Airworthiness Directives; Bombardier Model DHC-8-400 Series Airplanes, 3347-3350 [E7-909]
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Federal Register / Vol. 72, No. 16 / Thursday, January 25, 2007 / Rules and Regulations
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. Before using any AMOC approved
in accordance with § 39.19 on any airplane
to which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(g) Refer to MCAI European Aviation
Safety Agency (EASA) Emergency
Airworthiness Directive 2006–0330-E, dated
October 25, 2006; and Dassault Service
Bulletins F900–366 and F900EX–277, both
dated July 19, 2006; for related information.
Material Incorporated by Reference
(h) You must use Dassault Service Bulletin
F900–366, dated July 19, 2006; or Dassault
Service Bulletin F900EX–277, dated July 19,
2006; as applicable; to do the actions
required by this AD, unless the AD specifies
otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Dassault Falcon Jet, P.O. Box
2000, South Hackensack, New Jersey 07606.
(3) You may review copies at the FAA,
Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington 98057–
3356; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
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Issued in Renton, Washington, on January
12, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 07–258 Filed 1–24–07; 8:45 am]
BILLING CODE 4910–13–P
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Jkt 211001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–26050; Directorate
Identifier 2006–NM–078–AD; Amendment
39–14890; AD 2007–02–03]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–400 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain Bombardier
Model DHC–8–400 series airplanes.
That AD currently requires revising the
airplane flight manual (AFM) to advise
the flightcrew of appropriate procedures
to follow in the event that a main
landing gear (MLG) fails to extend
following a gear-down selection. That
AD also currently requires repetitive
replacement of the left and right MLG
uplock assemblies with new assemblies;
and an inspection of the left and right
MLG uplock rollers for the presence of
an inner low friction liner, and
corrective actions if necessary. This new
AD revises the requirement for replacing
the left and right MLG uplock
assemblies by allowing replacement
with alternative parts. For a certain
MLG uplock assembly, this new AD
requires repetitive inspections of the
uplock hatch lower jaw for the presence
of a wear groove and replacement with
an improved part if necessary. For a
certain MLG uplock assembly, this new
AD requires repetitive inspections of the
uplock roller to ensure that it rotates
freely and replacement with a new part
if necessary. This new AD allows
optional replacement of the left and
right MLG uplock assemblies with
improved parts, which ends the
requirements of the AFM revision and
repetitive replacement and inspections.
This new AD removes airplanes from
the applicability. This AD results from
development of a terminating action.
We are issuing this AD to ensure that
the flightcrew has the procedures
necessary to address failure of an MLG
to extend following a gear-down
selection; and to detect and correct such
failure, which could result in a gear-up
landing and possible injury to
passengers and crew.
DATES: This AD becomes effective
March 1, 2007.
The Director of the Federal Register
approved the incorporation by reference
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3347
of certain publications listed in the AD
as of March 1, 2007.
On April 23, 2002 (67 FR 19101, April
18, 2002), the Director of the Federal
Register approved the incorporation by
reference of Bombardier DHC–8 Alert
Service Bulletin A84–32–15, dated
February 4, 2002.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Bombardier, Inc., Bombardier
Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K
1Y5, Canada, for service information
identified in this AD.
FOR FURTHER INFORMATION CONTACT: Ezra
Sasson, Aerospace Engineer, Systems
and Flight Test Branch, ANE–172, FAA,
New York Aircraft Certification Office,
1600 Stewart Avenue, Suite 410,
Westbury, New York 11590; telephone
(516) 228–7320; fax (516) 794–5531.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that
supersedes AD 2002–08–05, amendment
39–12713 (67 FR 19101, April 18, 2002).
