[Federal Register Volume 76, Number 45 (Tuesday, March 8, 2011)]
[Proposed Rules]
[Pages 12629-12634]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-5161]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0151; Directorate Identifier 2009-NM-205-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier, Inc. Model DHC-8-400 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above that would supersede an existing AD. 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:
Two cases of main landing gear collapse had been reported. Main
landing gear collapse may result in unsafe landing of the aircraft.
* * * * *
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 April 22, 2011.
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,
[[Page 12630]]
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., Q-Series Technical Help Desk, 123 Garratt Boulevard,
Toronto, Ontario M3K 1Y5, Canada; telephone 416-375-4000; fax 416-375-
4539; e-mail [email protected]; 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 (ACO), 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-2011-0151;
Directorate Identifier 2009-NM-205-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 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
On October 19, 2007, we issued AD 2007-22-09, Amendment 39-15245
(72 FR 61288, October 30, 2007). That AD required actions intended to
address an unsafe condition on the products listed above.
Since we issued AD 2007-22-09, Transport Canada Civil Aviation
(TCCA), which is the aviation authority for Canada, has issued Canadian
Airworthiness Directive CF-2007-20R2, dated February 6, 2009 (referred
to after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
Two cases of main landing gear collapse had been reported. Main
landing gear collapse may result in unsafe landing of the aircraft.
Revision 1 of this directive amended the time compliance in
paragraph C.2 (3 months in addition to 500 hours air time), to add
new paragraph C.3 to cater for retract actuator which has
accumulated less than 4,000 landings or 2 years since new and to add
new paragraphs B.2 and C.4 to require that the respective
inspections be repetitively performed until terminating action
becomes available.
Revision 2 of this directive amends the detailed visual
inspection requirement in paragraph C.3 to include the main landing
gear retract actuator, part number 46550-11, and to add new
paragraph F to mandate the incorporation of main landing gear
retract actuator part number, 46550-13 as the terminating action and
to add new paragraph G for the maintenance requirement.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Bombardier has issued Service Bulletin 84-32-55, Revision A, dated
March 10, 2008; and Repair Drawing 8/4-32-059, Issue 7, dated June 26,
2008. Bombardier has also issued Temporary Revision (TR) MRB-35, dated
November 18, 2008, to Section 1-32 of Part 1 of the Bombardier Q400
Dash 8 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.
Changes to AD 2007-22-09
This proposed AD would retain certain requirements of AD 2007-22-
09. Since AD 2007-22-09 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this proposed AD, as listed in
the following table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement in this
Requirement in AD 2007-22-09 proposed AD
------------------------------------------------------------------------
paragraph (f) paragraph (g).
paragraph (g) paragraph (h).
paragraph (h) paragraph (i).
paragraph (i) paragraph (j).
paragraph (j) paragraph (k).
paragraph (l) paragraph (v)(3).
------------------------------------------------------------------------
We have revised paragraph (f) of AD 2007-22-09 to remove reference
to Tasks Z700-03E and Z700-04E specified in Part 1 (Maintenance Review
Board Report) of the Bombardier DHC-8 Series 400 Maintenance
Requirements Manual (PSM 1-84-7). Instead, we have added Note 3 to this
AD to specify that guidance on doing a general visual inspection to
detect discrepancies of the left- and right-hand main landing gear
system can be found in Tasks Z700-03E and Z700-04E of Part 1
(Maintenance Review Board Report) of the Bombardier DHC-8 Series 400
Maintenance Requirements Manual (PSM 1-84-7).
Change to Applicability of AD 2007-22-09
AD 2007-22-09 applies to airplanes having serial numbers (S/Ns) 003
and subsequent, which now corresponds to S/Ns 4003 and subsequent. This
proposed AD applies to S/Ns 4003, 4004, 4006, and 4008 through 4208
inclusive, and also adds S/N 4001. The airplanes having serial numbers
other than those specified in the Applicability of this proposed AD are
not affected by the identified unsafe condition.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
[[Page 12631]]
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 55 products of U.S. registry.
The actions that are required by AD 2007-22-09 and retained in this
proposed AD take about 5 work-hours per product, at an average labor
rate of $85 per work hour. Based on these figures, the estimated cost
of the currently required actions is $425 per product.
We estimate that it would take about 8 work-hours per product to
comply with the new basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Required parts would cost about
$27,511 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 $1,550,505, or $28,191 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 responsibilities 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 Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
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 removing Amendment 39-15245 (72 FR
61288, October 30, 2007) and adding the following new AD:
Bombardier, Inc.: Docket No. FAA-2011-0151; Directorate Identifier
2009-NM-205-AD.
Comments Due Date
(a) We must receive comments by April 22, 2011.
Affected ADs
(b) The AD supersedes AD 2007-22-09, Amendment 39-15245.
Applicability
(c) This AD applies to Bombardier, Inc. Model DHC-8-400, -401,
and -402 airplanes, certificated in any category, having serial
numbers (S/Ns) 4001, 4003, 4004, 4006, and 4008 through 4208
inclusive.
Subject
(d) Air Transport Association (ATA) of America Code 32: Landing
Gear.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Two cases of main landing gear collapse had been reported. Main
landing gear collapse may result in unsafe landing of the aircraft.
* * * * *
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of AD 2007-22-09, With Updated Service Information, Limited
Affected Airplanes, and Revised Compliance Times
General Visual Inspection of Main Landing Gear (MLG) System, and
Corrective Actions
(g) For airplanes having S/Ns 003, 004, 006, and 008 through 182
inclusive (now referred to as S/Ns 4003, 4004, 4006, and 4008
through 4182 inclusive), before further flight, do a general visual
inspection to detect discrepancies of the left- and right-hand MLG
system and do all applicable corrective actions, in accordance with
a method approved by the Manager, New York Aircraft Certification
Office (ACO), FAA; or Transport Canada Civil Aviation (TCCA) (or its
delegated agent).
Note 1: For the purposes of this AD, a general visual inspection
is: ``A visual examination of an interior or exterior area,
installation, or assembly to detect obvious damage, failure, or
irregularity. This level of inspection is made from within touching
distance unless otherwise specified. A mirror may be necessary to
ensure visual access to all surfaces in the inspection area. This
level of inspection is made under normally available lighting
conditions such as daylight, hangar lighting, flashlight, or
droplight and may require removal or opening of access panels or
doors. Stands, ladders, or platforms may be required to gain
proximity to the area being checked.''
Note 2: Guidance on doing a general visual inspection to detect
discrepancies of the left- and right-hand MLG system can be found in
Tasks Z700-03E and Z700-04E of Part 1 (Maintenance Review Board
Report) of the Bombardier DHC-8 Series 400 Maintenance Requirements
Manual (PSM 1-84-7).
General Visual Inspection of the Jam Nut of the Retract Actuator of the
MLG and Corrective Actions
(h) For all airplanes except for the airplane having serial
number 4001: Before further flight, do a general visual inspection
of the jam nut of the retract actuator of the left- and right-hand
MLG to ensure the wire lock is in place and the nut is secured. If
the wire lock is not in place or if the jam nut is not secured,
before further flight, adjust the retracted length of the rod end,
torque the jam nut, install a wire lock, and lubricate the piston,
as applicable, in accordance with
[[Page 12632]]
Bombardier Repair Drawing (RD) 8/4-32-059, Issue 4, dated September
14, 2007; or Issue 7, dated June 26, 2008. As of the effective date
of this AD, use only Bombardier RD 8/4-32-059, Issue 7, dated June
26, 2008. Doing the revision required by paragraph (r) of this AD
terminates the inspection required by this paragraph.
Note 3: Bombardier RD 8/4-32-059, Issue 4, dated September 14,
2007, refers to Goodrich Service Concession Request SCR 086-07,
Revision C, dated September 14, 2007 (specifically item 14); and
Bombardier RD 8/4-32-059, Issue 7, dated June 26, 2008, refers to
Goodrich Service Concession Request SCR 086-07, Revision F, dated
June 13, 2008 (specifically item 14); as an additional source of
service information for adjusting the retracted length of the rod
end, torquing the jam nut, installing a wire lock, and lubricating
the piston if necessary, as required by paragraph (h) of this AD.
Detailed Inspection of the Retract Actuator of the MLG, With Extended
Compliance Time for Paragraph (j) of This AD
(i) For airplanes having S/Ns 003, 004, 006, and 008 through 182
inclusive (now referred to as S/Ns 4003, 4004, 4006, and 4008
through 4182 inclusive) on which the retract actuator of the MLG, P/
N 46550-7 or 46550-9, has accumulated 8,000 or more total landings
or has been in-service 4 or more years since new, as of November 14,
2007 (the effective date of 2007-22-09): Before further flight, do a
detailed inspection of affected parts for any signs of corrosion or
wear, and applicable related investigative and corrective actions,
in accordance with Bombardier RD 8/4-32-059, Issue 4, dated
September 14, 2007; or Issue 7, dated June 26, 2008. As of the
effective date of this AD, use only Bombardier RD 8/4-32-059, Issue
7, dated June 26, 2008.
