Airworthiness Directives; Bombardier Model BD-700-1A10 and BD-700-1A11 Airplanes, 72316-72320 [E8-28103]
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Federal Register / Vol. 73, No. 230 / Friday, November 28, 2008 / Rules and Regulations
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
DEPARTMENT OF TRANSPORTATION
The effective date of AD 2008–
20–05 remains October 27, 2008.
Related Information
(h) Refer to MCAI European Aviation
Safety Agency AD No.: 2007–0027, dated
February 5, 2007, for related information.
repetitively inspecting the tailboom
attachment fittings, installing inspection
holes and attachment bolt washers,
modifying both access covers, and
replacing broken attachment bolts. This
document corrects the AD number that
is incorrectly listed as 2008–20–08 on
page 60104 of the AD.
RIN 2120–AA64
DATES:
Material Incorporated by Reference
(i) You must use Vulcanair S.p.A. Service
Bulletin No. 120 Rev. 1, dated June 7, 2006,
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 Vulcanair S.p.A, Via G.
Pascoli, 7, Casoria (Naples), 80026 Italy;
telephone: +39 081 5918111; fax: +39 081
5918172; e-mail: info@vulcanair.com;
Internet: https://www.vulcanair.com.
(3) You may review copies at the FAA,
Central Region, Office of the Regional
Counsel, 901 Locust, Room 506, Kansas City,
Missouri 64106; or at the National Archives
and Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
Issued in Kansas City, Missouri, on
November 19, 2008.
John R. Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E8–27916 Filed 11–26–08; 8:45 am]
BILLING CODE 4910–13–P
Eric
Schrieber, Aviation Safety Engineer,
FAA, Los Angeles Aircraft Certification
Office, Airframe Branch, 3960
Paramount Blvd., Lakewood, California
90712, telephone (562) 627–5348, fax
(562) 627–5210.
FOR FURTHER INFORMATION CONTACT:
SUPPLEMENTARY INFORMATION:
Discussion: On September 25, 2008,
we issued AD 2008–20–05 to amend 14
CFR part 39 to include an AD that
applies to MDHI Model 600N
helicopters. That AD requires modifying
the fuselage aft section, repetitively
inspecting the tailboom attachment
fittings, installing inspection holes and
attachment bolt washers, modifying
both access covers, and replacing
broken attachment bolts.
As published, AD 2008–20–05
contains an incorrect AD number (2008–
20–08) in the regulatory text on page
60104 of the AD. The correct AD
number is 2008–20–05.
No other part of the regulatory
information has been changed;
therefore, the AD is not republished in
the Federal Register.
Correction of Publication
DEPARTMENT OF TRANSPORTATION
[Docket No. FAA–2008–0835; Directorate
Identifier 2008–SW–34–AD; Amendment 39–
15684; AD 2008–20–05]
Accordingly, the publication on
October 10, 2008 of Amendment 39–
15684, AD 2008–20–05, Docket No.
FAA–2008–0835, Directorate Identifier
2008–SW–34–AD (73 FR 60102), which
is the subject of FR Doc. E8–23540, is
corrected as follows:
RIN 2120–AA64
§ 39.13
Airworthiness Directives; MD
Helicopters, Inc. Model 600N
Helicopters
On page 60104, in the second column,
in the paragraph under § 39.13
[Amended], change ‘‘2008–20–08’’ to
read ‘‘2008–20–05’’.
Federal Aviation Administration
14 CFR Part 39
Federal Aviation
Administration, DOT.
ACTION: Final rule; correction.
dwashington3 on PROD1PC60 with RULES
AGENCY:
SUMMARY: This document corrects
airworthiness directive (AD) 2008–20–
05 which was published on October 10,
2008 (73 FR 60102) and applies to MD
Helicopters, Inc. (MDHI) Model 600N
helicopters. AD 2008–20–05 requires
modifying the fuselage aft section,
VerDate Aug<31>2005
14:57 Nov 26, 2008
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[Corrected]
Issued in Fort Worth, Texas, on November
14, 2008.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. E8–28108 Filed 11–26–08; 8:45 am]
BILLING CODE 4910–13–P
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Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–1238; Directorate
Identifier 2008–NM–181–AD; Amendment
39–15753; AD 2008–24–12]
Airworthiness Directives; Bombardier
Model BD–700–1A10 and BD–700–
1A11 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: We are adopting a new
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.
