182, Revision 1, dated August 6, 2007, except
as required by paragraph (n) of this AD.
Exception to BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.53–
182, Revision 1
(n) If BAE Systems (Operations) Limited
Inspection Service Bulletin ISB.53–182,
Revision 1, dated August 6, 2007, specifies to
contact the manufacturer for appropriate
action, before further flight, repair per a
method approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or EASA (or its
delegated agent).
(o) Where BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.53–
182, Revision 1, dated August 6, 2007,
specifies a compliance time after the issuance
of the service bulletin, this AD requires
compliance within the specified compliance
time after the effective date of this AD. Where
BAE Systems (Operations) Limited
Inspection Service Bulletin ISB.53–182,
Revision 1, dated August 6, 2007, specifies a
compliance time ‘‘since date of construction’’
of the airplane, this AD requires compliance
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since the date of issuance of the original
airworthiness certificate or the date of
issuance of the original export certificate of
airworthiness.
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
No Reporting
(p) Although BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.53–
182, dated March 16, 2005; and Revision 1,
dated August 6, 2007; specify to submit
information to the manufacturer, this AD
does not include such a requirement.
Two cases of main hydraulic accumulator
failure have been reported, one of which was
caused by corrosion. Investigation has shown
that a severe failure can occur to any of the
four hydraulic accumulators which are
installed in the hydraulic compartment.
Either one of the two end parts on the
accumulator may depart from the pressure
vessel due to corrosion. This condition, if not
corrected, is likely to degrade the
functionality of the hydraulic system,
possibly resulting in degradation or total loss
of control of the landing gear, flap actuation
and brakes. A severe failure during flight may
even result in debris penetrating and exiting
the fuselage outer skin. When such a failure
occurs while the aircraft is on the ground, as
in the two reported cases, this may cause
severe damage to the fuselage and result in
injuries to persons nearby.
Alternative Methods of Compliance (AMOCs)
(q) The Manager, International Branch,
ANM–116, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. Send
information to ATTN: Todd Thompson,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue SW., Renton,
Washington 98057–3356; telephone (425)
227–1175; fax (425) 227–1149. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as
appropriate, or lacking a principal inspector,
your local Flight Standards District Office.
The AMOC approval letter must specifically
reference this AD.
Related Information
(r) European Aviation Safety Agency
airworthiness directive 2008–0092 R1, dated
May 15, 2008, also addresses the subject of
this AD.
Issued in Renton, Washington, on February
5, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–3400 Filed 2–17–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0134; Directorate
Identifier 2008–NM–162–AD]
RIN 2120–AA64
Airworthiness Directives; Saab AB,
Saab Aerosystems Model SAAB 340A
(SAAB/SF340A) and SAAB 340B
Airplanes
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
SUMMARY: We propose to adopt a new
Airworthiness Directive (AD) for the
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
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The proposed AD would require actions
that are intended to address the unsafe
condition described in the MCAI.
DATES: We must receive comments on
this proposed AD by March 20, 2009.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–40, 1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and
5 p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Saab Aircraft
AB, SAAB Aerosystems, SE–581 88,
¨
Linkoping, Sweden; telephone +46 13
18 5591; fax +46 13 18 4874; e-mail
saab2000.techsupport@saabgroup.com;
Internet https://www.saabgroup.com.
You may review copies of the
referenced service information at the
FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA,
call 425–227–1221 or 425–227–1152.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
E:\FR\FM\18FEP1.SGM
18FEP1
Agencies
[Federal Register Volume 74, Number 31 (Wednesday, February 18, 2009)]
[Proposed Rules]
[Pages 7565-7568]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-3400]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0133; Directorate Identifier 2008-NM-107-AD]
RIN 2120-AA64
Airworthiness Directives; BAE Systems (Operations) Limited Model
BAe 146 and Avro 146-RJ Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to all BAE Systems (Operations) Limited
Model BAe 146 and Avro 146-RJ airplanes. The existing AD currently
requires repetitive inspections for corrosion of frames 15, 18, 41, and
43 and applicable related investigative and corrective actions. The
existing AD also provides an optional action that would extend the
repetitive inspection interval. This proposed AD would add a high
frequency eddy current inspection for corrosion of the outer frame
flanges and door hinge bosses of frames 15, 18, 41, and 43. This
proposed AD results from a report indicating that corrosion has been
detected in the outer frame flanges and door hinge bosses during
scheduled maintenance. We are proposing this AD to prevent reduced
structural integrity of the airplane.
