Airworthiness Directives; Bombardier, Inc. Model DHC-8-400 Series Airplanes, 12629-12634 [2011-5161]
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Federal Register / Vol. 76, No. 45 / Tuesday, March 8, 2011 / Proposed Rules
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Reason
(e) The mandatory continuing
airworthiness information (MCAI) states:
Since 2004, more than 30 reports have
been received of in-flight loss of a rear
passenger door on Diamond aeroplanes, the
majority of which were DA 40. In additional,
at least 18 doors have been replaced because
of damage found on the hinge.
Diamond Aircraft Industries conducted
analyses and structural tests to determine the
root cause of the door opening in flight. The
conclusions were that the primary locking
mechanism provided adequate strength to
react to the loads in flight. It was also
determined that the root cause was the crew
not properly securing the rear passenger door
by the main locking mechanism, prior to
flight. Damage to the hinges has been caused
primarily by external loads (wind gust
conditions) while the aeroplane was parked.
All DA 40 and DA 42 aeroplanes have a
system installed that provides a warning if
the main door latch is not fully closed and
a secondary safety latch (with retaining
bracket) design feature. The initial intended
design function of the latch was to hold the
rear passenger door in the ‘‘near closed’’
position while on the ground, protecting the
door from wind gusts. However, the original
retaining bracket Part Number (P/N) DA4–
5200–00–69 might not hold the door in this
‘‘near closed’’ position while in flight. To
address this problem, DAI have designed an
improved retaining bracket, P/N DA4–5200–
00–69–SB, which has been satisfactory tested
to hold the door closed in flight. In addition,
DAI have revised the Airplane Flight Manual
(AFM) emergency door unlocked/open
procedure.
This condition, if not corrected, could
result in the rear passenger door opening and
departing the aeroplane in flight.
For the reasons described above, this AD
requires implementation of amendment of
the AFM procedures for flight with the door
unlocked/open, and replacement of the
passenger door retaining bracket with an
improved part.
Actions and Compliance
(f) Unless already done, do the following
actions:
(1) Within 6 months after the effective date
of this AD, incorporate Diamond Aircraft
¨
Temporary Revision TR–MAM 42–443, pages
3–55a and 3–55b, dated June 17, 2010, into
the FAA-approved airplane flight manual
following Diamond Aircraft Temporary
¨
Revision TR–MAM 42–443, Cover Page,
dated June 17, 2010.
(2) Within 6 months after the effective date
of this AD, replace the rear passenger door
retaining bracket with an improved design
retaining bracket following Diamond Aircraft
Industries GmbH Mandatory Service Bulletin
No. MSB 42–083/No. MSB 42NG–014, dated
July 13, 2010; and Diamond Aircraft
Industries GmbH Work Instruction WI–MSB
42–083/WI–MSB 42NG–014, dated July 13,
2010.
(3) As of 6 months after the effective date
of this AD, do not install a part number DA4–
5200–00–69 rear passenger door retaining
bracket.
FAA AD Differences
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Note: This AD differs from the MCAI and/
or service information as follows: On
November 23, 2010, we issued AD 2010–25–
01 as a unilateral action to address this
unsafe condition on Diamond Aircraft
Industries GmbH Models DA 40 and DA 40F
airplanes. Subsequently, the European
Aviation Safety Agency (EASA) issued AD
2010–0235 to address the same unsafe
condition on both DA 40 and DA 42 series
airplanes. Since AD 2010–25–01 already
addresses this unsafe condition on Models
DA 40 and DA 40F airplanes, we are not
including those models in this AD.
¨
MAM 42–443, pages 3–55a and 3–55b, dated
June 17, 2010, for related information. For
service information related to this AD,
contact Diamond Aircraft Industries GmbH,
N.A. Otto-Stra+e 5, A–2700 Wiener Neustadt,
Austria, telephone: +43 2622 26700; fax: +43
2622 26780; e-mail: office@diamond-air.at;
Internet: https://www.diamond-air.at. You
may review copies of the referenced service
information at the FAA, Small Airplane
Directorate, 901 Locust, Kansas City,
Missouri 64106. For information on the
availability of this material at the FAA, call
816–329–4148.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
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: Mike Kiesov, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4144; fax: (816) 329–
4090. Before using any approved AMOC on
any airplane to which the AMOC applies,
notify your appropriate principal inspector
(PI) in the FAA Flight Standards District
Office (FSDO), or lacking a PI, your local
FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, a Federal
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave., SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
Issued in Kansas City, Missouri, on March
2, 2011.
John R. Colomy,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
Related Information
(h) Refer to MCAI EASA AD 2010–0235,
dated November 10, 2010; Diamond Aircraft
Industries GmbH Mandatory Service Bulletin
No. MSB 42–083/No. MSB 42NG–014, dated
July 13, 2010; Diamond Aircraft Industries
GmbH Work Instruction WI–MSB 42–083/
WI–MSB 42NG–014, dated July 13, 2010; and
Diamond Aircraft Temporary Revision TR–
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[FR Doc. 2011–5176 Filed 3–7–11; 8:45 am]
BILLING CODE 4910–13–P
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
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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:
SUMMARY:
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
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
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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
thd.qseries@aero.bombardier.com;
Internet https://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 https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this 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:
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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 https://
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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.
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
Requirement in AD
2007–22–09
Corresponding requirement in this proposed AD
paragraph (f)
paragraph (g)
paragraph (h)
paragraph (i)
paragraph (j)
paragraph (l)
paragraph (g).
paragraph (h).
paragraph (i).
paragraph (j).
paragraph (k).
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).
FAA’s Determination and Requirements
of This Proposed AD
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.
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
Differences Between This AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
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Federal Register / Vol. 76, No. 45 / Tuesday, March 8, 2011 / Proposed Rules
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.
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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
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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.
Authority for This Rulemaking
VerDate Mar<15>2010
products identified in this rulemaking
action.
§ 39.13
[Amended]
2. The FAA amends § 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.
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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 leftand 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
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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
Bombardier Repair Drawing 8/4–32–059 .........................................................................................................
Bombardier Repair Drawing 8/4–32–059 .........................................................................................................
Bombardier Repair Drawing 8/4–32–059 .........................................................................................................
New Requirements of this AD
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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.
VerDate Mar<15>2010
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Jkt 223001
Note 6: Guidance for doing a general visual
inspection to detect discrepancies of the leftand 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.
PO 00000
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1
2
3
Date
September 12, 2007.
September 13, 2007.
September 13, 2007.
(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
E:\FR\FM\08MRP1.SGM
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Federal Register / Vol. 76, No. 45 / Tuesday, March 8, 2011 / Proposed Rules
mstockstill on DSKH9S0YB1PROD with PROPOSALS
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.
VerDate Mar<15>2010
19:07 Mar 07, 2011
Jkt 223001
(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
PO 00000
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Fmt 4702
Sfmt 4702
12633
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.
E:\FR\FM\08MRP1.SGM
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12634
Federal Register / Vol. 76, No. 45 / Tuesday, March 8, 2011 / Proposed Rules
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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28661; Directorate
Identifier 2007–NM–013–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Model 737–600, –700, –700C,
–800, and –900 Series Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Supplemental notice of
proposed rulemaking (NPRM);
reopening of comment period.
AGENCY:
We are revising an earlier
proposed airworthiness directive (AD)
for the products listed above. That
NPRM proposed to require installation
of an automatic shutoff system for the
center tank fuel boost pumps,
installation of a placard in the airplane
flight deck if necessary, and concurrent
modification of the P5–2 fuel control
module assembly. That NPRM also
proposed to require revisions to the
Limitations and Normal Procedures
sections of the airplane flight manual to
advise the flightcrew of certain
operating restrictions for airplanes
equipped with an automated center tank
fuel pump shutoff control. Additionally,
that NPRM proposed to require a
revision to the Airworthiness
Limitations (AWL) section of the
Instructions for Continued
Airworthiness (ICA) to incorporate AWL
No. 28–AWL–19 and No. 28–AWL–23.
That NPRM further proposed to require
installation of a secondary control relay
for the electrical control circuit of each
of the two center tank fuel boost pumps.
That NPRM was prompted by fuel
system reviews conducted by the
manufacturer. This action revises that
NPRM by adding airplanes, adding
additional operational testing of the
automatic shutoff system for certain
airplanes, removing the requirement for
incorporating AWL No. 28–AWL–19
into the AWL section of the ICA, and
adding an option of installation and
maintenance of universal fault
interrupters using a certain
supplemental type certificate. We are
proposing this supplemental NPRM to
mstockstill on DSKH9S0YB1PROD with PROPOSALS
SUMMARY:
VerDate Mar<15>2010
19:07 Mar 07, 2011
Jkt 223001
prevent center tank fuel pump operation
with continuous low pressure, which
could lead to friction sparks or
overheating in the fuel pump inlet that
could create a potential ignition source
inside the center fuel tank. These
conditions, in combination with
flammable fuel vapors, could result in a
center fuel tank explosion and
consequent loss of the airplane. Since
these actions impose an additional
burden over those proposed in the
NPRM, we are reopening the comment
period to allow the public the chance to
comment on these proposed changes.
DATES: We must receive comments on
this supplemental NPRM by April 4,
2011.
You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue, SE., Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue, SE., Washington, DC 20590,
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
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. 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.
ADDRESSES:
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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
PO 00000
Frm 00026
Fmt 4702
Sfmt 4702
Tak
Kobayashi, Aerospace Engineer,
Propulsion Branch, ANM–140S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; phone: (425)
917–6499; fax: (425) 917–6590; e-mail:
Takahisa.Kobayashi@faa.gov.
FOR FURTHER INFORMATION CONTACT:
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–2007–28661; Directorate Identifier
2007–NM–013–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 because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
We issued an NPRM to amend 14 CFR
part 39 to include an airworthiness
directive (AD) that would apply to
certain Model 737–600, –700, –700C,
–800, and –900 series airplanes. That
NPRM published in the Federal
Register on July 10, 2007 (72 FR 37479).
That NPRM proposed to require
installation of an automatic shutoff
system for the center tank fuel boost
pumps, installation of a placard in the
airplane flight deck if necessary, and
concurrent modification of the P5–2 fuel
control module assembly. That NPRM
proposed to require revisions to the
Limitations and Normal Procedures
sections of the airplane flight manual to
advise the flightcrew of certain
operating restrictions for airplanes
equipped with an automated center tank
fuel pump shutoff control. Additionally,
that NPRM proposed to require a
revision to the Airworthiness
Limitations (AWL) section of the
Instructions for Continued
Airworthiness (ICA) to incorporate AWL
No. 28–AWL–19 and No. 28–AWL–23.
That NPRM also proposed to require
installation of a secondary control relay
for the electrical control circuit of each
of the two center tank fuel boost pumps.
E:\FR\FM\08MRP1.SGM
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]]>Agencies
[Federal Register Volume 76, Number 45 (Tuesday, March 8, 2011)]
[Proposed Rules]
[Pages 12629-12634]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-5161]
-----------------------------------------------------------------------
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).
-----------------------------------------------------------------------
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 https://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 thd.qseries@aero.bombardier.com; Internet https://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 https://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this 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 https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this 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