*
*
*
*
*
This AD requires actions that are
intended to address the unsafe
condition described in the MCAI.
DATES: This AD becomes effective
December 15, 2008.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of December 15, 2008.
We must receive comments on this
AD by December 29, 2008.
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.
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• 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.
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 AD, 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.
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
Transport Canada Civil Aviation
(TCCA), which is the airworthiness
authority for Canada, has issued
Canadian Emergency Airworthiness
Directive CF–2008–31, dated October 9,
2008 (referred to after this as ‘‘the
MCAI’’), 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
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.
Relevant Service Information
Bombardier has issued the service
information in the following table. The
actions described in the service
information are intended to correct the
unsafe condition identified in the
MCAI.
SERVICE BULLETINS
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 ...............................................................
FAA’s Determination and Requirements
of This 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 issuing this
AD because we evaluated all pertinent
information and determined the unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
dwashington3 on PROD1PC60 with RULES
Revision level
Differences Between the 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.
VerDate Aug<31>2005
14:57 Nov 26, 2008
Jkt 217001
01 ...........................................................
01 ...........................................................
Original ...................................................
Original ...................................................
We might also have required different
actions in this AD from those in the
MCAI in order to follow FAA policies.
Any such differences are highlighted in
a NOTE within the AD.
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
rule because failure of the bolts in both
PCUs on one side of the airplane could
cause disconnection of the elevator
control surface which could result in
flutter and consequent loss of the
airplane. Therefore, we determined that
notice and opportunity for public
comment before issuing this AD are
impracticable and that good cause exists
for making this amendment effective in
fewer than 30 days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and
opportunity for public comment. We
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Date
October
October
October
October
3,
3,
9,
9,
2008.
2008.
2008.
2008.
invite you to send any written relevant
data, views, or arguments about this AD.
Send your comments to an address
listed under the ADDRESSES section.
Include ‘‘Docket No. FAA–2008–1238;
Directorate Identifier 2008–NM–181–
AD’’ at the beginning of your comments.
We specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this 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 AD.
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
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Federal Register / Vol. 73, No. 230 / Friday, November 28, 2008 / Rules and Regulations
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.
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
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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
2008–24–12 Bombardier: Amendment 39–
15753. Docket No. FAA–2008–1238;
Directorate Identifier 2008–NM–181–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective December 15, 2008.
Affected ADs
(b) None.
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.
Actions and Compliance
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 continued airworthiness
information (MCAI) states:
(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 the effective date of this AD, 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
dwashington3 on PROD1PC60 with RULES
0030
0031
0033
0041
0046
0060
0062
0066
0081
0083
0087
0092
0097
0101
0105
0108
0109
0110
0111
0119
0130
0138
0141
0145
0156
0161
0163
0164
0165
0171
0173
0174
0178
0179
0181
0183
(1) Within 10 flight cycles or 50 flight
hours after the effective date of this AD,
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 01, dated October 3, 2008; or
Bombardier Alert Service Bulletin A700–27–
VerDate Aug<31>2005
14:57 Nov 26, 2008
Jkt 217001
0188
0190
0191
0197
0198
0199
0202
0205
0206
0208
0210
0214
0218
0222
0223
0240
0262
0265
0281
0296
0301
0310
0323
0365
066, Revision 01, dated October 3, 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–
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0369
0406
0407
0408
0413
0420
0427
0429
0430
0431
0433
0435
0438
0453
0491
0495
0504
0506
0513
0533
0536
0586
1A11–27–024, Revision 01, dated October 3,
2008; or Bombardier Alert Service Bulletin
A700–27–066, Revision 01, dated October 3,
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
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PCU attachment joints in accordance with
Bombardier Alert Service Bulletin A700–
1A11–27–024, Revision 01, dated October 3,
2008; or Bombardier Alert Service Bulletin
A700–27–066, Revision 01, dated October 3,
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, dated October 9, 2008; or
Bombardier Service Bulletin 700–27–067,
dated October 9, 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, dated October 9, 2008, or Bombardier
Service Bulletin 700–27–067, dated October
9, 2008, as applicable.