The existing AD applies to certain
Bombardier Model DHC–8–400 series
airplanes. That NPRM was published in
the Federal Register on October 13,
2006 (71 FR 60450). That NPRM
proposed to continue to require revising
the airplane flight manual (AFM) to
advise the flightcrew of appropriate
procedures to follow in the event that a
main landing gear (MLG) fails to extend
following a gear-down selection. That
NPRM also proposed to continue to
require repetitive replacement of the left
and right MLG uplock assemblies with
new assemblies; and an inspection of
the left and right MLG uplock rollers for
the presence of an inner low friction
liner, and corrective actions if
necessary. That NPRM also proposed to
revise the requirement for replacing the
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left and right MLG uplock assemblies by
allowing replacement with alternative
parts. For a certain MLG uplock
assembly, that NPRM also proposed to
require repetitive inspections of the
uplock hatch lower jaw for the presence
of a wear groove and replacement with
an improved part if necessary. For a
certain MLG uplock assembly, that
NPRM also proposed to require
repetitive inspections of the uplock
roller to ensure that it rotates freely and
replacement with a new part if
necessary. That NPRM also proposed to
allow optional replacement of the left
and right MLG uplock assemblies with
improved parts, which would end the
requirements of the AFM revision and
repetitive replacements and inspections.
That NPRM also proposed to remove
airplanes from the applicability.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the one comment that has
been received on the NPRM.
Request To Provide Additional
Terminating Action
Horizon Air requests that we revise
paragraph (k) of the NPRM to provide an
additional terminating action by
allowing replacement with a new or
overhauled uplock assembly having part
number (P/N) 46500–9. Paragraph (k) of
the NPRM proposed only to allow
replacement of uplock assemblies
having P/N 46500–3 or –5 with new or
overhauled uplock assemblies having P/
N 46500–7. As justification, the
commenter states that P/N 46500–9 is
the latest version of the uplock
assembly. The commenter also points
out that Bombardier DHC–8 Service
Bulletin 84–32–46, dated July 4, 2006,
provides instructions for modifying an
uplock assembly having P/N 46500–7
and reidentifying it as P/N 46500–9.
We agree to revise paragraph (k) of
this AD to provide P/N 46500–9 as a
terminating action. We have also revised
paragraphs (g) and (i)(1) of this AD to
allow replacement with P/N 46500–9.
Bombardier DHC–8 Service Bulletin 84–
32–46 modifies an uplock assembly
having P/N 46500–7 by improving
retention of the proximity sensor target.
Therefore, we have determined that a
new or overhauled uplock assembly
having P/N 46500–9 is also adequate for
addressing the unsafe condition of this
AD.
Conclusion
We have carefully reviewed the
available data, including the comment
that has been received, and determined
that air safety and the public interest
require adopting the AD with the
changes described previously. We have
determined that these changes will
neither increase the economic burden
on any operator nor increase the scope
of the AD.
Costs of Compliance
The following table provides the
estimated costs, at an average labor rate
of $80 per work hour, for U.S. operators
to comply with this AD.
ESTIMATED COSTS
Work
hours
Action
AFM revision (required by AD 2002–08–05) ...........
Replacement of uplock assemblies (required by AD
2002–08–05).
Inspection of uplock rollers (required by AD 2002–
08–05).
Inspections of uplock assemblies and uplock rollers
(new action).
Terminating action (new action) ...............................
1 The
None
1 $0
1
Fleet cost
21
21
None
$80 .................................
$320, per replacement
cycle.
$80 .................................
21
$1,680.
$6,720 per replacement
cycle.
$1,680.
5
None
$400 ...............................
21
$8,400.
4
1 $0
$320 ...............................
21
$6,720.
parts manufacturer states that it will supply required parts to operators at no cost.
Authority for This Rulemaking
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1
4
Number of
U.S.registered
airplanes
Cost per
airplane
Parts
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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products identified in this rulemaking
action.
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
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under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
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Federal Register / Vol. 72, No. 16 / Thursday, January 25, 2007 / Rules and Regulations
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by removing amendment 39–12713 (67
FR 19101, April 18, 2002) and by adding
the following new airworthiness
directive (AD):
I
2007–02–03 Bombardier, Inc. (Formerly de
Havilland, Inc.): Amendment 39–14890.
Docket No. FAA–2006–26050;
Directorate Identifier 2006–NM–078–AD.
Effective Date
(a) This AD becomes effective March 1,
2007.
Affected ADs
(b) This AD supersedes AD 2002–08–05.