DATES: We must receive comments on this proposed AD by March 20, 2009.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this proposed AD, contact BAE
Systems Regional Aircraft, 13850 McLearen Road, Herndon, Virginia
20171; telephone 703-736-1080; e-mail raebusiness@baesystems.com;
Internet
[[Page 7566]]
https://www.baesystems.com/Businesses/RegionalAircraft/index.htm. You
may review copies of the referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at the
FAA, call 425-227-1221 or 425-227-1152.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone 800-647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1175; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2009-0133;
Directorate Identifier 2008-NM-107-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On May 31, 2006, we issued AD 2006-12-09, amendment 39-14634 (71 FR
33602, June 12, 2006), for certain BAE Systems (Operations) Limited
Model BAe 146 and Avro 146-RJ airplanes. That AD requires repetitive
inspections for corrosion of frames 15, 18, 41, and 43 and applicable
related investigative and corrective actions. That AD also provides an
optional action that would extend the repetitive inspection interval.
That AD resulted from a report indicating that in some cases the
inspections required by an existing AD revealed no damage, yet frame
corrosion and cracking were later found during scheduled maintenance in
the two forward fuselage frames 15 and 18. We issued that AD to prevent
reduced structural integrity of the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 2006-12-09, we have received a report indicating
that corrosion has been detected in the outer frame flanges and door
hinge bosses during scheduled maintenance.
Relevant Service Information
BAE Systems (Operations) Limited has issued Inspection Service
Bulletin ISB.53-182, Revision 1, dated August 6, 2007. We referred to
BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53-
182, dated March 16, 2005, as the appropriate source of service
information for accomplishing the required actions of AD 2006-12-09.
The procedures in Revision 1 are essentially the same as the original
issue of the service bulletin, except Revision 1 of the service
bulletin adds procedures for doing a high frequency eddy current (HFEC)
inspection for corrosion of the outer frame flanges and door hinge
bosses of frames 15, 18, 41, and 43. Accomplishing the actions
specified in the service information is intended to adequately address
the unsafe condition. The European Aviation Safety Agency mandated the
service information and issued airworthiness directive 2008-0092 R1,
dated May 15, 2008 (referred to after this as ``the MCAI''), to ensure
the continued airworthiness of these airplanes in the European Union.
The compliance times for the new actions are the same as for the
existing actions.
FAA's Determination and Requirements of the Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
This proposed AD would supersede AD 2006-12-09 and would retain the
requirements of the existing AD. This proposed AD would also require
accomplishing the additional inspection specified in the service
bulletin described previously.
Change to Existing AD
This proposed AD would retain all requirements of AD 2006-12-09.
Since AD 2006-12-09 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this proposed AD, as listed in
the following table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement in
Requirement in AD 2006-12-09 this proposed AD
------------------------------------------------------------------------
Paragraph (f)............................. Paragraph (g).
Paragraph (g)............................. Paragraph (h).
Paragraph (h)............................. Paragraph (i).
Paragraph (i)............................. Paragraph (p).
Paragraph (j)............................. Paragraph (j).
------------------------------------------------------------------------
Costs of Compliance
The following table provides the estimated costs for U.S. operators
to comply with this proposed AD.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of U.S.-
Action Work hours Average labor Cost per registered Fleet cost
rate per hour airplane airplanes
----------------------------------------------------------------------------------------------------------------
HFEC inspection, per inspection 5 $80 $400 1 $400
cycle (required by AD 2006-12-
09)............................
Detailed Inspection, per 3 80 240 1 240
inspection cycle (required by
AD 2006-12-09).................
[[Page 7567]]
HFEC inspection, per inspection 5 80 400 1 400
cycle (new proposed action)....
----------------------------------------------------------------------------------------------------------------
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket. See the
ADDRESSES section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-14634 (71 FR 33602, June 12, 2006) and adding the
following new airworthiness directive (AD):
BAE Systems (Operations) Limited (Formerly British Aerospace
Regional Aircraft): Docket No. FAA-2009-0133; Directorate Identifier
2008-NM-107-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by March 20,
2009.
Affected ADs
(b) This AD supersedes AD 2006-12-09.
Applicability
(c) This AD applies to all BAE Systems (Operations) Limited
Model BAe 146-100A, -200A, and -300A series airplanes; and Model
Avro 146-RJ70A, 146-RJ85A, and 146-RJ100A airplanes; certificated in
any category.
Subject
(d) Air Transport Association (ATA) of America Code 53:
Fuselage.
Unsafe Condition
(e) This AD results from a report indicating that corrosion has
been detected in the outer frame flanges and door hinge bosses
during scheduled maintenance. We are issuing this AD to prevent
reduced structural integrity of the airplane.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2006-12-09
Repetitive Inspections
(g) Use high-frequency eddy current (HFEC) and detailed methods
to inspect for signs of corrosion (including cracks, blistering, or
flaking paint) of frames 15, 18, 41, and 43, in accordance with the
Accomplishment Instructions of BAE Systems (Operations) Limited
Inspection Service Bulletin ISB.53-182, dated March 16, 2005, except
as required by paragraph (k) of this AD. Inspect at the applicable
time specified in 1.D. ``Compliance'' of BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.53-182, dated March 16,
2005. Application of corrosion-preventive treatment, in accordance
with BAE Systems (Operations) Limited Inspection Service Bulletin
ISB.53-182, dated March 16, 2005; or Revision 1, dated August 6,
2007; extends the repetitive inspection interval, as specified in
Table 2 in 1.D. ``Compliance'' of BAE Systems (Operations) Limited
Inspection Service Bulletin ISB.53-182, dated March 16, 2005.