(6) Actions done before the effective date
of this AD in accordance with the
Bombardier Alert Service Bulletins A700–
1A11–27–024 and A700–27–066, both dated
October 2, 2008, 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 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
the effective date of this AD: Submit the
report within 14 days after the inspection.
(ii) If the inspection was done before the
effective date of this AD: Submit the report
within 14 days after the effective date of this
AD.
TABLE 2—SERVICE BULLETINS FOR REPORTS
Service Bulletin
Bombardier
Bombardier
Bombardier
Bombardier
Revision level
Alert Service Bulletin; A700–1A11–27–024 ........................................
Alert Service Bulletin; A700–27–066 ...................................................
Service Bulletin; 700–1A11–27–025 ...................................................
Service Bulletin; 700–27–067 ..............................................................
FAA AD Differences
Note 2: This AD differs from the MCAI
and/or service information as follows:
(1) This AD does not mandate the
terminating action specified in paragraph
A.4. of the MCAI; it is included as an
optional terminating action in paragraph
(f)(4) of this AD. The planned compliance
times for that action would allow enough
time to provide notice and opportunity for
prior public comment on the merits of those
actions. Therefore, we are considering further
rulemaking to require the terminating action
on all affected airplanes.
(2) Paragraph A.3. of the MCAI requires a
one-time inspection; however, since we have
changed the terminating action in paragraph
A.4. of the MCAI to an optional action,
paragraph (f)(3) of this AD requires repeating
the inspections until the terminating action
is performed.
(3) This AD does not require the inspection
and lubrication of PCUs specified in
Paragraph B. of the MCAI. The planned
compliance times for those actions would
allow enough time to provide notice and
opportunity for prior public comment on the
merits of those actions. Therefore, we are
considering further rulemaking to address
this issue.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York Aircraft
01 ...........................................................
01 ...........................................................
Original ...................................................
Original ...................................................
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
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(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.
Date
October
October
October
October
3,
3,
9,
9,
2008.
2008.
2008.
2008.
Related Information
(h) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Transport
Canada Civil Aviation 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
(i) You must use the service information
specified 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
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec 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 at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
(202) 741–6030, or go to: https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
TABLE 3—MATERIAL INCORPORATED BY REFERENCE
dwashington3 on PROD1PC60 with RULES
Service Bulletin
Bombardier
Bombardier
Bombardier
Bombardier
Revision level
Alert Service Bulletin A700–1A11–27–024 .........................................
Alert Service Bulletin A700–27–066 ....................................................
Service Bulletin 700–1A11–27–025 ....................................................
Service Bulletin 700–27–067 ...............................................................
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01 ...........................................................
01 ...........................................................
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Original ...................................................
E:\FR\FM\28NOR1.SGM
28NOR1
Date
October
October
October
October
3,
3,
9,
9,
2008.
2008.
2008.
2008.
72320
Federal Register / Vol. 73, No. 230 / Friday, November 28, 2008 / Rules and Regulations
Issued in Renton, Washington, on
November 16, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E8–28103 Filed 11–26–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
by reference of Boeing Service Bulletin
737–25–1404, dated May 25, 2000 on
August 28, 2001 (66 FR 38361, July 24,
2001).
For service information
identified in this AD, contact Boeing
Commercial Airplanes, P.O. Box 3707,
Seattle, Washington 98124–2207;
telephone (206) 544–9990; fax (206)
766–5682; e-mail DDCS@boeing.com;
Internet https://
www.myboeingfleet.com.