Applicability
(c) This AD applies to Bombardier Model
DHC–8–400 series airplanes, certificated in
any category; serial numbers 4001 and 4003
through 4087 inclusive; equipped with main
landing gear (MLG) uplock assembly part
numbers (P/Ns) 46500–3 and –5.
Unsafe Condition
(d) This AD results from development of a
terminating action. We are issuing this AD to
ensure that the flightcrew has the procedures
necessary to address failure of an MLG to
extend following a gear-down selection; and
to detect and correct such failure, which
could result in a gear-up landing and
possible injury to passengers and crew.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
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Requirements of AD 2002–08–05
Revision of FAA-Approved Airplane Flight
Manual (AFM)
(f) Within 3 days after April 23, 2002 (the
effective date of AD 2002–08–05), amend all
copies of the FAA-approved Bombardier
Series 400 AFM, PSM 1–84–1A (for Models
400, 401, and 402), by adding the following
procedure to the Limitations section of the
AFM and opposite page 4–21–1 of the AFM;
and advise all flightcrew members of these
changes. (The revision may be accomplished
by inserting a copy of this AD into the
Limitations section of the AFM and affected
paragraphs of the AFM.):
‘‘If ONE main landing gear fails to extend
after performing landing gear extension per
normal procedures given in paragraph 4.3.7
and alternate extension procedures per
paragraph 4.21.1 of the AFM:
1. Visually confirm that the affected gear
has not extended and that the associated
doors have opened.
2. Ensure No. 2 hydraulic system pressure
and quantity are normal and the following
landing gear advisory lights are illuminated:
selector lever amber, gear green locked down
(nose and non-affected main gear), red gear
unlocked (affected main gear) and all amber
doors open.
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3. NOSE L/G RELEASE handle—Return to
the stowed position.
4. LANDING GEAR ALTERNATE
EXTENSION door—Close fully.
5. MAIN L/G RELEASE handle—Return to
the stowed position.
6. LANDING GEAR ALTERNATE
RELEASE door—Close fully.
7. LANDING GEAR lever—DN.
8. L/G DOWN SELECT INHIBIT SW—
Normal and guarded. Check amber doors
open advisory lights out (nose and nonaffected main gear) and LDG GEAR INOP
caution light out.
9. LANDING GEAR lever—UP Check all
gear, door and LANDING GEAR lever
advisory lights out.
10. With minimum delay, LANDING GEAR
lever—DN. Check 3 green gear locked down
advisory lights illuminate, all amber doors
open, red gear unlocked and selector lever
amber advisory lights out.
11. Items 9 and 10 may be repeated in an
effort to achieve 3 gear down and locked.
CAUTION
Should the LDG GEAR INOP caution light
illuminate, or loss of no. 2 hydraulic system
pressure or quantity, or any abnormality in
landing gear system indication other than
those associated with the affected main
landing gear be experienced, see paragraph
4.21.1 ALTERNATE LANDING GEAR
EXTENSION.’’
Accomplishing the actions specified in
paragraph (k) of this AD terminates the
requirements of this paragraph, and after the
replacement has been done, the AFM
limitation may be removed from the AFM.
Replacement of Uplock Assembly With New
Replacement Parts and Requirements
(g) At the later of the times specified in
paragraph (g)(1) or (g)(2) of this AD: Replace
the left and right MLG uplock assemblies, P/
N 46500–3, with new or overhauled uplock
assemblies having P/N 46500–3, –5, –7, or –9
according to a method approved by either the
Manager, New York Aircraft Certification
Office (ACO), FAA; or Transport Canada
Civil Aviation (TCCA) (or its delegated
agent). Using Tasks 32–31–21–000–801 and
32–31–21–400–801 of Chapter 32–31–21 of
Bombardier Q400 Dash 8 Aircraft
Maintenance Manual (AMM), PSM 1–84–2, is
one approved method. For any uplock
assembly having P/N 46500–3, repeat the
replacement thereafter at intervals not to
exceed 2,500 flight hours or 3,000 flight
cycles, whichever occurs earlier. For any
uplock assembly having P/N 46500–5, do the
actions required by paragraph (i) of this AD.
Replacing an uplock assembly with a new or
overhauled uplock assembly having P/N
46500–7 or –9 terminates the requirements of
this paragraph, for that uplock assembly
only.
