COMMENTS DUE DATE
(a) We must receive comments by May 3, 2010.
AFFECTED ADS
(b) None.
APPLICABILITY
(c) This AD applies to Bombardier, Inc. Model DHC-8-400, -401, and -402
airplanes, having serial numbers (S/Ns) 4001, 4003, 4004, 4006, and
4008 through 4227 inclusive, certificated in any category.
NOTE 1: This AD requires revisions to certain operator maintenance docum-
ents to include new inspections. Compliance with these inspections is
required by 14 CFR 91.403(c). For airplanes that have been previously
modified, altered, or repaired in the areas addressed by these
inspections, the operator may not be able to accomplish the inspections
described in the revisions. In this situation, to comply with 14 CFR
91.403(c), the operator must request approval for an alternative method of
compliance according to paragraph (i) of this AD. The request should
include a description of changes to the required inspections that will
ensure the continued damage tolerance of the affected structure. The FAA
has provided guidance for this determination in Advisory Circular (AC)
25.1529-1A.
SUBJECT
(d) Air Transport Association (ATA) of America Code 32: Landing gear.
REASON
(e) The mandatory continuing airworthiness information (MCAI) states:
Certain main landing gear components have experienced premature failure
during certification testing. Revision has been made to the DHC-8-400
Maintenance Requirements Manual, Airworthiness Limitation Items (ALI), to
incorporate the revised safe life limits for the main landing gear lock
actuator assembly, retraction actuator assembly rod end and piston, and
the upper bearing in the main landing gear shock strut assembly. Failure
of these components could adversely affect the structural integrity of the
main landing gear.
This [Canadian] directive is issued to ensure safe operation of the main
landing gear during its service life.
The corrective actions include revising the Airworthiness Limitations
Section (ALS) of the Instructions for Continued Airworthiness, replacing
the upper bearing on certain airplanes, and replacing certain rod ends.
COMPLIANCE
(f) You are responsible for having the actions required by this AD per-
formed within the compliance times specified, unless the actions have
already been done.
ACTIONS
(g) For Model DHC-8-400, -401, and -402 airplanes having S/Ns 4001, 4003,
4004, 4006, and 4008 through 4210 inclusive: Do the actions specified
in paragraphs (g)(1) and (g)(2) of this AD.
(1) Within 60 days after the effective date of this AD: Revise the ALS of
the Instructions for Continued Airworthiness by incorporating the
revised structural safe life limit for the upper bearing having part
number (P[sol]N) 46114-1, as provided in Bombardier Temporary Revision
(TR), ALI-82, dated August 15, 2008, to Part 2, Airworthiness
Limitation Items, of the Bombardier Dash 8 Q400 Maintenance
Requirements Manual (MRM), PSM 1-84-7. The initial compliance time for
replacing the upper bearing is specified in paragraph (g)(2) of this
AD.
(2) Replace the upper bearing having P/N 46114-1 with a new or serviceable
upper bearing, in accordance with Goodrich Dressed Shock Strut
Assembly Main Landing Gear Part No. 46100-29/-31/-33/-35/-37/-39/-41/
-43/-45/-47/-49/-51/-53 and -55 Component Maintenance Manual with
Illustrated Parts List 32-11-03, Revision 11, dated August 22, 2008,
at the applicable time specified in paragraphs (g)(2)(i), (g)(2)(ii),
and (g)(2)(iii), of this AD.
(i) For airplanes having accumulated fewer than 15,000 total flight cycles
as of the effective date of this AD: Replace prior to the accumulation
of 15,000 total flight cycles.
(ii) For airplanes having accumulated 15,000 total flight cycles or more,
but fewer than 20,000 total flight cycles, as of the effective date
of this AD: Replace prior to the accumulation of 20,000 total flight
cycles.
(iii) For airplanes having accumulated 20,000 total flight cycles or more
as of the effective date of this AD: Replace before further flight.
(h) For Model DHC-8-400, -401, and -402 series airplanes having S/Ns 4001,
4003, 4004, 4006, and 4008 through 4227 inclusive: Do the applicable
actions specified in paragraphs (h)(1) and (h)(2) of this AD.
(1) Within 60 days after the effective date of this AD: Revise the ALS of
the Instructions for Continued Airworthiness to incorporate the
revised safe life limits for the retraction actuator assembly rod end
having P[sol]N P3A2750 and P3A2750-1; retraction actuator assembly
piston having P/N 46570-5; lock actuator cylinder assembly having P/N
46601-1/-3; and lock actuator assembly having P/ N 46600-1/-3/-5/-7;
as provided in Bombardier TR ALI-89, dated March 27, 2009, to Part 2,
Airworthiness Limitation Items, of the Bombardier Dash 8 Q400 MRM, PSM
1-84-7. The initial compliance time for the replacement is specified
in the TR, except as provided by paragraph (h)(2) of this AD.