Note 1: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
Corrective Action
(h) If any discrepancy is found during any inspection required
by paragraph (g) of this AD: Before further flight, perform
applicable related investigative/corrective actions in accordance
with the Accomplishment Instructions of BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.53-182, dated March 16,
2005, except as required by paragraphs (i) and (k) of this AD.
Exceptions to Service Bulletin Specifications
(i) If BAE Systems (Operations) Limited Inspection Service
Bulletin ISB.53-182, dated March 16, 2005, specifies to contact the
manufacturer for appropriate action, before further flight, repair
per a method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or the Civil Aviation Authority
(or its delegated agent); or European Aviation Safety Agency (EASA)
(or its delegated agent).
(j) Where BAE Systems (Operations) Limited Inspection Service
Bulletin ISB.53-182, dated March 16, 2005, specifies a compliance
time after the issuance of the service bulletin, this AD requires
compliance within the specified compliance time after July 17, 2006
(the effective date of AD 2006-12-09). Where BAE Systems
(Operations) Limited Inspection Service Bulletin ISB.53-182, dated
March 16, 2005, specifies a
[[Page 7568]]
compliance time ``since date of construction'' of the airplane, this
AD requires compliance since the date of issuance of the original
standard airworthiness certificate or the date of issuance of the
original export certificate of airworthiness.
New Requirements of This AD
New Service Bulletin
(k) As of the effective date of this AD: Do the actions required
by paragraphs (g) and (h) of this AD in accordance with the
Accomplishment Instructions of BAE Systems (Operations) Limited
Inspection Service Bulletin ISB.53-182, Revision 1, dated August 6,
2007, except as required by paragraph (n) of this AD.
Additional Inspection Areas
(l) At the applicable compliance time specified in paragraph (g)
of this AD, except as provided by paragraph (o) of this AD; or
within six months after the effective date of this AD; whichever
occurs later: Do an HFEC inspection for corrosion of the outer frame
flanges and door hinge bosses of frames 15, 18, 41, and 43, in
accordance with the Accomplishment Instructions of BAE Systems
(Operations) Limited Inspection Service Bulletin ISB.53-182,
Revision 1, dated August 6, 2007 (``the service bulletin''). Repeat
the inspection thereafter at the applicable time specified in
paragraph 1.D., ``Compliance,'' of the service bulletin. Application
of corrosion-preventive treatment, in accordance with the
Accomplishment Instructions of the service bulletin, extends the
repetitive inspection interval, as specified in Table 2 in paragraph
1.D., ``Compliance,'' of the service bulletin.
Corrective Action for Additional Inspection
(m) If any discrepancy is found during any inspection required
by paragraph (l) of this AD: Before further flight, perform
applicable related investigative/corrective actions in accordance
with the Accomplishment Instructions of BAE Systems (Operations)
Limited Inspection Service Bulletin ISB.53-182, Revision 1, dated
August 6, 2007, except as required by paragraph (n) of this AD.
Exception to BAE Systems (Operations) Limited Inspection Service
Bulletin ISB.53-182, Revision 1
(n) If BAE Systems (Operations) Limited Inspection Service
Bulletin ISB.53-182, Revision 1, dated August 6, 2007, specifies to
contact the manufacturer for appropriate action, before further
flight, repair per a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA (or
its delegated agent).
(o) Where BAE Systems (Operations) Limited Inspection Service
Bulletin ISB.53-182, Revision 1, dated August 6, 2007, specifies a
compliance time after the issuance of the service bulletin, this AD
requires compliance within the specified compliance time after the
effective date of this AD. Where BAE Systems (Operations) Limited
Inspection Service Bulletin ISB.53-182, Revision 1, dated August 6,
2007, specifies a compliance time ``since date of construction'' of
the airplane, this AD requires compliance since the date of issuance
of the original airworthiness certificate or the date of issuance of
the original export certificate of airworthiness.
No Reporting
(p) Although BAE Systems (Operations) Limited Inspection Service
Bulletin ISB.53-182, dated March 16, 2005; and Revision 1, dated
August 6, 2007; specify to submit information to the manufacturer,
this AD does not include such a requirement.
Alternative Methods of Compliance (AMOCs)
(q) The Manager, International Branch, ANM-116, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. Send information to ATTN: Todd
Thompson, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton,
Washington 98057-3356; telephone (425) 227-1175; fax (425) 227-1149.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
Related Information
(r) European Aviation Safety Agency airworthiness directive
2008-0092 R1, dated May 15, 2008, also addresses the subject of this
AD.
Issued in Renton, Washington, on February 5, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-3400 Filed 2-17-09; 8:45 am]
BILLING CODE 4910-13-P