ADDRESSES:
14 CFR Part 39
Examining the AD Docket
[Docket No. FAA–2008–0176; Directorate
Identifier 2007–NM–228–AD; Amendment
39–15748; AD 2008–24–08]
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 AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is the Document Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue, SE.,
Washington, DC 20590.
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–600, –700, –700C, –800 and
–900 Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for certain
Boeing Model 737–600, –700, –700C,
–800 and –900 series airplanes. This AD
requires an inspection of the escape
slides for the forward and aft entry and
service doors to determine the part
number and service bulletin number
stenciled on the escape slide girt, and
modification of the escape slide
assemblies. This AD also requires
concurrent modification of the escape
slide latch assemblies; concurrent
inspection of the escape slides to
determine the part number and service
bulletin number stenciled on the escape
slide girts, and replacement of the
trigger housing on the regulator valve
with an improved trigger housing if
necessary; and concurrent replacement
of the rod in the pilot valve regulator
with a new, improved rod; as
applicable. This AD results from reports
that certain escape slides did not
automatically inflate when deployed or
after the manual inflation cable was
pulled. We are issuing this AD to
prevent failure of an escape slide to
inflate when deployed, which could
result in the slide being unusable during
an emergency evacuation and
consequent injury to passengers or
crewmembers.
This AD is effective January 2,
2009.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of January 2, 2009.
The Director of the Federal Register
previously approved the incorporation
dwashington3 on PROD1PC60 with RULES
DATES:
VerDate Aug<31>2005
14:57 Nov 26, 2008
Jkt 217001
FOR FURTHER INFORMATION CONTACT:
Robert K. Hettman, Aerospace Engineer,
Cabin Safety and Environmental
Systems Branch, ANM–150S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6457, fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an airworthiness
directive (AD) that would apply to
certain Boeing Model 737–600, –700,
–700C, –800 and –900 series airplanes.
That NPRM was published in the
Federal Register on February 15, 2008
(73 FR 8833). That NPRM proposed to
require an inspection of the escape
slides for the forward and aft entry and
service doors to determine the part
number and service bulletin number
stenciled on the escape slide girt, and
modification of the escape slide
assemblies. That NPRM also proposed
to require concurrent modification of
the escape slide latch assemblies;
concurrent inspection of the escape
slides to determine the part number and
service bulletin number stenciled on the
escape slide girts, and replacement of
the trigger housing on the regulator
valve with an improved trigger housing
if necessary; and concurrent
replacement of the rod in the pilot valve
PO 00000
Frm 00018
Fmt 4700
Sfmt 4700
regulator with a new, improved rod; as
applicable.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comments received from
the three commenters.
Support for the NPRM
Boeing concurs with the contents of
the proposed rule.
Requests To Refer to Additional
Goodrich Service Bulletin
Goodrich, and Air Transport
Association (ATA) on behalf of one of
its members, American Airlines (AA),
request that Boeing revise Boeing
Service Bulletin 737–25–1491, dated
April 23, 2007 (cited in the NPRM as the
appropriate source of service
information for accomplishing certain
actions specified in the NPRM), to
include a reference to Goodrich Service
Bulletin 5A3307–25–339, Revision 2,
dated March 31, 2004, as an alternative
method of compliance (AMOC) to
BFGoodrich Service Bulletin 25–308,
dated January 21, 2000 (cited in the
NPRM as a source of service information
for accomplishing certain other actions
specified in the NPRM). ATA and AA
note that this service bulletin modifies
the applicable slide to the latest
standard offered by Goodrich. AA and
Goodrich suggest that if Boeing Service
Bulletin 737–25–1491, dated April 23,
2007, is not revised, the AD should state
that it does not apply to Goodrich part
number (P/N) 5A3307–5 slides and that
Goodrich Service Bulletin 5A3307–25–
339, Revision 2, dated March 31, 2004,
be identified as an AMOC for the slide
portion of the AD.
We disagree with the request to revise
the AD to refer to Goodrich Service
Bulletin 5A3307–25–339, Revision 2,
dated March 31, 2004. There are
significant differences in the actions
between BFGoodrich Service Bulletin
25–308, dated January 21, 2000 and
Goodrich Service Bulletin 5A3307–25–
339, Revision 2, dated March 31, 2004.
Therefore, any request to use the
procedures in Goodrich Service Bulletin
5A3307–25–339 is best handled through
the AMOC process. Under the
provisions of paragraph (k) of the AD,
we will consider requests for approval
of an AMOC if sufficient data are
submitted to substantiate that the
change would provide an acceptable
level of safety. We have not changed the
AD in this regard.
Request To Revise Unsafe Condition
Goodrich notes that paragraph (g)(1)
of the NPRM addresses an unsafe
E:\FR\FM\28NOR1.SGM
28NOR1
]]>Agencies
[Federal Register Volume 73, Number 230 (Friday, November 28, 2008)]
[Rules and Regulations]
[Pages 72316-72320]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-28103]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-1238; Directorate Identifier 2008-NM-181-AD;
Amendment 39-15753; AD 2008-24-12]
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; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new 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.
* * * * *
This AD requires actions that are intended to address the unsafe
condition described in the MCAI.
DATES: This AD becomes effective December 15, 2008.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of December 15,
2008.
We must receive comments on this AD by December 29, 2008.
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.
[[Page 72317]]
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.
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 AD, 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.
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
Transport Canada Civil Aviation (TCCA), which is the airworthiness
authority for Canada, has issued Canadian Emergency Airworthiness
Directive CF-2008-31, dated October 9, 2008 (referred to after this as
``the MCAI''), 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 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.
Relevant Service Information
Bombardier has issued the service information in the following
table. The actions described in the service information are intended to
correct the unsafe condition identified in the MCAI.
Service Bulletins
------------------------------------------------------------------------
Service Bulletin Revision level Date
------------------------------------------------------------------------
Bombardier Alert Service 01.............. October 3, 2008.
Bulletin A700-1A11-27-024.
Bombardier Alert Service 01.............. October 3, 2008.
Bulletin A700-27-066.
Bombardier Service Bulletin Original........ October 9, 2008.
700-1A11-27-025.
Bombardier Service Bulletin Original........ October 9, 2008.
700-27-067.
------------------------------------------------------------------------
FAA's Determination and Requirements of This 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 issuing this AD because we
evaluated all pertinent information and determined the unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between the 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 FAA policies. Any such differences are
highlighted in a NOTE within the AD.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because
failure of the bolts in both PCUs on one side of the airplane could
cause disconnection of the elevator control surface which could result
in flutter and consequent loss of the airplane. Therefore, we
determined that notice and opportunity for public comment before
issuing this AD are impracticable and that good cause exists for making
this amendment effective in fewer than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and opportunity for public
comment. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2008-1238; Directorate
Identifier 2008-NM-181-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this 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 AD.
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
[[Page 72318]]
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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
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 adding the following new AD:
2008-24-12 Bombardier: Amendment 39-15753. Docket No. FAA-2008-1238;
Directorate Identifier 2008-NM-181-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective December
15, 2008.
Affected ADs
(b) None.
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 continued 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.