(2) For airplanes with a main landing gear retraction actuator assembly
rod end that has accumulated more than 9,850 total flight cycles as of
the effective date of this AD: Within 600 flight cycles after the
effective date of this AD, replace any affected rod end having P/Ns
P3A2750 and P3A2750-1 with a new or serviceable rod end, in accordance
with Goodrich Dressed Shock Strut Assembly Main Landing Gear Part No.
46100-29/-31/-33/-35/-37/-39/-41/-43/-45/-47/-49/-51/-53 and -55
Component Maintenance Manual with Illustrated Parts List 32-11-03,
Revision 11, dated August 22, 2008.
(i) After accomplishing the revision specified in paragraph (g)(1) or
(h)(1) of this AD, except as provided in paragraph (j) of this AD, no
alternative replacement times may be approved for this part.
NOTE 2: The ALI revisions required by paragraphs (g) and (h) of this AD
may be done by inserting a copy of Bombardier TRs ALI-82 and ALI-89 into
Part 2, Airworthiness Limitation Items, of the Bombardier Dash 8 Q400 MRM,
PSM 1-84-7. When these TRs have been included in the general revision of
the MRM, the general revision may be inserted into the MRM, provided the
relevant information in the general revision is identical to that in
Bombardier TRs ALI-82 and ALI-89.
FAA AD DIFFERENCES
NOTE 3: This AD differs from the MCAI and/or service information as
follows: The MCAI and service information do not contain replacement
procedures for the upper bearings and rod ends. This AD requires replacing
the upper bearings and rod ends in accordance with Goodrich Dressed Shock
Strut Assembly Main Landing Gear Part No. 46100-29/-31/-33/-35/-37/-39/
-41/-43/ -45/-47/-49/-51/-53 and -55 Component Maintenance Manual with
Illustrated Parts List 32-11-03, Revision 11, dated August 22, 2008.
OTHER FAA AD PROVISIONS
(j) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New York Air-
craft Certification Office (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.
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.
(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 (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.
(4) Special Flight Permits: Special flight permits, as described in Sec-
tion 21.197 and Section 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199), are allowed, provided that the actions
required in paragraph (h) of this AD have been accomplished.
RELATED INFORMATION
(k) Refer to MCAI Canadian Airworthiness Directive CF-2009-17, dated April
22, 2009; Bombardier TR ALI-82, dated August 15, 2008, and
Bombardier TR ALI-89, dated March 27, 2009, to Part 2, Airworthiness
Limitation Items, of the Bombardier Dash 8 Q400 Maintenance
Requirements Manual, PSM 1-84-7; and Goodrich Dressed Shock Strut
Assembly Main Landing Gear Part No. 46100-29/-31/-33/-35/-37/-39/-41/
-43/-45/-47/-49/-51/-53 and -55 Component Maintenance Manual with
Illustrated Parts List 32-11-03, Revision 11, dated August 22, 2008;
for related information.
Issued in Renton, Washington, on March 9, 2010. Jeffrey E. Duven, Acting
Manager, Transport Airplane Directorate, Aircraft Certification Service.
DATES: We must receive comments on this proposed AD by May 3, 2010.
DEPARTMENT OF TRANSPORTATION
FEDERAL AVIATION ADMINISTRATION
14 CFR Part 39
[Docket No. FAA-2010-0229; Directorate Identifier 2009-NM-115-AD] RIN
2120-AA64
AIRWORTHINESS DIRECTIVES; Bombardier, Inc., Model DHC-8-400 Series Air-
planes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
--------------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD results from mandatory continuing
airworthiness information (MCAI) originated by an aviation authority of
another country to identify and correct an unsafe condition on an aviation
product. The MCAI describes the unsafe condition as: Certain main landing
gear components have experienced premature failure during certification
testing. Revision has been made to the DHC-8-400 Maintenance Requirements
Manual, Airworthiness Limitation Items, to incorporate the revised safe
life limits for the main landing gear lock actuator assembly, retraction
actuator assembly rod end and piston, and the upper bearing in the main
landing gear shock strut assembly. Failure of these components could
adversely affect the structural integrity of the main landing gear. The
proposed AD would require actions that are intended to address the unsafe
condition described in the MCAI.
DATES: We must receive comments on this proposed AD by May 3, 2010.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the
instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-40, 1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except
Federal holidays.
For service information identified in this proposed AD, contact
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[dash]mail
thd.qseries@aero.bombardier.com; Internet http://www.bombardier.com. You
may review copies of the referenced service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington.
For information on the availability of this material at the FAA, call 425
-227-1221.
