Airworthiness Directives; Bombardier Model BD-700-1A10 and BD-700-1A11 Airplanes, 34225-34229 [E9-16467]
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Federal Register / Vol. 74, No. 134 / Wednesday, July 15, 2009 / Rules and Regulations
TABLE 2—RELATED SERVICE INFORMATION
Airbus Mandatory Service Bulletin
A330–92–3066
A330–92–3066
A340–92–4071
A340–92–4071
A340–92–4071
Revision
................................................................................................................................................
................................................................................................................................................
................................................................................................................................................
................................................................................................................................................
................................................................................................................................................
Material Incorporated by Reference
(i) You must use the applicable service
information contained in Table 3 of this AD
to do the actions required by this AD, unless
the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Airbus SA—Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80, e-mail
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
01
02
01
02
03
Date
August 1, 2008.
March 19, 2009.
August 1, 2008.
November 28, 2008.
March 19, 2009.
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(4) You may also review copies of the
service information that is incorporated by
reference 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 3—MATERIAL INCORPORATED BY REFERENCE
Airbus Mandatory Service Bulletin
A330–92–3066
A330–92–3066
A340–92–4071
A340–92–4071
A340–92–4071
................................................................................................................................................
................................................................................................................................................
................................................................................................................................................
................................................................................................................................................
................................................................................................................................................
Issued in Renton, Washington, on July 2,
2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–16468 Filed 7–14–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0138; Directorate
Identifier 2008–NM–216–AD; Amendment
39–15966; AD 2009–15–03]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model BD–700–1A10 and BD–700–
1A11 Airplanes
srobinson on DSKHWCL6B1PROD with RULES
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: We are superseding an
existing airworthiness directive (AD) for
the products listed above. This AD
results from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
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Revision
15:15 Jul 14, 2009
Jkt 217001
product. The MCAI describes the unsafe
condition as:
During scheduled maintenance inspection,
a bolt which connects the PCU (power
control unit) to the elevator surface was
found fractured in the assembly. Further
inspection of the assembly revealed that the
bearing on the PCU rod end had seized,
which resulted in damage to the attachment
fitting bushing and fracture of the bolt.
Inspection of other in-service airplanes
revealed two more seized PCU attachment
joints. However, except seizure, no fractured
bolt was found on these airplanes. Failure of
the bolts in both PCUs on one side could
result in disconnection of the elevator control
surface which would lead to flutter and loss
of the aircraft.
*
*
*
*
*
We are issuing this AD to require
actions to correct the unsafe condition
on these products.
DATES: This AD becomes effective
August 19, 2009.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of August 19, 2009.
You may examine the AD
docket on the Internet at https://
www.regulations.gov or in person at the
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC.
ADDRESSES:
PO 00000
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Fmt 4700
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01
02
01
02
03
Date
August 1, 2008.
March 19, 2009.
August 1, 2008.
November 28, 2008.
March 19, 2009.
FOR FURTHER INFORMATION CONTACT:
Pong K. Lee, 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) 228–7324; fax
(516) 794–5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to the specified products. That
NPRM was published in the Federal
Register on February 23, 2009 (74 FR
8045). That NPRM proposed to correct
an unsafe condition for the specified
products. The MCAI states:
During scheduled maintenance inspection,
a bolt which connects the PCU (power
control unit) to the elevator surface was
found fractured in the assembly. Further
inspection of the assembly revealed that the
bearing on the PCU rod end had seized,
which resulted in damage to the attachment
fitting bushing and fracture of the bolt.
Inspection of other in-service airplanes
revealed two more seized PCU attachment
joints. However, except seizure, no fractured
bolt was found on these airplanes. Failure of
the bolts in both PCUs on one side could
result in disconnection of the elevator control
surface which would lead to flutter and loss
of the aircraft.
This Airworthiness Directive (AD) is
issued to mandate the inspection and
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Federal Register / Vol. 74, No. 134 / Wednesday, July 15, 2009 / Rules and Regulations
lubrication of all part number (P/N) GT411–
3800–5 and GT411–3800–7 PCU attachment
joints.
The required actions include
inspections for damage and seizure
(including signs of seizure) of the PCU
attachment joints, an inspection for
damage (including wear damage,
fretting, corrosion, galling, scoring,
fretting wear, and parts that do not meet
inspection requirements) of the PCU
attachment joint components, and
applicable corrective actions. You may
obtain further information by examining
the MCAI in the AD docket.
Explanation of Revised Service
Information
below table. We have changed
paragraphs (f)(1) through (f)(5),
paragraph (f)(7), and paragraphs (g)(1)
and (g)(2) of this AD to add the revised
service information specified in the
following table.
Bombardier has issued the revised
service information specified in the
REVISED SERVICE INFORMATION
Revision
level
Service Bulletin
Bombardier
Bombardier
Bombardier
Bombardier
Alert Service Bulletin A700–1A11–27–024 .................................................................................