Actions and Compliance
(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 the effective date of this AD, 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 0097 0156 0188 0218 0369 0438
0031 0101 0161 0190 0222 0406 0453
0033 0105 0163 0191 0223 0407 0491
0041 0108 0164 0197 0240 0408 0495
0046 0109 0165 0198 0262 0413 0504
0060 0110 0171 0199 0265 0420 0506
0062 0111 0173 0202 0281 0427 0513
0066 0119 0174 0205 0296 0429 0533
0081 0130 0178 0206 0301 0430 0536
0083 0138 0179 0208 0310 0431 0586
0087 0141 0181 0210 0323 0433
0092 0145 0183 0214 0365 0435
------------------------------------------------------------------------
(1) Within 10 flight cycles or 50 flight hours after the
effective date of this AD, 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 01, dated October 3, 2008; or Bombardier Alert Service
Bulletin A700-27-066, Revision 01, dated October 3, 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 01, dated October 3, 2008; or Bombardier Alert
Service Bulletin A700-27-066, Revision 01, dated October 3, 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
[[Page 72319]]
PCU attachment joints in accordance with Bombardier Alert Service
Bulletin A700-1A11-27-024, Revision 01, dated October 3, 2008; or
Bombardier Alert Service Bulletin A700-27-066, Revision 01, dated
October 3, 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, dated October 9, 2008; or Bombardier Service Bulletin
700-27-067, dated October 9, 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,
dated October 9, 2008, or Bombardier Service Bulletin 700-27-067,
dated October 9, 2008, as applicable.
(6) Actions done before the effective date of this AD in
accordance with the Bombardier Alert Service Bulletins A700-1A11-27-
024 and A700-27-066, both dated October 2, 2008, 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 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 the effective date of
this AD: Submit the report within 14 days after the inspection.
(ii) If the inspection was done before the effective date of
this AD: Submit the report within 14 days after the effective date
of this AD.
Table 2--Service Bulletins for Reports
------------------------------------------------------------------------
Service Bulletin Revision level Date
------------------------------------------------------------------------
Bombardier Alert Service 01.............. October 3, 2008.
Bulletin; A700-1A11-27-024.
Bombardier Alert Service 01.............. October 3, 2008.
Bulletin; A700-27-066.
Bombardier Service Bulletin; Original........ October 9, 2008.
700-1A11-27-025.
Bombardier Service Bulletin; Original........ October 9, 2008.
700-27-067.
------------------------------------------------------------------------
FAA AD Differences
Note 2: This AD differs from the MCAI and/or service information
as follows:
(1) This AD does not mandate the terminating action specified in
paragraph A.4. of the MCAI; it is included as an optional
terminating action in paragraph (f)(4) of this AD. The planned
compliance times for that action would allow enough time to provide
notice and opportunity for prior public comment on the merits of
those actions. Therefore, we are considering further rulemaking to
require the terminating action on all affected airplanes.
(2) Paragraph A.3. of the MCAI requires a one-time inspection;
however, since we have changed the terminating action in paragraph
A.4. of the MCAI to an optional action, paragraph (f)(3) of this AD
requires repeating the inspections until the terminating action is
performed.
(3) This AD does not require the inspection and lubrication of
PCUs specified in Paragraph B. of the MCAI. The planned compliance
times for those actions would allow enough time to provide notice
and opportunity for prior public comment on the merits of those
actions. Therefore, we are considering further rulemaking to address
this issue.
Other FAA AD Provisions
(g) 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
appropriate principal inspector (PI) in the FAA Flight Standards
District Office (FSDO), or lacking a PI, your local FSDO.
(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
(h) Refer to Mandatory Continuing Airworthiness Information
(MCAI) Transport Canada Civil Aviation 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
(i) You must use the service information specified 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
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 at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the
National Archives and Records Administration (NARA). For information
on the availability of this material at NARA, call (202) 741-6030,
or go to: https://www.archives.gov/federal_register/code_of_
federal_regulations/ibr_locations.html.
Table 3--Material Incorporated by Reference
------------------------------------------------------------------------
Service Bulletin Revision level Date
------------------------------------------------------------------------
Bombardier Alert Service 01.............. October 3, 2008.
Bulletin A700-1A11-27-024.
Bombardier Alert Service 01.............. October 3, 2008.
Bulletin A700-27-066.
Bombardier Service Bulletin Original........ October 9, 2008.
700-1A11-27-025.
Bombardier Service Bulletin Original........ October 9, 2008.
700-27-067.
------------------------------------------------------------------------
[[Page 72320]]
Issued in Renton, Washington, on November 16, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E8-28103 Filed 11-26-08; 8:45 am]
BILLING CODE 4910-13-P