Note 4: For the purposes of this AD, a detailed inspection is:
``An intensive examination of a specific item, installation, or
assembly to detect damage, failure, or irregularity. Available
lighting is normally supplemented with a direct source of good
lighting at an intensity deemed appropriate. Inspection aids such as
mirror, magnifying lenses, etc., may be necessary. Surface cleaning
and elaborate procedures may be required.''
(j) For airplanes having S/Ns 003, 004, 006, and 008 through 182
inclusive (now referred to as S/Ns 4003, 4004, 4006, and 4008
through 4182 inclusive) with a retract actuator of the MLG, P/N
46550-7 or 46550-9, other than those identified in paragraph (i) of
this AD: Do a detailed inspection of affected parts for any signs of
corrosion or wear, and applicable related investigative and
corrective actions, in accordance with Bombardier RD 8/4-32-059,
Issue 4, dated September 14, 2007; or Issue 7, dated June 26, 2008;
at the later of the times specified in paragraphs (j)(1) and (j)(2)
of this AD. As of the effective date of this AD, use only Bombardier
RD 8/4-32-059, Issue 7, dated June 26, 2008.
(1) Before the accumulation of 4,500 total landings or 27 months
since new, whichever occurs first.
(2) Within 500 flight hours after November 14, 2007, or within 3
months after the effective date of this AD, whichever occurs first.
Note 5: Bombardier RD 8/4-32-059, Issue 7, dated June 26, 2008,
refers to Goodrich Service Concession Request SCR 086-07, Revision
F, dated June 13, 2008, as an additional source of service
information for accomplishing the applicable related investigative
and corrective actions required by paragraphs (i) and (j) of this
AD.
Actions Done in Accordance With Previous Issues of Service Information
(k) Actions done before November 14, 2007, in accordance with
repair drawings specified in Table 1 of this AD, are acceptable for
compliance with the corresponding actions specified in paragraphs
(h) through (j) of this AD.
Table 1--Previous Repair Drawings
------------------------------------------------------------------------
Document Issue Date
------------------------------------------------------------------------
Bombardier Repair Drawing 8/4- 1 September 12, 2007.
32-059.
Bombardier Repair Drawing 8/4- 2 September 13, 2007.
32-059.
Bombardier Repair Drawing 8/4- 3 September 13, 2007.
32-059.
------------------------------------------------------------------------
New Requirements of this AD
General Visual Inspection of the Jam Nut of the Retract Actuator of
the MLG, and Corrective Actions
(l) For all airplanes: At the later of the times specified in
paragraphs (l)(1) and (l)(2) of this AD, do a general visual
inspection of the left- and right-hand MLG retract actuator jam nut
to ensure that the wire lock is in place and that the nut is secure,
in accordance with a method approved by the Manager, New York
Aircraft Certification Office (ACO), FAA; or Transport Canada Civil
Aviation (TCCA) (or its delegated agent). If the wire lock is not in
place or the jam nut is not secured, before further flight, re-
torque the jam nut and safety lockwire, in accordance with
Bombardier RD 8/4-32-059, Issue 7, dated June 26, 2008. Repeat the
inspection thereafter at intervals not to exceed 250 flight cycles
or 30 days, whichever occurs first. Doing the revision required by
paragraph (r) of this AD terminates the inspections required by this
paragraph.
(1) Within 250 flight cycles or 30 days after accomplishing the
inspection required by paragraph (h) of this AD, whichever occurs
first.
(2) Within 7 days after the effective date of this AD.
Note 6: Guidance for doing a general visual inspection to
detect discrepancies of the left- and right-hand MLG system can be
found in Tasks Z700-03E and Z700-04E of Part 1 (Maintenance Review
Board Report) of the Bombardier DHC-8 Series 400 Maintenance
Requirements Manual (PSM 1-84-7).
Detailed Inspection of the Retract Actuator of the MLG, and Related
Investigative and Corrective Actions
(m) For airplanes equipped with a MLG retract actuator having P/
N 46550-7 or 46550-9: At the later of the times specified in
paragraphs (m)(1) and (m)(2) of this AD, do a detailed inspection of
affected parts for any signs of corrosion or wear, and do applicable
related investigative and corrective actions, in accordance with
Bombardier RD 8/4-32-059, Issue 7, dated June 26, 2008. Do all
applicable related investigative and corrective actions before
further flight. Repeat the inspection thereafter at intervals not to
exceed 2,000 flight cycles or 12 months, whichever occurs first.
(1) Within 2,000 flight cycles or within 12 months after
accomplishing the inspection required by paragraph (i) or (j) of
this AD, whichever occurs first.
(2) Within 30 days after the effective date of this AD.
(n) For airplanes having serial numbers 4001, 4003, 4004, 4006,
and 4008 through 4182 inclusive equipped with a MLG retract actuator
having P/N 46550-11: At the later of the times specified in
paragraphs (n)(1) and (n)(2) of this AD, do a detailed inspection of
affected parts for any signs of corrosion or wear, and applicable
related investigative and corrective actions, in accordance with
Bombardier RD 8/4-32-059, Issue 7, dated June 26, 2008. Do all
applicable related investigative and corrective actions before
further flight. Repeat the inspection thereafter at intervals not to
exceed 2,000 flight cycles or 12 months, whichever occurs first.
(1) Before the accumulation of 4,500 total landings or 27 months
since new, whichever occurs first.
(2) Within 500 flight hours or 3 months after the effective date
of this AD, whichever occurs first.
(o) For airplanes having serial numbers 4001, 4003, 4004, 4006,
and 4008 through 4182 inclusive equipped with a MLG retract actuator
having P/N 46550-7, P/N 46550-9, or P/N 46550-11, and that have
accumulated 7,500 total flight cycles or more as of the effective
date of this AD, or that have more than 48 months since new: Within
500 flight cycles or 3 months after the effective date of this AD,
whichever occurs first, replace the affected retract actuator with a
new design
[[Page 12633]]
retract actuator having P/N 46550-13, in accordance with Bombardier
Service Bulletin 84-32-55, Revision A, dated March 10, 2008
(Bombardier Modsum 4-901603). Doing the replacement specified in
this paragraph terminates the requirements of paragraphs (i), (j),
(m), and (n) of this AD.
(p) For airplanes having serial numbers 4001, 4003, 4004, 4006,
and 4008 through 4182 inclusive equipped with MLG retract actuators
having P/N 46550-7, P/N 46550-9, or P/N 46550-11, that have
accumulated less than 7,500 total flight cycles as of the effective
date of this AD and that have 48 months or less since new: Prior to
the accumulation of 8,000 total flight cycles, or within 51 months
since new, whichever occurs first, replace the affected retract
actuator with a new design retract actuator having P/N 46550-13, in
accordance with Bombardier Service Bulletin 84-32-55, Revision A,
dated March 10, 2008 (Bombardier Modsum 4-901603). Doing the
replacement specified in this paragraph terminates the requirements
of paragraphs (i), (j), (m), and (n) of this AD.
(q) Replacing the affected retract actuator with a new design
retract actuator having P/N 46550-15, in accordance with the
Accomplishment Instructions of Bombardier Service Bulletin 84-32-60,
Revision A, dated September 29, 2008 (Bombardier Modsum 4-901610),
is also acceptable for compliance with the requirements of
paragraphs (o) and (p) of this AD.
Revision of the Maintenance Program
(r) For all airplanes: Within 30 days after the effective date
of this AD, revise the maintenance program by incorporating Task
320100-211 (repetitive detailed inspections of the retraction
actuator rod end jam nut, gland nut, and actuator attachment pins
for condition, the security of installation, and corrosion) and Task
320100-212 (repetitive restorations of the retraction actuator for
complete overhaul), as specified in Bombardier Temporary Revision
(TR) MRB-35, dated November 18, 2008, to the Bombardier Q400 Dash 8
Maintenance Requirements Manual (PSM 1-84-7). Doing this revision
terminates the requirements of paragraphs (h) and (l) of this AD.
The initial compliance times for doing Task 320100-211 and Task
320100-212 are specified in paragraphs (r)(1) and (r)(2) of this AD.
After doing this revision, no alternative inspections, restorations,
or intervals may be used, unless the inspections, restorations, or
intervals are approved as an alternative method of compliance (AMOC)
in accordance with the procedures specified in paragraph (v)(1) of
this AD.
(1) For Task 320100-211 in Bombardier TR MRB-35, dated November
18, 2008, to the Bombardier Q400 Dash 8 Maintenance Requirements
Manual (PSM 1-84-7): The compliance time for the initial inspection
is within 600 flight hours after the effective date of this AD.
(2) For Task 320100-212 in Bombardier TR MRB-35, dated November
18, 2008, to the Bombardier Q400 Dash 8 Maintenance Requirements
Manual (PSM 1-84-7): The compliance time for the initial restoration
is the later of the times of paragraphs (r)(2)(i) and (r)(2)(ii) of
this AD.
(i) Prior to the accumulation of 25,000 total flight cycles, or
within 12 years since the date of issuance of the original
airworthiness certificate or the date of issuance of the original
export certificate of airworthiness, whichever occurs first.
(ii) Within 500 flight cycles after the effective date of this
AD.
Note 7: The actions required by paragraph (r) of this AD may be
done by inserting copies of Bombardier TR MRB-35, dated November 18,
2008, into the Bombardier Q400 Dash 8 Maintenance Requirements
Manual (PSM 1-84-7). When this TR has been included in general
revisions of the PSM, the general revisions may be inserted in the
PSM, provided the relevant information in the general revision is
identical to that in Bombardier TR MRB-35, dated November 18, 2008.
Credit for Actions Accomplished in Accordance With Previous Service
Information
(s) Doing a general visual inspection of the jam nut of the
retract actuator of the left- and right-hand MLG; and doing a
detailed inspection of affected parts for any signs of corrosion or
wear, and applicable related investigative and corrective actions;
is also acceptable for compliance with the corresponding
requirements of paragraphs (h), (i), (j), (l), (m), and (n) of this
AD, if done before the effective date of this AD in accordance with
Bombardier Repair Drawing 8/4-32-059, Issue 5, dated September 20,
2007; or Bombardier Repair Drawing 8/4-32-059, Issue 6, dated
January 31, 2008.
(t) Replacing the affected retract actuator with a new design
retract actuator having P/N 46550-13 is also acceptable for
compliance with the requirements of paragraphs (o) and (p) of this
AD, if done before the effective date of this AD in accordance with
Bombardier Service Bulletin 84-32-55, dated January 14, 2008 (Modsum
4-901603).
No Reporting
(u) While Canadian Airworthiness Directive CF-2007-20R2, dated
February 6, 2009, has a reporting action, this AD does not require
reporting.
FAA AD Differences
Note 8: This AD differs from the MCAI and/or service
information as follows: Although the MCAI or service information
tells you to submit information to the manufacturer, paragraph (u)
of this AD specifies that such submittal is not required.
Other FAA AD Provisions
(v) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York Aircraft 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. AMOCs approved previously in
accordance with AD 2007-22-09, Amendment 39-15245, are approved as
AMOCs for the corresponding provisions of paragraph (i) and (j) of
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) Special Flight Permits: Special flight permits may be issued
in accordance with sections 21.197 and 21.199 of the Federal
Aviation Regulations (14 CFR 21.197 and 21.199) to operate the
airplane to a location where the airplane can be inspected (if the
operator elects to do so), provided that the procedures and
limitations in paragraphs (v)(3)(i) and (v)(3)(ii) of this AD are
adhered to.
(i) Flight Crew Limitations and Procedures:
(A) Ferry flight with gear extended and pinned;
(B) Landing to be conducted at a minimum descent rate;
(C) Minimize braking on landing;
(D) Flight to be conducted in accordance with Section 4.8 of the
Aircraft Operating Manual (AOM);
(E) Only essential crew on board; and
(F) Flight in known or forecast icing condition is prohibited.
(ii) Maintenance Procedures:
(A) Do the general visual inspection required by paragraph (h)
of this AD;
(B) Do the general visual inspections of the stabilizer stay and
the hinge points of the MLG for general condition and security, in
accordance with Bombardier Q400 All Operator Message 236A, dated
September 11, 2007;
(C) If no discrepancy is detected during the inspections
required by paragraph (v)(3)(ii)(A) and (v)(3)(ii)(B) of this AD,
before further flight, insert the ground lock pins and a wire lock
of the MLG in place.
(D) Ensure the nose landing gear ground lock is engaged.
Related Information
(w) Refer to MCAI Canadian Airworthiness Directive CF-2007-20R2,
dated February 6, 2009; Bombardier Service Bulletin 84-32-55,
Revision A, dated March 10, 2008; Bombardier Service Bulletin 84-32-
60, Revision A, dated September 29, 2008; Bombardier Repair Drawing
8/4-32-059, Issue 7, dated June 26, 2008; and Bombardier Temporary
Revision MRB-35, dated November 18, 2008, to the Bombardier Q400
Dash 8 Maintenance Requirements Manual (PSM 1-84-7); for related
information.
[[Page 12634]]
Issued in Renton, Washington, on February 22, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-5161 Filed 3-7-11; 8:45 am]
BILLING CODE 4910-13-P