Alert Service Bulletin A700–27–066 ............................................................................................
Service Bulletin 700–1A11–27–025 ............................................................................................
Service Bulletin 700–27–067 .......................................................................................................
No additional work is necessary for
airplanes on which the previously
issued service information specified in
the following table has been
accomplished. We have revised
paragraph (f)(6) and added a new
paragraph (g)(3) to this AD to include
credit for accomplishing the actions
02
02
01
01
Date
November
November
November
November
10,
10,
24,
24,
2008.
2008.
2008.
2008.
before the effective date of this AD using
the previously issued service
information.
PREVIOUSLY ISSUED SERVICE INFORMATION
Revision
level
Service Bulletin
Bombardier
Bombardier
Bombardier
Bombardier
Alert Service Bulletin A700–1A11–27–024 .................................................................................
Alert Service Bulletin A700–27–066 ............................................................................................
Service Bulletin 700–1A11–27–025 ............................................................................................
Service Bulletin 700–27–067 .......................................................................................................
01
01
(1)
(1)
Date
October
October
October
October
3,
3,
9,
9,
2008.
2008.
2008.
2008.
1 Original.
Costs of Compliance
We estimate that this AD will affect
about 157 products of U.S. registry.
We estimate that it will take about 4
work-hours per product to comply with
the basic requirements of this AD. The
average labor rate is $80 per work-hour.
Based on these figures, we estimate the
cost of this AD to the U.S. operators to
be $50,240, or $320 per product.
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
srobinson on DSKHWCL6B1PROD with RULES
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
We reviewed the available data and
determined that air safety and the
public interest require adopting the AD
with the changes described previously.
We determined that these changes will
not increase the economic burden on
any operator or increase the scope of the
AD.
policies. Any such differences are
highlighted in a NOTE within the AD.
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow our FAA
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
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Authority for This Rulemaking
PO 00000
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We 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 this AD:
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.
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Federal Register / Vol. 74, No. 134 / Wednesday, July 15, 2009 / Rules and Regulations
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
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 the NPRM, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
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:
■
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–15753 (73 FR
72316, November 28, 2008) and adding
the following new AD:
■
2009–15–03 Bombardier, Inc.: Amendment
39–15966. Docket No. FAA–2009–0138;
Directorate Identifier 2008–NM–216–AD.
control unit) to the elevator surface was
found fractured in the assembly. Further
inspection of the assembly revealed that the
bearing on the PCU rod end had seized,
which resulted in damage to the attachment
fitting bushing and fracture of the bolt.
Inspection of other in-service airplanes
revealed two more seized PCU attachment
joints. However, except seizure, no fractured
bolt was found on these airplanes. Failure of
the bolts in both PCUs on one side could
result in disconnection of the elevator control
surface which would lead to flutter and loss
of the aircraft.
This Airworthiness Directive (AD) is
issued to mandate the inspection and
lubrication of all part number (P/N) GT411–
3800–5 and GT411–3800–7 PCU attachment
joints.
The required actions include inspections
for damage and seizure (including signs of
seizure) of the PCU attachment joints, an
inspection for damage (including wear
damage, fretting, corrosion, galling, scoring,
fretting wear, and parts that do not meet
inspection requirements) of the PCU
attachment joint components, and applicable
corrective actions.
Restatement of Requirements of AD 2008–
24–12:
(f) Unless already done: For airplanes on
which elevator PCUs with P/N GT411–3800–
5 or P/N GT411–3800–7, S/N 0615 and
lower, are installed, excluding P/N GT411–
3800–7 PCUs having a serial number listed
in Table 1 of this AD, and excluding P/N
GT411–3800–7 PCUs on which less than
1,000 flight hours have accumulated on the
PCUs as of December 15, 2008 (the effective
date of AD 2008–24–12), do the actions
specified in paragraphs (f)(1), (f)(2), and (f)(3)
of this AD.
Note 1: Units listed in Table 1 of this AD
have been lubricated by the vendor and the
inspections required by paragraphs (f)(1),
(f)(2), (f)(3), and (f)(4) of this AD are not
required for those units.
TABLE 1—SERIAL NUMBERS
Effective Date
(a) This airworthiness directive (AD)
becomes effective August 19, 2009.
Affected ADs
(b) This AD supersedes AD 2008–24–12,
Amendment 39–15753.
srobinson on DSKHWCL6B1PROD with RULES
Applicability
(c) This AD applies to Bombardier Model
BD–700–1A10 and BD–700–1A11 airplanes,
certificated in any category, serial numbers
(S/Ns) 9002 through 9222 inclusive;
equipped with elevator power control units
(PCUs) having part number (P/N) GT411–
3800–5 or GT411–3800–7.
Subject
(d) Air Transport Association (ATA) of
America Code 27: Flight controls.
Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
During scheduled maintenance inspection,
a bolt which connects the PCU (power
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PO 00000
0030
0031
0033
0041
0046
0060
0062
0066
0081
0083
0087
0092
0097
0101
0105
0108
0109
0111
0110
0119
0130
0138
0141
0145
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0205
0206
0208
0210
0214
0218
0222
0223
0240
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0265
0281
0296
0301
0310
0323
0365
0369
0406
0407
0408
0413
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TABLE 1—SERIAL NUMBERS—
Continued
0156
0161
0163
0164
0165
0171
0173
0174
0178
0179
0181
0183
0188
0190
0191
0197
0198
0420
0427
0429
0430
0431
0433
0435
0438
0453
0491
0495
0504
0506
0513
0533
0536
0586
(1) Within 10 flight cycles or 50 flight
hours after December 15, 2008, whichever
occurs first: Inspect for damage and wear and
lubricate the PCU attachment joints in
accordance with Bombardier Alert Service
Bulletin A700–1A11–27–024, Revision 02,
dated November 10, 2008; or Bombardier
Alert Service Bulletin A700–27–066,
Revision 02, dated November 10, 2008; as
applicable.
(2) Within 90 days or 200 flight hours after
performing the actions required by paragraph
(f)(1) of this AD, whichever occurs first:
Repeat the inspection and lubrication of the
PCU attachment joints in accordance with
Bombardier Alert Service Bulletin A700–
1A11–27–024, Revision 02, dated November
10, 2008; or Bombardier Alert Service
Bulletin A700–27–066, Revision 02, dated
November 10, 2008; as applicable.
(3) Within 45 days or 100 flight hours after
performing the actions required by paragraph
(f)(2) of this AD, whichever occurs first:
Repeat the inspection and lubrication of the
PCU attachment joints in accordance with
Bombardier Alert Service Bulletin A700–
1A11–27–024, Revision 02, dated November
10, 2008; or Bombardier Alert Service
Bulletin A700–27–066, Revision 02, dated
November 10, 2008; as applicable. Repeat the
inspection thereafter at intervals not to
exceed 45 days or 100 flight hours,
whichever occurs first, until paragraph (f)(4)
of this AD is accomplished.
(4) Completion of a disassembly with an
inspection for damage, applicable corrective
actions, and lubrication of the PCU
attachment joint components in accordance
with Bombardier Service Bulletin 700–1A11–
27–025, Revision 01, dated November 24,
2008; or Bombardier Service Bulletin 700–
27–067, Revision 01, dated November 24,
2008; as applicable; constitutes terminating
action for the inspections required by
paragraphs (f)(1), (f)(2), and (f)(3) of this AD.
(5) Unless already done, if any damage or
seizure is found during any inspection
required by paragraphs (f)(1), (f)(2), (f)(3), and
(f)(4) of this AD, before further flight, replace
the affected part in accordance with
Bombardier Service Bulletin 700–1A11–27–
025, Revision 01, dated November 24, 2008;
or Bombardier Service Bulletin 700–27–067,
Revision 01, dated November 24, 2008; as
applicable.
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Federal Register / Vol. 74, No. 134 / Wednesday, July 15, 2009 / Rules and Regulations
(6) Actions done before December 15, 2008,
in accordance with Bombardier Alert Service
Bulletin A700–1A11–27–024 or Bombardier
Alert Service Bulletin A700–27–066, both
dated October 2, 2008; or Revision 01, both
dated October 3, 2008; as applicable; are
acceptable for compliance with the
corresponding requirements of this AD.
(7) Unless already done, submit a report to
Bombardier of all findings found during any
inspection required by paragraphs (f)(1),
(f)(2), (f)(3), and (f)(4) of this AD, in
accordance with the applicable service
bulletin listed in Table 2 of this AD.
(i) If the inspection was done on or after
December 15, 2008: Submit the report within
14 days after the inspection.
(ii) If the inspection was done before
December 15, 2008: Submit the report within
14 days after December 15, 2008.
TABLE 2—SERVICE BULLETINS FOR REPORTS
Revision
level
Service Bulletin
Bombardier
Bombardier
Bombardier
Bombardier
Alert Service Bulletin A700–1A11–27–024 .................................................................................
Alert Service Bulletin A700–27–066 ............................................................................................
Service Bulletin 700–1A11–27–025 ............................................................................................
Service Bulletin 700–27–067 .......................................................................................................
New Requirements of This AD: Actions and
Compliance
(g) Unless already done, do the actions
specified in paragraph (g)(1) or (g)(2) of this
AD, as applicable, at the time specified.
(1) For airplanes identified in paragraph (f)
of this AD: Within 45 days or 100 flight hours
after the effective date of this AD, whichever
occurs first, complete a disassembly with an
inspection for damage, applicable corrective
actions, and lubrication of the PCU
attachment joint components in accordance
with Bombardier Service Bulletin 700–1A11–
27–025, Revision 01, dated November 24,
2008; or Bombardier Service Bulletin 700–
27–067, Revision 01, dated November 24,
2008; as applicable.
(2) For airplanes not identified in
paragraph (f) of this AD on which elevator
PCUs with P/N GT411–3800–7 are installed:
Within 180 days or 400 flight hours after the
effective date of this AD, whichever occurs
first, complete a disassembly with an
inspection for damage, applicable corrective
actions, and lubrication of the PCU
attachment joint components in accordance
with Bombardier Service Bulletin 700–1A11–
27–025, Revision 01, dated November 24,
2008; or Bombardier Service Bulletin 700–
27–067, Revision 01, dated November 24,
2008; as applicable.
(3) Actions done before the effective date
of this AD in accordance with Bombardier
Service Bulletin 700–1A11–27–025, dated
October 9, 2008; or Bombardier Service
Bulletin 700–27–067, dated October 9, 2008;
as applicable; are acceptable for compliance
with the corresponding requirements of this
AD.
FAA AD Differences
Note 2: This AD differs from the MCAI
and/or service information as follows:
Paragraph A.3. of the MCAI requires a onetime inspection; however, since we have
changed the compliance time for the
terminating action in paragraph A.4. of the
MCAI (refer to paragraph (g)(1) of this AD),
paragraph (f)(3) of this AD requires repeating
the inspections until the terminating action
is performed.
Other FAA AD Provisions
(h) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York Aircraft
Certification Office (ACO), 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: Pong K.
Lee, Aerospace Engineer, Airframe and
Propulsion Branch, ANE–171, FAA, New
York ACO, 1600 Stewart Avenue, Suite 410,
Westbury, New York 11590; telephone (516)
228–7324; fax (516) 794–5531. 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.
02
02
01
01
Date
November
November
November
November
10,
10,
24,
24,
2008.
2008.
2008.
2008.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
(4) Special Flight Permits: As described in
Section 21.197 and Section 21.199 of the
Federal Aviation Regulations (14 CFR 21.197
and 21.199), special flight permits are not
allowed.
Related Information
(i) Refer to MCAI Canadian Emergency
Airworthiness Directive CF–2008–31, dated
October 9, 2008, and the service information
specified in Table 2 of this AD, for related
information.
Material Incorporated by Reference
(j) You must use the service information
contained in Table 3 of this AD to do the
actions required by this AD, as applicable,
unless the AD specifies otherwise.
TABLE 3—MATERIAL INCORPORATED BY REFERENCE
Revision
level
Document
srobinson on DSKHWCL6B1PROD with RULES
Bombardier
Bombardier
Bombardier
Bombardier
Alert Service Bulletin A700–1A11–27–024 .................................................................................
Alert Service Bulletin A700–27–066 ............................................................................................
Service Bulletin 700–1A11–27–025 ............................................................................................
Service Bulletin 700–27–067 .......................................................................................................
(1) The Director of the Federal Register
approved the incorporation by reference of
the service information under 5 U.S.C. 552(a)
and 1 CFR part 51.
(2) For service information identified in
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
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15:15 Jul 14, 2009
Jkt 217001
Canada; telephone 514–855–5000; fax 514–
855–7401; e-mail
thd.crj@aero.bombardier.com; Internet https://
www.bombardier.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
PO 00000
Frm 00020
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02
02
01
01
Date
November
November
November
November
10,
10,
24,
24,
2008.
2008.
2008.
2008.
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(4) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
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Federal Register / Vol. 74, No. 134 / Wednesday, July 15, 2009 / Rules and Regulations
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.
Issued in Renton, Washington, on July 2,
2009.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E9–16467 Filed 7–14–09; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Parts 61 and 121
[Docket No. FAA–2006–26139; Amendment
Nos. 61–123 and 121–344]
RIN 2120–AJ01
Part 121 Pilot Age Limit
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
This action amends the Code
of Federal Regulations to conform
certain regulations with recent
legislation raising the upper age limit
for pilots serving in domestic, flag, and
supplemental operations until they
reach their 65th birthday. The
legislation, known as the ‘‘Fair
Treatment for Experienced Pilots Act,’’
raised the upper age limit from age 60
to age 65. The legislation became
effective December 13, 2007. The
intended effect of this action is to
update the Code of Federal Regulations
to reflect the recent legislation.
DATES: These amendments become
effective July 15, 2009. Except as
otherwise required by statute, affected
parties do not have to comply with the
information collection requirements in
§§ 61.23 and 121.440 until the FAA
publishes in the Federal Register the
control number assigned by the Office of
Management and Budget (OMB) for
these information collection
requirements. Publication of the control
number notifies the public that OMB
has approved these information
collection requirements under the
Paperwork Reduction Act of 1995.
FOR FURTHER INFORMATION CONTACT: For
technical questions concerning this rule
contact Lawrence Youngblut, Air
Transportation Division, AFS–200,
Federal Aviation Administration, 800
Independence Avenue, SW.,
Washington, DC 20591; telephone (202)
267–9630, e-mail
lawrence.youngblut@faa.gov. For legal
srobinson on DSKHWCL6B1PROD with RULES
SUMMARY:
VerDate Nov<24>2008
15:15 Jul 14, 2009
Jkt 217001
questions concerning this rule contact
Angela Washington, Office of the Chief
Counsel, AGC–210, Federal Aviation
Administration, 800 Independence
Avenue, SW., Washington, DC 20591;
telephone (202) 267–7556; e-mail
angela.washington@faa.gov.
SUPPLEMENTARY INFORMATION:
Availability of Rulemaking Documents
You can get an electronic copy using
the Internet by:
1. Searching the Federal eRulemaking
Portal at https://www.regulations.gov;
2. Visiting the FAA’s Regulations and
Policies Web page at https://
www.faa.gov/regulations_policies/; or
3. Accessing the Government Printing
Office’s Web page at https://
www.gpoaccess.gov/fr/.
You can also get a copy by sending a
request to the Federal Aviation
Administration, Office of Rulemaking,
ARM–1, 800 Independence Avenue,
SW., Washington, DC 20591, or by
calling (202) 267–9680. Make sure to
identify the amendment number or
docket number of this rulemaking.
Small Business Regulatory Enforcement
Fairness Act
The Small Business Regulatory
Enforcement Fairness Act (SBREFA) of
1996 requires FAA to comply with
small entity requests for information or
advice about compliance with statutes
and regulations within its jurisdiction.
Therefore, any small entity that has a
question regarding this document may
contact their local FAA official, or the
person listed under FOR FURTHER
INFORMATION CONTACT. You can find out
more about SBREFA on the Internet at
our site, https://www.faa.gov/
regulations_policies/rulemaking/
sbre_act/.
Authority for This Rulemaking
The FAA’s authority to issue rules
regarding aviation safety is found in
Title 49 of the United States Code.
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. This rulemaking
fulfills the mandate of H.R. 4343, the
‘‘Fair Treatment for Experienced Pilots
Act,’’ Pub. L. 110–135, hereinafter
referred to as the Act.
Background
On December 13, 2007, the President
signed into law the Act, which raised
the upper age limit for pilots serving in
14 CFR part 121 air carrier operations to
age 65. The legislation took effect
December 13, 2007. As of that date,
§ 121.383(c) of the Code of Federal
PO 00000
Frm 00021
Fmt 4700
Sfmt 4700
34229
Regulations (14 CFR 121.383(c)) ceased
to be effective. Section 121.383(c)
prohibited any air carrier or commercial
operator conducting flights under part
121 from using the services of any
person as a pilot, and prohibited any
person from serving as a pilot, on an
airplane engaged in operations under
part 121 if that person had reached his
or her 60th birthday.
The Act has now been codified at 49
U.S.C. Section 44729. Section 44729 of
Title 49 allows a pilot to ‘‘serve in
multicrew covered operations until
attaining 65 years of age,’’ subject to
certain limitations. For the purposes of
the Act, ‘‘Covered Operations’’ means
‘‘operations under part 121 of Title 14,
Code of Federal Regulations.’’ The Act
specifies a limitation for international
flights. Pursuant to § 44729(c)(1), ‘‘A
pilot who has attained 60 years of age
may serve as pilot-in-command in
covered operations between the United
States and another country only if there
is another pilot in the flight deck crew
who has not yet attained 60 years of
age.’’ Section 44729(c)(2) states that
paragraph (c)(1) ceases to be effective
‘‘on such date as the Convention on
International Civil Aviation provides
that a pilot who has attained 60 years
of age may serve as pilot-in-command in
international commercial operations
without regard to whether there is
another pilot in the flight deck crew
who has not attained age 60.’’
Section 44729(e)(1) states ‘‘No person
who has attained 60 years of age before
the date of enactment of this section
may serve as a pilot for an air carrier
engaged in covered operations unless—
(A) such person is in the employment
of that air carrier in such operations on
such date of enactment as a required
flight deck crew member; or
(B) such person is newly hired by an
air carrier as a pilot on or after such date
of enactment without credit for prior
seniority or prior longevity for benefits
or other terms related to length of
service prior to the date rehired under
any labor agreement or employment
policies of the air carrier.’’
Section 44729(g)(1) requires that,
except as provided by paragraph (g)(2)
‘‘a person serving as a pilot for an air
carrier engaged in covered operations
shall not be subject to different medical
standards, or different, greater, or more
frequent medical examinations, on
account of age unless the Secretary
determines (based on data received or
studies published after the date of
enactment of this section) that different
medical standards, or different, greater,
or more frequent medical examinations,
are needed to ensure an adequate level
of safety in flight.’’
E:\FR\FM\15JYR1.SGM
15JYR1
]]>Agencies
[Federal Register Volume 74, Number 134 (Wednesday, July 15, 2009)]
[Rules and Regulations]
[Pages 34225-34229]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-16467]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0138; Directorate Identifier 2008-NM-216-AD;
Amendment 39-15966; AD 2009-15-03]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model BD-700-1A10 and BD-
700-1A11 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for the products listed above. This AD results from mandatory
continuing airworthiness information (MCAI) originated by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:
During scheduled maintenance inspection, a bolt which connects
the PCU (power control unit) to the elevator surface was found
fractured in the assembly. Further inspection of the assembly
revealed that the bearing on the PCU rod end had seized, which
resulted in damage to the attachment fitting bushing and fracture of
the bolt. Inspection of other in-service airplanes revealed two more
seized PCU attachment joints. However, except seizure, no fractured
bolt was found on these airplanes. Failure of the bolts in both PCUs
on one side could result in disconnection of the elevator control
surface which would lead to flutter and loss of the aircraft.
* * * * *
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective August 19, 2009.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of August 19,
2009.
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Pong K. Lee, 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) 228-7324; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on February 23, 2009
(74 FR 8045). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:
During scheduled maintenance inspection, a bolt which connects
the PCU (power control unit) to the elevator surface was found
fractured in the assembly. Further inspection of the assembly
revealed that the bearing on the PCU rod end had seized, which
resulted in damage to the attachment fitting bushing and fracture of
the bolt. Inspection of other in-service airplanes revealed two more
seized PCU attachment joints. However, except seizure, no fractured
bolt was found on these airplanes. Failure of the bolts in both PCUs
on one side could result in disconnection of the elevator control
surface which would lead to flutter and loss of the aircraft.
This Airworthiness Directive (AD) is issued to mandate the
inspection and
[[Page 34226]]
lubrication of all part number (P/N) GT411-3800-5 and GT411-3800-7
PCU attachment joints.
The required actions include inspections for damage and seizure
(including signs of seizure) of the PCU attachment joints, an
inspection for damage (including wear damage, fretting, corrosion,
galling, scoring, fretting wear, and parts that do not meet inspection
requirements) of the PCU attachment joint components, and applicable
corrective actions. You may obtain further information by examining the
MCAI in the AD docket.
Explanation of Revised Service Information
Bombardier has issued the revised service information specified in
the below table. We have changed paragraphs (f)(1) through (f)(5),
paragraph (f)(7), and paragraphs (g)(1) and (g)(2) of this AD to add
the revised service information specified in the following table.
Revised Service Information
----------------------------------------------------------------------------------------------------------------
Revision
Service Bulletin level Date
----------------------------------------------------------------------------------------------------------------
Bombardier Alert Service Bulletin A700-1A11-27-024 02 November 10, 2008.
Bombardier Alert Service Bulletin A700-27-066..... 02 November 10, 2008.
Bombardier Service Bulletin 700-1A11-27-025....... 01 November 24, 2008.
Bombardier Service Bulletin 700-27-067............ 01 November 24, 2008.
----------------------------------------------------------------------------------------------------------------
No additional work is necessary for airplanes on which the
previously issued service information specified in the following table
has been accomplished. We have revised paragraph (f)(6) and added a new
paragraph (g)(3) to this AD to include credit for accomplishing the
actions before the effective date of this AD using the previously
issued service information.
Previously Issued Service Information
----------------------------------------------------------------------------------------------------------------
Revision
Service Bulletin level Date
----------------------------------------------------------------------------------------------------------------
Bombardier Alert Service Bulletin A700-1A11-27-024 01 October 3, 2008.
Bombardier Alert Service Bulletin A700-27-066..... 01 October 3, 2008.
Bombardier Service Bulletin 700-1A11-27-025....... (\1\) October 9, 2008.
Bombardier Service Bulletin 700-27-067............ (\1\) October 9, 2008.
----------------------------------------------------------------------------------------------------------------
\1\ Original.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
We reviewed the available data and determined that air safety and
the public interest require adopting the AD with the changes described
previously. We determined that these changes will not increase the
economic burden on any operator or increase the scope of the AD.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect about 157 products of U.S.
registry.
We estimate that it will take about 4 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $80 per work-hour. Based on these figures, we estimate the cost of
this AD to the U.S. operators to be $50,240, or $320 per product.
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 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 this AD:
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.
[[Page 34227]]
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
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 the NPRM, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (telephone (800) 647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
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 FAA 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 39-15753 (73 FR
72316, November 28, 2008) and adding the following new AD:
2009-15-03 Bombardier, Inc.: Amendment 39-15966. Docket No. FAA-
2009-0138; Directorate Identifier 2008-NM-216-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective August
19, 2009.
Affected ADs
(b) This AD supersedes AD 2008-24-12, Amendment 39-15753.
Applicability
(c) This AD applies to Bombardier Model BD-700-1A10 and BD-700-
1A11 airplanes, certificated in any category, serial numbers (S/Ns)
9002 through 9222 inclusive; equipped with elevator power control
units (PCUs) having part number (P/N) GT411-3800-5 or GT411-3800-7.
Subject
(d) Air Transport Association (ATA) of America Code 27: Flight
controls.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
During scheduled maintenance inspection, a bolt which connects
the PCU (power control unit) to the elevator surface was found
fractured in the assembly. Further inspection of the assembly
revealed that the bearing on the PCU rod end had seized, which
resulted in damage to the attachment fitting bushing and fracture of
the bolt. Inspection of other in-service airplanes revealed two more
seized PCU attachment joints. However, except seizure, no fractured
bolt was found on these airplanes. Failure of the bolts in both PCUs
on one side could result in disconnection of the elevator control
surface which would lead to flutter and loss of the aircraft.
This Airworthiness Directive (AD) is issued to mandate the
inspection and lubrication of all part number (P/N) GT411-3800-5 and
GT411-3800-7 PCU attachment joints.
The required actions include inspections for damage and seizure
(including signs of seizure) of the PCU attachment joints, an
inspection for damage (including wear damage, fretting, corrosion,
galling, scoring, fretting wear, and parts that do not meet
inspection requirements) of the PCU attachment joint components, and
applicable corrective actions.
Restatement of Requirements of AD 2008-24-12:
(f) Unless already done: For airplanes on which elevator PCUs
with P/N GT411-3800-5 or P/N GT411-3800-7, S/N 0615 and lower, are
installed, excluding P/N GT411-3800-7 PCUs having a serial number
listed in Table 1 of this AD, and excluding P/N GT411-3800-7 PCUs on
which less than 1,000 flight hours have accumulated on the PCUs as
of December 15, 2008 (the effective date of AD 2008-24-12), do the
actions specified in paragraphs (f)(1), (f)(2), and (f)(3) of this
AD.
Note 1: Units listed in Table 1 of this AD have been lubricated
by the vendor and the inspections required by paragraphs (f)(1),
(f)(2), (f)(3), and (f)(4) of this AD are not required for those
units.
Table 1--Serial Numbers
------------------------------------------------------------------------
------------------------------------------------------------------------
0030 0199
0031 0202
0033 0205
0041 0206
0046 0208
0060 0210
0062 0214
0066 0218
0081 0222
0083 0223
0087 0240
0092 0262
0097 0265
0101 0281
0105 0296
0108 0301
0109 0310
0111 0323
0110 0365
0119 0369
0130 0406
0138 0407
0141 0408
0145 0413
0156 0420
0161 0427
0163 0429
0164 0430
0165 0431
0171 0433
0173 0435
0174 0438
0178 0453
0179 0491
0181 0495
0183 0504
0188 0506
0190 0513
0191 0533
0197 0536
0198 0586
------------------------------------------------------------------------
(1) Within 10 flight cycles or 50 flight hours after December
15, 2008, whichever occurs first: Inspect for damage and wear and
lubricate the PCU attachment joints in accordance with Bombardier
Alert Service Bulletin A700-1A11-27-024, Revision 02, dated November
10, 2008; or Bombardier Alert Service Bulletin A700-27-066, Revision
02, dated November 10, 2008; as applicable.
(2) Within 90 days or 200 flight hours after performing the
actions required by paragraph (f)(1) of this AD, whichever occurs
first: Repeat the inspection and lubrication of the PCU attachment
joints in accordance with Bombardier Alert Service Bulletin A700-
1A11-27-024, Revision 02, dated November 10, 2008; or Bombardier
Alert Service Bulletin A700-27-066, Revision 02, dated November 10,
2008; as applicable.
(3) Within 45 days or 100 flight hours after performing the
actions required by paragraph (f)(2) of this AD, whichever occurs
first: Repeat the inspection and lubrication of the PCU attachment
joints in accordance with Bombardier Alert Service Bulletin A700-
1A11-27-024, Revision 02, dated November 10, 2008; or Bombardier
Alert Service Bulletin A700-27-066, Revision 02, dated November 10,
2008; as applicable. Repeat the inspection thereafter at intervals
not to exceed 45 days or 100 flight hours, whichever occurs first,
until paragraph (f)(4) of this AD is accomplished.
(4) Completion of a disassembly with an inspection for damage,
applicable corrective actions, and lubrication of the PCU attachment
joint components in accordance with Bombardier Service Bulletin 700-
1A11-27-025, Revision 01, dated November 24, 2008; or Bombardier
Service Bulletin 700-27-067, Revision 01, dated November 24, 2008;
as applicable; constitutes terminating action for the inspections
required by paragraphs (f)(1), (f)(2), and (f)(3) of this AD.
(5) Unless already done, if any damage or seizure is found
during any inspection required by paragraphs (f)(1), (f)(2), (f)(3),
and (f)(4) of this AD, before further flight, replace the affected
part in accordance with Bombardier Service Bulletin 700-1A11-27-025,
Revision 01, dated November 24, 2008; or Bombardier Service Bulletin
700-27-067, Revision 01, dated November 24, 2008; as applicable.
[[Page 34228]]
(6) Actions done before December 15, 2008, in accordance with
Bombardier Alert Service Bulletin A700-1A11-27-024 or Bombardier
Alert Service Bulletin A700-27-066, both dated October 2, 2008; or
Revision 01, both dated October 3, 2008; as applicable; are
acceptable for compliance with the corresponding requirements of
this AD.
(7) Unless already done, submit a report to Bombardier of all
findings found during any inspection required by paragraphs (f)(1),
(f)(2), (f)(3), and (f)(4) of this AD, in accordance with the
applicable service bulletin listed in Table 2 of this AD.
(i) If the inspection was done on or after December 15, 2008:
Submit the report within 14 days after the inspection.
(ii) If the inspection was done before December 15, 2008: Submit
the report within 14 days after December 15, 2008.
Table 2--Service Bulletins for Reports
----------------------------------------------------------------------------------------------------------------
Revision
Service Bulletin level Date
----------------------------------------------------------------------------------------------------------------
Bombardier Alert Service Bulletin A700-1A11-27-024 02 November 10, 2008.
Bombardier Alert Service Bulletin A700-27-066..... 02 November 10, 2008.
Bombardier Service Bulletin 700-1A11-27-025....... 01 November 24, 2008.
Bombardier Service Bulletin 700-27-067............ 01 November 24, 2008.
----------------------------------------------------------------------------------------------------------------
New Requirements of This AD: Actions and Compliance
(g) Unless already done, do the actions specified in paragraph
(g)(1) or (g)(2) of this AD, as applicable, at the time specified.
(1) For airplanes identified in paragraph (f) of this AD: Within
45 days or 100 flight hours after the effective date of this AD,
whichever occurs first, complete a disassembly with an inspection
for damage, applicable corrective actions, and lubrication of the
PCU attachment joint components in accordance with Bombardier
Service Bulletin 700-1A11-27-025, Revision 01, dated November 24,
2008; or Bombardier Service Bulletin 700-27-067, Revision 01, dated
November 24, 2008; as applicable.
(2) For airplanes not identified in paragraph (f) of this AD on
which elevator PCUs with P/N GT411-3800-7 are installed: Within 180
days or 400 flight hours after the effective date of this AD,
whichever occurs first, complete a disassembly with an inspection
for damage, applicable corrective actions, and lubrication of the
PCU attachment joint components in accordance with Bombardier
Service Bulletin 700-1A11-27-025, Revision 01, dated November 24,
2008; or Bombardier Service Bulletin 700-27-067, Revision 01, dated
November 24, 2008; as applicable.
(3) Actions done before the effective date of this AD in
accordance with Bombardier Service Bulletin 700-1A11-27-025, dated
October 9, 2008; or Bombardier Service Bulletin 700-27-067, dated
October 9, 2008; as applicable; are acceptable for compliance with
the corresponding requirements of this AD.
FAA AD Differences
Note 2: This AD differs from the MCAI and/or service information
as follows: Paragraph A.3. of the MCAI requires a one-time
inspection; however, since we have changed the compliance time for
the terminating action in paragraph A.4. of the MCAI (refer to
paragraph (g)(1) of this AD), paragraph (f)(3) of this AD requires
repeating the inspections until the terminating action is performed.
Other FAA AD Provisions
(h) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York Aircraft Certification Office (ACO), 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: Pong K. Lee, Aerospace
Engineer, Airframe and Propulsion Branch, ANE-171, FAA, New York
ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590;
telephone (516) 228-7324; fax (516) 794-5531. 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.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.
(4) Special Flight Permits: As described in Section 21.197 and
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199), special flight permits are not allowed.
Related Information
(i) Refer to MCAI Canadian Emergency Airworthiness Directive CF-
2008-31, dated October 9, 2008, and the service information
specified in Table 2 of this AD, for related information.
Material Incorporated by Reference
(j) You must use the service information contained in Table 3 of
this AD to do the actions required by this AD, as applicable, unless
the AD specifies otherwise.
Table 3--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Revision
Document level Date
----------------------------------------------------------------------------------------------------------------
Bombardier Alert Service Bulletin A700-1A11-27-024 02 November 10, 2008.
Bombardier Alert Service Bulletin A700-27-066..... 02 November 10, 2008.
Bombardier Service Bulletin 700-1A11-27-025....... 01 November 24, 2008.
Bombardier Service Bulletin 700-27-067............ 01 November 24, 2008.
----------------------------------------------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of the service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
Bombardier, Inc., 400 C[ocirc]te-Vertu Road West, Dorval,
Qu[eacute]bec H4S 1Y9, Canada; telephone 514-855-5000; fax 514-855-
7401; e-mail thd.crj@aero.bombardier.com; Internet https://www.bombardier.com.
(3) You may review copies of the 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.
(4) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For
[[Page 34229]]
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.
Issued in Renton, Washington, on July 2, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-16467 Filed 7-14-09; 8:45 am]
BILLING CODE 4910-13-P