EXAMINING THE AD DOCKET
You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office between
9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD
docket contains this proposed AD, the 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: 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:
COMMENTS INVITED
We invite you to send any written relevant data, views, or arguments about
this proposed AD. Send your comments to an address listed under the
ADDRESSES section. Include "Docket No. FAA-2010-0229; Directorate
Identifier 2009-NM-115-AD" at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this proposed AD. We will consider
all comments received by the closing date and may amend this proposed AD
based on those comments.
We have lengthened the 30-day comment period for proposed ADs that address
MCAI originated by aviation authorities of other countries to provide
adequate time for interested parties to submit comments. The comment
period for these proposed ADs is now typically 45 days, which is
consistent with the comment period for domestic transport ADs.
We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
DISCUSSION
Transport Canada Civil Aviation, which is the aviation authority for
Canada, has issued Canadian Airworthiness Directive CF-2009-17, dated
April 22, 2009 (referred to after this as "the MCAI"), to correct an
unsafe condition for the specified products. The MCAI states:
Certain main landing gear components have experienced premature failure
during certification testing. Revision has been made to the DHC-8-400
Maintenance Requirements Manual, Airworthiness Limitation Items, to
incorporate the revised safe life limits for the main landing gear lock
actuator assembly, retraction actuator assembly rod end and piston, and
the upper bearing in the main landing gear shock strut assembly. Failure
of these components could adversely affect the structural integrity of the
main landing gear.
This [Canadian] directive is issued to ensure safe operation of the main
landing gear during its service life.
The corrective actions include revising the Airworthiness Limitations
Section of the Instructions for Continued Airworthiness, replacing the
upper bearing on certain airplanes, and replacing certain rod ends. You
may obtain further information by examining the MCAI in the AD docket.
RELEVANT SERVICE INFORMATION
Bombardier has issued Temporary Revision ALI-82, dated August 15, 2008;
and Temporary Revision ALI-89, dated March 27, 2009; to Part 2, Airworth-
iness Limitation Items, of the Bombardier Dash 8 Q400 Maintenance
Requirements Manual, PSM 1-84-7. The actions described in this service
information are intended to correct the unsafe condition identified in the
MCAI.
FAA'S DETERMINATION AND REQUIREMENTS OF THIS PROPOSED AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant to
our bilateral agreement with the State of Design Authority, we have been
notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
DIFFERENCES BETWEEN THIS AD AND THE MCAI OR SERVICE INFORMATION
We have reviewed the MCAI and related service information and, in general,
agree with their substance. But we might have found it necessary to use
different words from those in the MCAI to ensure the AD is clear for U.S.
operators and is enforceable. In making these changes, we do not intend to
differ substantively from the information provided in the MCAI and related
service information.
We might also have proposed 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 proposed AD.
COSTS OF COMPLIANCE
Based on the service information, we estimate that this proposed AD would
affect about 62 products of U.S. registry. We also estimate that it would
take about 22 work-hours per product to comply with the basic requirements
of this proposed AD. The average labor rate is $85 per work-hour. Required
parts would cost about $18,588 per product. Where the service information
lists required parts costs that are covered under warranty, we have
assumed that there will be no charge for these costs. As we do not control
warranty coverage for affected parties, some parties may incur costs
higher than estimated here. Based on these figures, we estimate the cost
of the proposed AD on U.S. operators to be $1,268,396, or $20,458 per
product.
AUTHORITY FOR THIS RULEMAKING
Title 49 of the United States Code specifies the FAA's authority to issue
rules on aviation safety. Subtitle I, section 106, describes the authority
of the FAA Administrator. "Subtitle VII: Aviation Programs," describes in
more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in "Subtitle
VII, Part A, Subpart III, Section 44701: General requirements." Under that
section, Congress charges the FAA with promoting safe flight of civil
aircraft in air commerce by prescribing regulations for practices,
methods, and procedures the Administrator finds necessary for safety in
air commerce. This regulation is within the scope of that authority
because it addresses an unsafe condition that is likely to exist or
develop on products identified in this rulemaking action.
REGULATORY FINDINGS
We determined that this proposed AD would not have federalism implications
under Executive Order 13132. This proposed AD would not have a substantial
direct effect on the States, on the relationship between the national
Government and the States, or on the distribution of power and responsib-
ilities among the various levels of government.
For the reasons discussed above, I certify this proposed regulation:
1. Is not a "significant regulatory action" under Executive Order 12866;
2. Is not a "significant rule" under the DOT Regulatory Policies and Proc-
edures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or negative, on a
substantial number of small entities under the criteria of the
Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to comply with
this proposed AD and placed it in the AD docket.
LIST OF SUBJECTS IN 14 CFR PART 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference,
Safety.
THE PROPOSED AMENDMENT
Accordingly, under the authority delegated to me by the Administrator, the
FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
SEC. 39.13 [AMENDED]
2. The FAA amends Sec. 39.13 by adding the following new AD: