Airworthiness Directives; Bombardier, Inc. Model DHC-8-100 and DHC-8-200 Series Airplanes, and Model DHC-8-301, -311, and -315 Airplanes, 9756-9760 [2010-3226]
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Federal Register / Vol. 75, No. 42 / Thursday, March 4, 2010 / Rules and Regulations
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0712; Directorate
Identifier 2007–NM–152–AD; Amendment
39–16205; AD 2010–04–12]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Model DHC–8–100 and DHC–8–200
Series Airplanes, and Model DHC–8–
301, –311, and –315 Airplanes
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
SUMMARY: We are adopting a new
airworthiness directive (AD) for certain
Model DHC–8–100 and DHC–8–200
series airplanes, and DHC–8–301, –311,
and –315 airplanes. This AD requires
implementing a corrosion prevention
and control program (CPCP) either by
accomplishing specific tasks or by
revising the maintenance inspection
program to include a CPCP. This AD
results from the determination that, as
airplanes age, they are more likely to
exhibit indications of corrosion. We are
issuing this AD to prevent structural
failure of the airplane due to corrosion.
DATES: This AD is effective April 8,
2010.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of April 8, 2010.
ADDRESSES: For service information
identified in this AD, contact
ˆ
Bombardier, Inc., 400 Cote-Vertu Road
´
West, Dorval, Quebec H4S 1Y9, Canada;
telephone 514–855–5000; fax 514–855–
7401; e-mail
thd.qseries@aero.bombardier.com;
Internet https://www.bombardier.com.
srobinson on DSKHWCL6B1PROD with RULES
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this 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.
FOR FURTHER INFORMATION CONTACT:
Craig Yates, Aerospace Engineer,
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Airframe and Mechanical Systems
Branch, ANE–171, FAA, New York
Aircraft Certification Office, 1600
Stewart Avenue, Suite 410, Westbury,
New York 11590; telephone (516) 228–
7355; fax (516) 794–5531.
SUPPLEMENTARY INFORMATION:
with the changes described previously.
We also determined that these changes
will not increase the economic burden
on any operator or increase the scope of
the AD.
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 Bombardier Model DHC–8–100
and DHC–8–200 series airplanes, and
DHC–8–301, –311, and –315 airplanes.
That NPRM was published in the
Federal Register on August 13, 2009 (74
FR 40778). That NPRM proposed to
require implementing a corrosion
prevention and control program (CPCP)
either by accomplishing specific tasks or
by revising the maintenance inspection
program to include a CPCP.
Since issuance of the NPRM, we have
increased the labor rate used in the
Costs of Compliance from $80 per workhour to $85 per work-hour. The Costs of
Compliance information, below, reflects
this increase in the specified hourly
labor rate.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comment received from
the single commenter.
Explanation of Change to Costs of
Compliance
Costs of Compliance
This AD affects about 154 airplanes of
U.S. registry. There are between 16 and
17 specific inspections, depending on
the applicable manual identified in
Table 1 of this AD. The inspections take
about 53 work hours per airplane, per
inspection cycle, at an average labor rate
of $85 per work hour. Based on these
figures, the estimated cost of this AD for
U.S. operators is $693,770, or $4,505 per
airplane, per inspection cycle.
Authority for This Rulemaking
Request for Clarification of Inspections
Mesa Airlines requests that we restate
that the inspections required by
paragraph (h) of this AD to specify to
inspect for Environmental Damage and/
or Corrosion Protection and Control
Program (ED/CPCP). The commenter
asserts that the NPRM would require
only tasks identified as both ED and
CPCP. Mesa Airlines notes that
accomplishing the ED/CPCP inspections
only does not encompass the Air
Transport Association (ATA) of America
Codes listed in the NPRM.
We agree. Canadian AD CF–2007–06,
dated April 10, 2007, describes doing
‘‘ED/CPCP’’ inspections. The required
actions include ‘‘ED’’ inspections and
inspections identified as both ‘‘ED’’ and
‘‘CPCP.’’ We have clarified this in
paragraph (h) of this AD. This has been
coordinated with TCCA. We have also
revised paragraphs (i) and (i)(2) of this
AD to clarify the inspections.
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.
Explanation of Change Made to This
AD
We have revised this AD to identify
the legal name of the manufacturer as
published in the most recent type
certificate data sheet for the affected
airplane models.
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
Conclusion
We reviewed the relevant data,
considered the comment received, and
determined that air safety and the
public interest require adopting the AD
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Regulatory Findings
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Federal Register / Vol. 75, No. 42 / Thursday, March 4, 2010 / Rules and Regulations
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979), and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
You can find our regulatory
evaluation and the estimated costs of
compliance in the AD Docket.
9757
PART 39—AIRWORTHINESS
DIRECTIVES
DHC–8–301, DHC–8–311, and DHC–8–315
airplanes, certificated in any category; serial
numbers 003 and subsequent.
1. The authority citation for part 39
continues to read as follows:
Subject
(d) Air Transport Association (ATA) of
America Codes 32: Landing Gear, 51:
Standard Practices/Structures; 52: Doors; 53:
Fuselage; 54: Nacelles/Pylons; 55: Stabilizers;
and 57: Wings.
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
■
Unsafe Condition
(e) This AD results from the determination
that, as airplanes age, they are more likely to
exhibit indications of corrosion. We are
issuing this AD to prevent structural failure
of the airplane due to corrosion.
List of Subjects in 14 CFR Part 39
2010–04–12 Bombardier, Inc.: Amendment
39–16205. Docket No. FAA–2009–0712;
Directorate Identifier 2007–NM–152–AD.
Air transportation, Aircraft, Aviation
safety, Incorporation by Reference,
Safety.
Effective Date
(a) This airworthiness directive (AD) is
effective April 8, 2010.
Adoption of the Amendment
Affected ADs
(b) None.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
Applicability
(c) This AD applies to Bombardier, Inc.
Model DHC–8–101, DHC–8–102, DHC–8–
103, DHC–8–106, DHC–8–201, DHC–8–202,
Compliance
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Manual References
(g) This AD refers to the manuals listed in
Table 1 of this AD.
■
TABLE 1—APPLICABLE MANUALS
Bombardier model
Manual
(1) DHC–8–101, –102, –103, and –106 airplanes.
Part 1, Section 3, Structural Inspection Program, of the Bombardier de Havilland Dash 8 Maintenance Program Maintenance Review Board Report Dash 8 Series 100 Program Support
Manual (PSM) 1–8–7, Revision 22, dated November 1, 2008.
Part 1, Section 3, Structural Inspection Program, of the Bombardier de Havilland Dash 8 Maintenance Program Maintenance Review Board Report Dash 8 Series 200 PSM 1–82–7, Revision 13, dated November 1, 2008.
Part 1, Section 3, Structural Inspection Program, of the Bombardier de Havilland Dash 8 Maintenance Program Maintenance Review Board Report Dash 8 Series 300, PSM 1–83–7, Revision 22, dated November 1, 2008.
(2) DHC–8–201 and DHC–8–202 airplanes .......
srobinson on DSKHWCL6B1PROD with RULES
(3) Model DHC–8–301, DHC–8–311, and DHC–
8–315 airplanes.
Inspections
(h) At the later of the times specified in
paragraphs (h)(1) and (h)(2) of this AD, do
each of the Environmental Damage/Corrosion
Protection and Control Program (ED/CPCP)
inspections identified with both ‘‘ED’’ and
‘‘CPCP,’’ or with only ‘‘ED,’’ including reprotection tasks, as applicable, which are
found in the ‘‘Type of Damage’’ column of the
applicable manual found in Table 1 of this
AD, in accordance with the applicable
manual identified in Table 1 of this AD.
Except as provided by paragraph (i) of this
AD, repeat each task thereafter at intervals
not to exceed the compliance time specified
in the ‘‘Repeat’’ column of the applicable
manual identified in Table 1 of this AD.
(1) Within 24 months after the effective
date of this AD.
(2) At the compliance time specified in the
‘‘Threshold’’ column of the applicable manual
identified in Table 1 of this AD since the date
of issuance of the original Canadian
airworthiness certificate or the date of
issuance of the original Canadian export
certificate of airworthiness. If there is no
value in the ‘‘Threshold’’ column, use the
time specified in the ‘‘Repeat’’ column.
(i) After accomplishment of each initial
ED/CPCP and ED task required by paragraph
(h) of this AD, the FAA may approve the
incorporation into the operator’s approved
maintenance/inspection program of the CPCP
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specified in the applicable manual identified
in Table 1 of this AD; or the equivalent
program that is approved in accordance with
this AD. In all cases, the initial corrosion task
for each airplane area must be completed by
the initial compliance time specified in
paragraph (h) of this AD.
(1) Any operator complying with paragraph
(i) of this AD may use an alternative
recordkeeping method to that otherwise
required by section 91.417 (‘‘Maintenance
records’’) or section 121.380 (‘‘Maintenance
recording requirements’’) of the Federal
Aviation Regulations (14 CFR 91.417 or 14
CFR 121.380, respectively) for the actions
required by this AD, provided that the
recordkeeping method is approved by the
FAA and is included in a revision to the
maintenance/inspection program. For the
purposes of this paragraph, ‘‘the FAA’’ is
defined as the cognizant Principal
Maintenance Inspector (PMI) for operators
that are assigned a PMI (i.e., part 121, 125,
and 135 operators), and the cognizant Flight
Standards District Office for other operators
(i.e., part 91 operators).
(2) After the initial accomplishment of the
ED/CPCP and ED tasks required by paragraph
(h) of this AD, any extension of the repetitive
intervals specified in the manual must be
approved by the Manager, New York Aircraft
Certification Office (ACO), FAA.
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Corrective Actions
(j) If any corrosion is found during
accomplishment of any action required by
paragraph (h) of this AD: Before further
flight, rework, repair, or replace, as
applicable, in accordance with a method
approved by either the Manager, New York
ACO, FAA; or Transport Canada Civil
Aviation (TCCA) (or its delegated agent).
Reporting Requirements for Level 3
Corrosion Findings
(k) If any Level 3 corrosion, as defined in
Part 1 of the Bombardier (de Havilland)
DHC–6 Twin Otter, Dash 7 & Dash 8
Corrosion Prevention and Control Manual,
PSM 1–GEN–5, Revision 3, dated November
30, 1998, is found during the
accomplishment of any action required by
this AD, do paragraphs (k)(1), (k)(2), and
(k)(3) of 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.
(1) Within 3 days after the finding of Level
3 corrosion, report findings to the Manager,
New York ACO, FAA, in accordance with the
Bombardier (de Havilland) DHC–6 Twin
Otter, Dash 7 & Dash 8 Corrosion Prevention
and Control Manual, PSM 1–GEN–5,
Revision 3, dated November 30, 1998.
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Federal Register / Vol. 75, No. 42 / Thursday, March 4, 2010 / Rules and Regulations
(2) Within 10 days after the finding of
Level 3 corrosion, either submit a plan to the
FAA to identify a schedule for accomplishing
the applicable CPCP task on the remainder of
the airplanes in the operator’s fleet that are
subject to this AD, or provide data
substantiating that the Level 3 corrosion that
was found is an isolated case. The FAA may
impose a schedule other than that proposed
in the plan upon finding that a change to the
schedule is needed to ensure that any other
Level 3 corrosion is detected in a timely
manner. For the purposes of this paragraph,
‘‘the FAA’’ is defined as the cognizant
Principal Maintenance Inspector (PMI) for
operators that are assigned a PMI (i.e., part
121, 125, and 135 operators), and the
cognizant Flight Standards District Office for
other operators (i.e., part 91 operators).
(3) Within the time schedule approved in
accordance with paragraph (k)(2) of this AD,
accomplish the applicable task on the
remainder of the airplanes in the operator’s
fleet that are subject to this AD.
Limiting Future Corrosion Findings
(l) If corrosion findings that exceed Level
1 are found in any area during any repeat of
any CPCP task after the initial
accomplishment required by paragraph (h) of
this AD: Within 60 days after such finding,
implement a means approved by the FAA to
reduce future findings of corrosion in that
area to Level 1 or better. For the purposes of
this paragraph, ‘‘the FAA’’ is defined as the
cognizant PMI for operators that are assigned
a PMI (i.e., part 121, 125, and 135 operators),
and the cognizant Flight Standards District
Office for other operators (i.e., part 91
operators).
Standards District Office for other operators
(i.e., part 91 operators).
Scheduling Corrosion Tasks for Transferred
Airplanes
(m) Before any airplane subject to this AD
is transferred and placed into service by an
operator: Establish a schedule for
accomplishing the CPCP tasks required by
this AD in accordance with paragraph (m)(1)
or (m)(2) of this AD, as applicable.
(1) For airplanes on which the CPCP tasks
required by this AD have been accomplished
previously at the schedule established by this
AD: Perform the first CPCP task in each area
in accordance with the previous operator’s
schedule, or in accordance with the new
operator’s schedule, whichever results in an
earlier accomplishment of that CPCP task.
After the initial accomplishment of each
CPCP task in each area as required by this
paragraph, repeat each CPCP task in
accordance with the new operator’s schedule.
(2) For airplanes on which the CPCP tasks
required by this AD have not been
accomplished previously, or have not been
accomplished at the schedule established by
this AD: The new operator must perform
each initial CPCP task in each area before
further flight or in accordance with a
schedule approved by the FAA. For the
purposes of this paragraph, ‘‘the FAA’’ is
defined as the cognizant Principal
Maintenance Inspector (PMI) for operators
that are assigned a PMI (i.e., part 121, 125,
and 135 operators), and the cognizant Flight
Alternative Methods of Compliance
(AMOCs)
(n)(1) The Manager, New York ACO, ANE–
170, 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: Program Manager,
Continuing Operational Safety, FAA, New
York ACO, 1600 Stewart Avenue, Suite 410,
Westbury, New York 11590; telephone 516–
228–7300; fax 516–794–5531.
(2) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
Office. The AMOC approval letter must
specifically reference this AD.
Related Information
(o) Canadian airworthiness directive CF–
2007–06, dated April 10, 2007, also addresses
the subject of this AD.
Material Incorporated by Reference
(p) You must use the service information
contained in Table 2 of this AD, as
applicable, to do the actions required by this
AD, unless the AD specifies otherwise.
TABLE 2—MATERIAL INCORPORATED BY REFERENCE
Document
Revision
Part 1, Section 3, Structural Inspection Program, of the Bombardier de Havilland Dash 8 Maintenance Program Maintenance Review Board Report Dash 8 Series 100 Program Support Manual (PSM) 1–8–7.
Part 1, Section 3, Structural Inspection Program, of the Bombardier de Havilland Dash 8 Maintenance Program Maintenance Review Board Report Series 200 PSM 1–82–7.
Part 1, Section 3, Structural Inspection Program, of the Bombardier de Havilland Dash 8 Maintenance Program Maintenance Review Board Report Dash 8 Series 300, PSM 1–83–7.
Bombardier (de Havilland) DHC–6 Twin Otter, Dash 7 & Dash 8 Corrosion Prevention and Control Manual,
PSM 1-GEN–5, Part 1.
Bombardier de Havilland Dash 8
Maintenance Program Maintenance Review
Board Report Dash 8 Series 100 PSM 1–8–7,
Date
22
November 1, 2008.
13
November 1, 2008.
22
November 1, 2008.
3
November 30, 1998.
Revision 22, dated November 1, 2008,
contains the following effective pages:
LIST OF EFFECTIVE PAGES
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description
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Federal Register / Vol. 75, No. 42 / Thursday, March 4, 2010 / Rules and Regulations
Bombardier de Havilland Dash 8
Maintenance Program Maintenance Review
Board Report Dash 8 Series 200 PSM 1–82–
7, Revision 13, dated November 1, 2008,
contains the following effective pages:
LIST OF EFFECTIVE PAGES
Page title/
description
Page number(s)
Revision number
Title Page ..............................................................................
List of Effective Pages ..........................................................
Log of Revisions ...................................................................
Record of Revisions ..............................................................
Contents ................................................................................
Section 3:
Subject 3–0 ....................................................................
Subject 3–32 ..................................................................
Subject 3–52 ..................................................................
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Bombardier de Havilland Dash 8
Maintenance Program Maintenance Review
Board Report Dash 8 Series 300 PSM 1–83–
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Contents ................................................................................
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(*Only the title page and Record of Revisions of these documents specify the revision level of these documents.)
Bombardier (de Havilland) DHC–6 Twin
Otter, Dash 7 & Dash 8 Corrosion Prevention
and Control Manual PSM 1–GEN–5, Part 1,
Revision 3, dated November 30, 1998,
contains the following effective pages:
LIST OF EFFECTIVE PAGES
Page number(s)
Revision number
Date shown
on page(s)
Title Page .............................................................................
Record of Revisions .............................................................
...............................................................................................
Part 1 List of Effective Pages ...............................................
Part 1 Table of Contents ......................................................
Part 1 List of Illustrations ......................................................
Part 1 List of Tables .............................................................
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3–1 through 3–4 ...................
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6–1 through 6–8, ..................
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November 8, 1993.
August 27, 1991.
August 27, 1991.
November 30, 1998.
November 8, 1993.
November 8, 1993.
November 8, 1993.
August 27, 1991.
November 8, 1993.
November 5, 1992.
November 8, 1993.
November 8, 1993.
November 8, 1993.
November 8, 1993.
November 8, 1993.
August 27, 1991.
Introduction ...........................................................................
Chapter
Chapter
Chapter
Chapter
Chapter
Chapter
1
2
3
4
5
6
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Federal Register / Vol. 75, No. 42 / Thursday, March 4, 2010 / Rules and Regulations
LIST OF EFFECTIVE PAGES—Continued
Page title/
description
Page number(s)
Chapter 7 ..............................................................................
Chapter 8 ..............................................................................
Chapter 9 ..............................................................................
6–9 ........................................
6–10 ......................................
7–1 through 7–2 ...................
8–1 through 8–4 ...................
9–1 through 9–4 ...................
Revision number
None
None
None
None
None
shown*
shown*
shown*
shown*
shown*
........................
........................
........................
........................
........................
Date shown
on page(s)
November
November
November
November
November
8, 1993.
5, 1992.
8, 1993.
8, 1993.
30, 1998.
(*Only page 1 of the Record of Revisions of Bombardier (de Havilland) DHC–6 Twin Otter, Dash 7 & Dash 8 Corrosion Prevention and Control
Manual PSM 1–GEN– 5, Part 1, Revision 3, contains the revision level of this document.)
(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.qseries@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
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 February
11, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2010–3226 Filed 3–3–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0718; Directorate
Identifier 2009–NM–025–AD; Amendment
39–16212; AD 2010–05–03]
srobinson on DSKHWCL6B1PROD with RULES
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 747–100, 747–100B,
747–100B SUD, 747–200B, 747–200C,
747–200F, 747–300, 747–400, 747–
400D, 747–400F, 747SR, and 747SP
Series Airplanes
AGENCY: Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
SUMMARY: We are adopting a new
airworthiness directive (AD) for all
VerDate Nov<24>2008
16:20 Mar 03, 2010
Jkt 220001
Model 747–100, 747–100B, 747–100B
SUD, 747–200B, 747–200C, 747–200F,
747–300, 747–400, 747–400D, 747–
400F, 747SR, and 747SP series
airplanes. This AD requires one-time
detailed and high frequency eddy
current inspections for cracks in the
wing and horizontal stabilizer side-ofbody joints and the fuselage skin
circumferential splices, and repair if
necessary. This AD also requires, for
certain airplanes, repetitive detailed
inspections for cracks of the fuselage
skin circumferential splices, and repair
if necessary. This AD results from
Boeing analysis indicating that the wing
and horizontal stabilizer side-of-body
joints, and the fuselage skin
circumferential splices, are susceptible
to fatigue cracking due to high cyclic
loads on the airplane. We are issuing
this AD to detect and correct fatigue
cracking at multiple adjacent locations
in the subject areas, which could
connect to form large cracks and result
in reduced structural integrity leading to
rapid decompression and consequent
loss of control of the airplane.
DATES: This AD is effective April 8,
2010.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of April 8, 2010.
ADDRESSES: For service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention: Data
& Services Management, P.O. Box 3707,
MC 2H–65, Seattle, Washington 98124–
2207; telephone 206–544–5000,
extension 1; fax 206–766–5680; e-mail
me.boecom@boeing.com; Internet
https://www.myboeingfleet.com.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
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.
FOR FURTHER INFORMATION CONTACT: Ivan
Li, Aerospace Engineer, Airframe
Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue, SW., Renton, Washington
98057–3356; telephone (425) 917–6437;
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 all
Model 747 airplanes. That NPRM was
published in the Federal Register on
August 25, 2009 (74 FR 42807). That
NPRM proposed to require one-time
detailed and high frequency eddy
current inspections for cracks in the
wing and horizontal stabilizer side-ofbody joints and the fuselage skin
circumferential splices, and repair if
necessary. That NPRM also proposed to
require, for certain airplanes, repetitive
detailed inspections for cracks of the
fuselage skin circumferential splices,
and repair if necessary.
Comments
We gave the public the opportunity to
participate in developing this AD. We
considered the comments received.
Supportive Comment
Boeing concurs with the contents of
the NPRM.
Requests To Change Compliance Times
UPS asks that we change the NPRM
to extend the compliance time for the
inspections specified in Table 3 of
paragraph 1.E. of Boeing Alert Service
Bulletin 747–51A2060, dated October
30, 2008, and required by paragraph (g)
of the NPRM. UPS states that the
inspections are not to be done until at
least 28,500 total flight cycles or
130,000 total flight hours, whichever
occurs later, have been accumulated on
E:\FR\FM\04MRR1.SGM
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]]>Agencies
[Federal Register Volume 75, Number 42 (Thursday, March 4, 2010)]
[Rules and Regulations]
[Pages 9756-9760]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-3226]
[[Page 9756]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0712; Directorate Identifier 2007-NM-152-AD;
Amendment 39-16205; AD 2010-04-12]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Model DHC-8-100 and
DHC-8-200 Series Airplanes, and Model DHC-8-301, -311, and -315
Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Model DHC-8-100 and DHC-8-200 series airplanes, and DHC-8-301, -311,
and -315 airplanes. This AD requires implementing a corrosion
prevention and control program (CPCP) either by accomplishing specific
tasks or by revising the maintenance inspection program to include a
CPCP. This AD results from the determination that, as airplanes age,
they are more likely to exhibit indications of corrosion. We are
issuing this AD to prevent structural failure of the airplane due to
corrosion.
DATES: This AD is effective April 8, 2010.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of April 8,
2010.
ADDRESSES: 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.qseries@aero.bombardier.com; Internet https://www.bombardier.com.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this 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.
FOR FURTHER INFORMATION CONTACT: Craig Yates, Aerospace Engineer,
Airframe and Mechanical Systems Branch, ANE-171, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New
York 11590; telephone (516) 228-7355; fax (516) 794-5531.
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 Bombardier Model DHC-8-100 and DHC-8-200 series airplanes, and
DHC-8-301, -311, and -315 airplanes. That NPRM was published in the
Federal Register on August 13, 2009 (74 FR 40778). That NPRM proposed
to require implementing a corrosion prevention and control program
(CPCP) either by accomplishing specific tasks or by revising the
maintenance inspection program to include a CPCP.
Comments
We gave the public the opportunity to participate in developing
this AD. We considered the comment received from the single commenter.
Request for Clarification of Inspections
Mesa Airlines requests that we restate that the inspections
required by paragraph (h) of this AD to specify to inspect for
Environmental Damage and/or Corrosion Protection and Control Program
(ED/CPCP). The commenter asserts that the NPRM would require only tasks
identified as both ED and CPCP. Mesa Airlines notes that accomplishing
the ED/CPCP inspections only does not encompass the Air Transport
Association (ATA) of America Codes listed in the NPRM.
We agree. Canadian AD CF-2007-06, dated April 10, 2007, describes
doing ``ED/CPCP'' inspections. The required actions include ``ED''
inspections and inspections identified as both ``ED'' and ``CPCP.'' We
have clarified this in paragraph (h) of this AD. This has been
coordinated with TCCA. We have also revised paragraphs (i) and (i)(2)
of this AD to clarify the inspections.
Explanation of Change Made to This AD
We have revised this AD to identify the legal name of the
manufacturer as published in the most recent type certificate data
sheet for the affected airplane models.
Conclusion
We reviewed the relevant data, considered the comment received, and
determined that air safety and the public interest require adopting the
AD with the changes described previously. We also determined that these
changes will not increase the economic burden on any operator or
increase the scope of the AD.
Explanation of Change to Costs of Compliance
Since issuance of the NPRM, we have increased the labor rate used
in the Costs of Compliance from $80 per work-hour to $85 per work-hour.
The Costs of Compliance information, below, reflects this increase in
the specified hourly labor rate.
Costs of Compliance
This AD affects about 154 airplanes of U.S. registry. There are
between 16 and 17 specific inspections, depending on the applicable
manual identified in Table 1 of this AD. The inspections take about 53
work hours per airplane, per inspection cycle, at an average labor rate
of $85 per work hour. Based on these figures, the estimated cost of
this AD for U.S. operators is $693,770, or $4,505 per airplane, per
inspection cycle.
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
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
[[Page 9757]]
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979), and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
You can find our regulatory evaluation and the estimated costs of
compliance 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:
2010-04-12 Bombardier, Inc.: Amendment 39-16205. Docket No. FAA-
2009-0712; Directorate Identifier 2007-NM-152-AD.
Effective Date
(a) This airworthiness directive (AD) is effective April 8,
2010.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Bombardier, Inc. Model DHC-8-101, DHC-8-
102, DHC-8-103, DHC-8-106, DHC-8-201, DHC-8-202, DHC-8-301, DHC-8-
311, and DHC-8-315 airplanes, certificated in any category; serial
numbers 003 and subsequent.
Subject
(d) Air Transport Association (ATA) of America Codes 32: Landing
Gear, 51: Standard Practices/Structures; 52: Doors; 53: Fuselage;
54: Nacelles/Pylons; 55: Stabilizers; and 57: Wings.
Unsafe Condition
(e) This AD results from the determination that, as airplanes
age, they are more likely to exhibit indications of corrosion. We
are issuing this AD to prevent structural failure of the airplane
due to corrosion.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Manual References
(g) This AD refers to the manuals listed in Table 1 of this AD.
Table 1--Applicable Manuals
------------------------------------------------------------------------
Bombardier model Manual
------------------------------------------------------------------------
(1) DHC-8-101, -102, -103, Part 1, Section 3, Structural Inspection
and -106 airplanes. Program, of the Bombardier de Havilland
Dash 8 Maintenance Program Maintenance
Review Board Report Dash 8 Series 100
Program Support Manual (PSM) 1-8-7,
Revision 22, dated November 1, 2008.
(2) DHC-8-201 and DHC-8-202 Part 1, Section 3, Structural Inspection
airplanes. Program, of the Bombardier de Havilland
Dash 8 Maintenance Program Maintenance
Review Board Report Dash 8 Series 200
PSM 1-82-7, Revision 13, dated November
1, 2008.
(3) Model DHC-8-301, DHC-8- Part 1, Section 3, Structural Inspection
311, and DHC-8-315 airplanes. Program, of the Bombardier de Havilland
Dash 8 Maintenance Program Maintenance
Review Board Report Dash 8 Series 300,
PSM 1-83-7, Revision 22, dated November
1, 2008.
------------------------------------------------------------------------
Inspections
(h) At the later of the times specified in paragraphs (h)(1) and
(h)(2) of this AD, do each of the Environmental Damage/Corrosion
Protection and Control Program (ED/CPCP) inspections identified with
both ``ED'' and ``CPCP,'' or with only ``ED,'' including re-
protection tasks, as applicable, which are found in the ``Type of
Damage'' column of the applicable manual found in Table 1 of this
AD, in accordance with the applicable manual identified in Table 1
of this AD. Except as provided by paragraph (i) of this AD, repeat
each task thereafter at intervals not to exceed the compliance time
specified in the ``Repeat'' column of the applicable manual
identified in Table 1 of this AD.
(1) Within 24 months after the effective date of this AD.
(2) At the compliance time specified in the ``Threshold'' column
of the applicable manual identified in Table 1 of this AD since the
date of issuance of the original Canadian airworthiness certificate
or the date of issuance of the original Canadian export certificate
of airworthiness. If there is no value in the ``Threshold'' column,
use the time specified in the ``Repeat'' column.
(i) After accomplishment of each initial ED/CPCP and ED task
required by paragraph (h) of this AD, the FAA may approve the
incorporation into the operator's approved maintenance/inspection
program of the CPCP specified in the applicable manual identified in
Table 1 of this AD; or the equivalent program that is approved in
accordance with this AD. In all cases, the initial corrosion task
for each airplane area must be completed by the initial compliance
time specified in paragraph (h) of this AD.
(1) Any operator complying with paragraph (i) of this AD may use
an alternative recordkeeping method to that otherwise required by
section 91.417 (``Maintenance records'') or section 121.380
(``Maintenance recording requirements'') of the Federal Aviation
Regulations (14 CFR 91.417 or 14 CFR 121.380, respectively) for the
actions required by this AD, provided that the recordkeeping method
is approved by the FAA and is included in a revision to the
maintenance/inspection program. For the purposes of this paragraph,
``the FAA'' is defined as the cognizant Principal Maintenance
Inspector (PMI) for operators that are assigned a PMI (i.e., part
121, 125, and 135 operators), and the cognizant Flight Standards
District Office for other operators (i.e., part 91 operators).
(2) After the initial accomplishment of the ED/CPCP and ED tasks
required by paragraph (h) of this AD, any extension of the
repetitive intervals specified in the manual must be approved by the
Manager, New York Aircraft Certification Office (ACO), FAA.
Corrective Actions
(j) If any corrosion is found during accomplishment of any
action required by paragraph (h) of this AD: Before further flight,
rework, repair, or replace, as applicable, in accordance with a
method approved by either the Manager, New York ACO, FAA; or
Transport Canada Civil Aviation (TCCA) (or its delegated agent).
Reporting Requirements for Level 3 Corrosion Findings
(k) If any Level 3 corrosion, as defined in Part 1 of the
Bombardier (de Havilland) DHC-6 Twin Otter, Dash 7 & Dash 8
Corrosion Prevention and Control Manual, PSM 1-GEN-5, Revision 3,
dated November 30, 1998, is found during the accomplishment of any
action required by this AD, do paragraphs (k)(1), (k)(2), and (k)(3)
of 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.
(1) Within 3 days after the finding of Level 3 corrosion, report
findings to the Manager, New York ACO, FAA, in accordance with the
Bombardier (de Havilland) DHC-6 Twin Otter, Dash 7 & Dash 8
Corrosion Prevention and Control Manual, PSM 1-GEN-5, Revision 3,
dated November 30, 1998.
[[Page 9758]]
(2) Within 10 days after the finding of Level 3 corrosion,
either submit a plan to the FAA to identify a schedule for
accomplishing the applicable CPCP task on the remainder of the
airplanes in the operator's fleet that are subject to this AD, or
provide data substantiating that the Level 3 corrosion that was
found is an isolated case. The FAA may impose a schedule other than
that proposed in the plan upon finding that a change to the schedule
is needed to ensure that any other Level 3 corrosion is detected in
a timely manner. For the purposes of this paragraph, ``the FAA'' is
defined as the cognizant Principal Maintenance Inspector (PMI) for
operators that are assigned a PMI (i.e., part 121, 125, and 135
operators), and the cognizant Flight Standards District Office for
other operators (i.e., part 91 operators).
(3) Within the time schedule approved in accordance with
paragraph (k)(2) of this AD, accomplish the applicable task on the
remainder of the airplanes in the operator's fleet that are subject
to this AD.
Limiting Future Corrosion Findings
(l) If corrosion findings that exceed Level 1 are found in any
area during any repeat of any CPCP task after the initial
accomplishment required by paragraph (h) of this AD: Within 60 days
after such finding, implement a means approved by the FAA to reduce
future findings of corrosion in that area to Level 1 or better. For
the purposes of this paragraph, ``the FAA'' is defined as the
cognizant PMI for operators that are assigned a PMI (i.e., part 121,
125, and 135 operators), and the cognizant Flight Standards District
Office for other operators (i.e., part 91 operators).
Scheduling Corrosion Tasks for Transferred Airplanes
(m) Before any airplane subject to this AD is transferred and
placed into service by an operator: Establish a schedule for
accomplishing the CPCP tasks required by this AD in accordance with
paragraph (m)(1) or (m)(2) of this AD, as applicable.
(1) For airplanes on which the CPCP tasks required by this AD
have been accomplished previously at the schedule established by
this AD: Perform the first CPCP task in each area in accordance with
the previous operator's schedule, or in accordance with the new
operator's schedule, whichever results in an earlier accomplishment
of that CPCP task. After the initial accomplishment of each CPCP
task in each area as required by this paragraph, repeat each CPCP
task in accordance with the new operator's schedule.
(2) For airplanes on which the CPCP tasks required by this AD
have not been accomplished previously, or have not been accomplished
at the schedule established by this AD: The new operator must
perform each initial CPCP task in each area before further flight or
in accordance with a schedule approved by the FAA. For the purposes
of this paragraph, ``the FAA'' is defined as the cognizant Principal
Maintenance Inspector (PMI) for operators that are assigned a PMI
(i.e., part 121, 125, and 135 operators), and the cognizant Flight
Standards District Office for other operators (i.e., part 91
operators).
Alternative Methods of Compliance (AMOCs)
(n)(1) The Manager, New York ACO, ANE-170, 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: Program
Manager, Continuing Operational Safety, FAA, New York ACO, 1600
Stewart Avenue, Suite 410, Westbury, New York 11590; telephone 516-
228-7300; fax 516-794-5531.
(2) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
Related Information
(o) Canadian airworthiness directive CF-2007-06, dated April 10,
2007, also addresses the subject of this AD.
Material Incorporated by Reference
(p) You must use the service information contained in Table 2 of
this AD, as applicable, to do the actions required by this AD,
unless the AD specifies otherwise.
Table 2--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
Part 1, Section 3, Structural Inspection Program, of the 22 November 1, 2008.
Bombardier de Havilland Dash 8 Maintenance Program
Maintenance Review Board Report Dash 8 Series 100 Program
Support Manual (PSM) 1-8-7.
Part 1, Section 3, Structural Inspection Program, of the 13 November 1, 2008.
Bombardier de Havilland Dash 8 Maintenance Program
Maintenance Review Board Report Series 200 PSM 1-82-7.
Part 1, Section 3, Structural Inspection Program, of the 22 November 1, 2008.
Bombardier de Havilland Dash 8 Maintenance Program
Maintenance Review Board Report Dash 8 Series 300, PSM 1-
83-7.
Bombardier (de Havilland) DHC-6 Twin Otter, Dash 7 & Dash 3 November 30, 1998.
8 Corrosion Prevention and Control Manual, PSM 1[dash]GEN-
5, Part 1.
----------------------------------------------------------------------------------------------------------------
Bombardier de Havilland Dash 8 Maintenance Program Maintenance
Review Board Report Dash 8 Series 100 PSM 1-8-7, Revision 22, dated
November 1, 2008, contains the following effective pages:
List of Effective Pages
----------------------------------------------------------------------------------------------------------------
Page title/ description Page number(s) Revision number Date shown on page(s)
----------------------------------------------------------------------------------------------------------------
Title Page........................ None shown........... 22................... November 1, 2008.
List of Effective Pages........... 1-4.................. None shown*.......... November 1, 2008.
Log of Revisions.................. 1-18................. None shown*.......... November 1, 2008.
Record of Revisions............... 1-2.................. 22................... November 1, 2008.
Contents.......................... 1-4.................. None shown*.......... November 1, 2008.
Section 3:
Subject 3-0................... 1-4.................. None shown*.......... November 1, 2008.
Subject 3-32.................. 1-2.................. None shown*.......... November 1, 2008.
Subject 3-52.................. 1-2.................. None shown*.......... November 1, 2008.
Subject 3-53.................. 1-16................. None shown*.......... November 1, 2008.
Subject 3-54.................. 1-4.................. None shown*.......... November 1, 2008.
Subject 3-55.................. 1-8.................. None shown*.......... November 1, 2008.
Subject 3-57.................. 1-12................. None shown*.......... November 1, 2008.
----------------------------------------------------------------------------------------------------------------
[[Page 9759]]
Bombardier de Havilland Dash 8 Maintenance Program Maintenance
Review Board Report Dash 8 Series 200 PSM 1-82-7, Revision 13, dated
November 1, 2008, contains the following effective pages:
List of Effective Pages
----------------------------------------------------------------------------------------------------------------
Page title/ description Page number(s) Revision number Date shown on page(s)
----------------------------------------------------------------------------------------------------------------
Title Page........................ None shown........... 13................... November 1, 2008.
List of Effective Pages........... 1-4.................. None shown*.......... November 1, 2008.
Log of Revisions.................. 1-8.................. None shown*.......... November 1, 2008.
Record of Revisions............... 1-2.................. 13................... November 1, 2008.
Contents.......................... 1-4.................. None shown*.......... November 1, 2008.
Section 3:
Subject 3-0................... 1-4.................. None shown*.......... November 1, 2008.
Subject 3-32.................. 1-2.................. None shown*.......... November 1, 2008.
Subject 3-52.................. 1-2.................. None shown*.......... November 1, 2008.
Subject 3-53.................. 1-16................. None shown*.......... November 1, 2008.
Subject 3-54.................. 1-4.................. None shown*.......... November 1, 2008.
Subject 3-55.................. 1-6.................. None shown*.......... November 1, 2008.
Subject 3-57.................. 1-12................. None shown*.......... November 1, 2008.
----------------------------------------------------------------------------------------------------------------
Bombardier de Havilland Dash 8 Maintenance Program Maintenance
Review Board Report Dash 8 Series 300 PSM 1-83-7, Revision 22, dated
November 1, 2008, contains the following effective pages:
List of Effective Pages
----------------------------------------------------------------------------------------------------------------
Page title/description Page number(s) Revision number Date shown on page(s)
----------------------------------------------------------------------------------------------------------------
Title Page........................ None shown........... 22................... November 1, 2008.
List of Effective Pages........... 1-4.................. None shown*.......... November 1, 2008.
Log of Revisions.................. 1-18................. None shown*.......... November 1, 2008.
Record of Revisions............... 1-2.................. 22................... November 1, 2008.
Contents.......................... 1-4.................. None shown*.......... November 1, 2008.
Section 3:
Subject 3-0................... 1-4.................. None shown*.......... November 1, 2008.
Subject 3-32.................. 1-2.................. None shown*.......... November 1, 2008.
Subject 3-52.................. 1-2.................. None shown*.......... November 1, 2008.
Subject 3-53.................. 1-18................. None shown*.......... November 1, 2008.
Subject 3-54.................. 1-4.................. None shown*.......... November 1, 2008.
Subject 3-55.................. 1-8.................. None shown*.......... November 1, 2008.
Subject 3-57.................. 1-12................. None shown*.......... November 1, 2008.
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(*Only the title page and Record of Revisions of these documents specify the revision level of these documents.)
Bombardier (de Havilland) DHC-6 Twin Otter, Dash 7 & Dash 8
Corrosion Prevention and Control Manual PSM 1-GEN-5, Part 1,
Revision 3, dated November 30, 1998, contains the following
effective pages:
List of Effective Pages
----------------------------------------------------------------------------------------------------------------
Page title/ description Page number(s) Revision number Date shown on page(s)
----------------------------------------------------------------------------------------------------------------
Title Page........................ None shown........... None shown*.......... November 8, 1993.
Record of Revisions............... 1.................... 3.................... August 27, 1991.
2.................... None shown*.......... August 27, 1991.
Part 1 List of Effective Pages.... 1-2.................. None shown*.......... November 30, 1998.
Part 1 Table of Contents.......... 1-4.................. None shown*.......... November 8, 1993.
Part 1 List of Illustrations...... 1-2.................. None shown*.......... November 8, 1993.
Part 1 List of Tables............. 1.................... None shown*.......... November 8, 1993.
2.................... None shown*.......... August 27, 1991.
Introduction...................... 1-2.................. None shown*.......... November 8, 1993.
3-4.................. None shown*.......... November 5, 1992.
Chapter 1......................... 1-1 through 1-10..... None shown*.......... November 8, 1993.
Chapter 2......................... 2-1 through 2-6...... None shown*.......... November 8, 1993.
Chapter 3......................... 3-1 through 3-4...... None shown*.......... November 8, 1993.
Chapter 4......................... 4-1 through 4-44..... None shown*.......... November 8, 1993.
Chapter 5......................... 5-1 through 5-48..... None shown*.......... November 8, 1993.
Chapter 6......................... 6-1 through 6-8,..... None shown*.......... August 27, 1991.
6-11 through 6-16....
[[Page 9760]]
6-9.................. None shown*.......... November 8, 1993.
6-10................. None shown*.......... November 5, 1992.
Chapter 7......................... 7-1 through 7-2...... None shown*.......... November 8, 1993.
Chapter 8......................... 8-1 through 8-4...... None shown*.......... November 8, 1993.
Chapter 9......................... 9-1 through 9-4...... None shown*.......... November 30, 1998.
----------------------------------------------------------------------------------------------------------------
(*Only page 1 of the Record of Revisions of Bombardier (de Havilland) DHC-6 Twin Otter, Dash 7 & Dash 8
Corrosion Prevention and Control Manual PSM 1-GEN- 5, Part 1, Revision 3, contains the revision level of this
document.)
(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.qseries@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 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 February 11, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-3226 Filed 3-3-10; 8:45 am]
BILLING CODE 4910-13-P