(1) Before the accumulation of 2,500 total
flight hours or 3,000 total flight cycles on an
uplock assembly, whichever occurs earlier;
or
(2) Within 14 days after April 23, 2002.
One-Time Inspection of MLG Uplock Rollers
With Added Inspection Definition
(h) Within 30 days after April 23, 2002, do
a general visual inspection of the left and
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right MLG uplock rollers for the presence of
an inner low friction (black-colored) liner, in
accordance with the Accomplishment
Instructions of Bombardier DHC–8 Alert
Service Bulletin A84–32–15, dated February
4, 2002; and, before further flight, do the
actions required by paragraph (h)(1) or (h)(2)
of this AD.
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.’’
Corrective Actions
(1) If a low friction liner is present,
reinstall the existing uplock roller; or install
a new uplock roller, P/N 46575–1, having a
low friction liner; on the shock strut of the
MLG in accordance with the service bulletin.
(2) If a low friction liner is not present,
replace the existing uplock roller with a new
uplock roller, P/N 46575–1, having a low
friction liner, on the shock strut of the MLG
in accordance with the service bulletin. After
the effective date of this AD, if the low
friction liner is not present, replace the
uplock roller in accordance with paragraph
(i)(2) of this AD.
Note 2: Bombardier DHC–8 Alert Service
Bulletin A84–32–15, dated February 4, 2002,
references Chapter 32–11–01 of Bombardier
Q400 Dash 8 AMM, PSM 1–84–2, as an
additional source of service information for
procedures to replace an MLG uplock roller.
New Requirements of This AD
Repetitive Inspections and Replacement if
Necessary of a Certain Uplock Assembly
(i) For any MLG uplock assembly having
P/N 46500–5, do the inspections specified in
paragraphs (i)(1) and (i)(2) of this AD at the
later of the following compliance times:
Before the accumulation of 2,500 total flight
hours or 3,000 total flight cycles on the
uplock assembly, whichever occurs first; or
within 90 days after the effective date of this
AD. Repeat the inspections thereafter at
intervals not to exceed 400 flight hours or
480 flight cycles, whichever occurs first.
Replacement of an uplock assembly in
accordance with paragraph (i)(1) of this AD
terminates the repetitive inspections of
paragraphs (i)(1) and (i)(2) of this AD, for that
uplock assembly only.
(1) Do a detailed dimensional inspection of
the surface of the uplock hatch lower jaw for
the presence of a wear groove and measure
the wear groove depth to an accuracy of
0.001 inch, according to a method approved
by either the Manager, New York ACO; or
TCCA (or its delegated agent). Using Task
32–31–21–220–801 of the Bombardier Q400
Dash 8 AMM, PSM 1–84–2, is one approved
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method. If the groove depth exceeds 0.007
inch, before further flight, replace the uplock
assembly with a new or serviceable uplock
assembly, P/N 46500–7 or –9, according to a
method approved by either the Manager,
New York ACO; or TCCA (or its delegated
agent). Using Tasks 32–31–21–000–801 and
32–31–21–400–801 of Chapter 32–31–21 of
the Bombardier Q400 Dash 8 AMM, PSM 1–
84–2, is one approved method.
(2) Do a general visual inspection of the
uplock roller, P/N 46575–1, of the MLG
uplock assembly to ensure that it rotates
freely. If the uplock roller does not rotate
freely, before further flight, replace the
uplock roller with a new uplock roller, P/N
46575–1, in accordance with Bombardier
Temporary Revision (TR) 32–191 and
Bombardier TR 32–192, both dated May 29,
2006, both to Bombardier Q400 Dash 8 AMM.
(j) When the information in Bombardier TR
32–191 and Bombardier TR 32–192, both
dated May 29, 2006, is included in the AMM,
the AMM is approved as an acceptable
method of compliance for the replacement
specified in paragraph (i)(2) of this AD.
Optional Terminating Action for AFM
Revision, Repetitive Replacements, and
Repetitive Inspections
(k) Replacing the left and right MLG uplock
assemblies having P/N 46500–3 or –5 with
new or overhauled uplock assemblies having
P/N 46500–7 or –9 according to a method
approved by either the Manager, New York
Aircraft Certification Office (ACO), FAA; or
Transport Canada Civil Aviation (TCCA) (or
its delegated agent); terminates the
requirements of paragraphs (f), (g), (h), and (i)
of this AD, as applicable. Using Tasks 32–31–
21–000–801 and 32–31–21–400–801 of
Chapter 32–31–21 of Bombardier Q400 Dash
8 Aircraft Maintenance Manual (AMM), PSM
1–84–2, is one approved method. After the
replacements have been done, the AFM
limitation required by paragraph (f) of this
AD may be removed from the AFM.
Alternative Methods of Compliance (AMOCs)
(l)(1) The Manager, New York ACO, has the
authority to approve AMOCs for this AD, if
requested in accordance with the procedures
found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
(3) AMOCs approved previously in
accordance with AD 2002–08–05, are
approved as AMOCs for the corresponding
provisions of this AD.
Related Information
(m) Canadian airworthiness directive CF–
2002–13R2, dated May 19, 2005, also
addresses the subject of this AD.
Material Incorporated by Reference
(n) You must use the service information
listed in Table 1 of this AD to perform the
actions that are required by this AD, unless
the AD specifies otherwise.
TABLE 1.—MATERIAL INCORPORATED BY REFERENCE
Revision level
Bombardier DHC–8 Alert Service Bulletin A84–32–15 ..........................................................................
Bombardier Temporary Revision 32–191 to the Bombardier Q400 Dash 8 Aircraft Maintenance
Manual.
Bombardier Temporary Revision 32–192 to the Bombardier Q400 Dash 8 Aircraft Maintenance
Manual.
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Service information
Original ..................
Original ..................
February 4, 2002.
May 29, 2006.
Original ..................
May 29, 2006.
(1) The Director of the Federal Register
approved the incorporation by reference of
Bombardier Temporary Revision 32–191,
dated May 29, 2006, to the Bombardier Q400
Dash 8 Aircraft Maintenance Manual; and
Bombardier Temporary Revision 32–192,
dated May 29, 2006, to the Bombardier Q400
Dash 8 Aircraft Maintenance Manual; in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) On April 23, 2002 (67 FR 19101, April
18, 2002), the Director of the Federal Register
approved the incorporation by reference of
Bombardier DHC–8 Alert Service Bulletin
A84–32–15, dated February 4, 2002.
(3) Contact Bombardier, Inc., Bombardier
Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K 1Y5,
Canada, for a copy of this service
information. You may review copies at the
Docket Management Facility, U.S.
Department of Transportation, 400 Seventh
Street, SW., Room PL–401, Nassif Building,
Washington, DC; on the Internet at https://
dms.dot.gov; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at the NARA, call (202) 741–6030,
or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
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12:37 Jan 24, 2007
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Issued in Renton, Washington, on January
5, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–909 Filed 1–24–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25889; Directorate
Identifier 2006–NM–168–AD; Amendment
39–14902; AD 2007–02–15]
RIN 2120–AA64
Airworthiness Directives; Empresa
Brasileira de Aeronautica S.A.
(EMBRAER) Model ERJ 170 Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
EMBRAER Model ERJ 170 airplanes.
This AD requires replacement of certain
electrical bonding clamps and attaching
hardware with new or serviceable parts,
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
Date
as applicable, and other specified
action. This AD results from failure of
an electrical bonding clamp, used to
attach the electrical bonding straps to
the fuel system lines. We are issuing
this AD to prevent loss of bonding
protection in the interior of the fuel
tanks or adjacent areas that, in
combination with lightning strike, could
result in a fuel tank explosion and
consequent loss of the airplane.
DATES: This AD becomes effective
March 1, 2007.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of March 1, 2007.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Empresa Brasileira de
Aeronautica S.A. (EMBRAER), P.O. Box
343—CEP 12.225, Sao Jose dos
Campos—SP, Brazil, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Todd Thompson, Aerospace Engineer,
International Branch, ANM–116, FAA,
Transport Airplane Directorate, 1601
Lind Avenue, SW., Renton, Washington
E:\FR\FM\25JAR1.SGM
25JAR1
]]>Agencies
[Federal Register Volume 72, Number 16 (Thursday, January 25, 2007)]
[Rules and Regulations]
[Pages 3347-3350]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-909]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-26050; Directorate Identifier 2006-NM-078-AD;
Amendment 39-14890; AD 2007-02-03]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-400 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD), which applies to certain Bombardier Model DHC-8-400 series
airplanes. That AD currently requires revising the airplane flight
manual (AFM) to advise the flightcrew of appropriate procedures to
follow in the event that a main landing gear (MLG) fails to extend
following a gear-down selection. That AD also currently requires
repetitive replacement of the left and right MLG uplock assemblies with
new assemblies; and an inspection of the left and right MLG uplock
rollers for the presence of an inner low friction liner, and corrective
actions if necessary. This new AD revises the requirement for replacing
the left and right MLG uplock assemblies by allowing replacement with
alternative parts. For a certain MLG uplock assembly, this new AD
requires repetitive inspections of the uplock hatch lower jaw for the
presence of a wear groove and replacement with an improved part if
necessary. For a certain MLG uplock assembly, this new AD requires
repetitive inspections of the uplock roller to ensure that it rotates
freely and replacement with a new part if necessary. This new AD allows
optional replacement of the left and right MLG uplock assemblies with
improved parts, which ends the requirements of the AFM revision and
repetitive replacement and inspections. This new AD removes airplanes
from the applicability. This AD results from development of a
terminating action. We are issuing this AD to ensure that the
flightcrew has the procedures necessary to address failure of an MLG to
extend following a gear-down selection; and to detect and correct such
failure, which could result in a gear-up landing and possible injury to
passengers and crew.
DATES: This AD becomes effective March 1, 2007.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in the AD as of March 1, 2007.
On April 23, 2002 (67 FR 19101, April 18, 2002), the Director of
the Federal Register approved the incorporation by reference of
Bombardier DHC-8 Alert Service Bulletin A84-32-15, dated February 4,
2002.
ADDRESSES: You may examine the AD docket on the Internet at https://
dms.dot.gov or in person at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif Building,
Room PL-401, Washington, DC.
Contact Bombardier, Inc., Bombardier Regional Aircraft Division,
123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT: Ezra Sasson, Aerospace Engineer,
Systems and Flight Test Branch, ANE-172, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New
York 11590; telephone (516) 228-7320; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Examining the Docket
You may examine the airworthiness directive (AD) docket on the
Internet at https://dms.dot.gov or in person at the Docket Management
Facility office between 9 a.m. and 5 p.m., Monday through Friday,
except Federal holidays. The Docket Management Facility office
(telephone (800) 647-5227) is located on the plaza level of the Nassif
Building at the street address stated in the ADDRESSES section.
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to include an AD that supersedes AD 2002-08-05, amendment
39-12713 (67 FR 19101, April 18, 2002). The existing AD applies to
certain Bombardier Model DHC-8-400 series airplanes. That NPRM was
published in the Federal Register on October 13, 2006 (71 FR 60450).
That NPRM proposed to continue to require revising the airplane flight
manual (AFM) to advise the flightcrew of appropriate procedures to
follow in the event that a main landing gear (MLG) fails to extend
following a gear-down selection. That NPRM also proposed to continue to
require repetitive replacement of the left and right MLG uplock
assemblies with new assemblies; and an inspection of the left and right
MLG uplock rollers for the presence of an inner low friction liner, and
corrective actions if necessary. That NPRM also proposed to revise the
requirement for replacing the
[[Page 3348]]
left and right MLG uplock assemblies by allowing replacement with
alternative parts. For a certain MLG uplock assembly, that NPRM also
proposed to require repetitive inspections of the uplock hatch lower
jaw for the presence of a wear groove and replacement with an improved
part if necessary. For a certain MLG uplock assembly, that NPRM also
proposed to require repetitive inspections of the uplock roller to
ensure that it rotates freely and replacement with a new part if
necessary. That NPRM also proposed to allow optional replacement of the
left and right MLG uplock assemblies with improved parts, which would
end the requirements of the AFM revision and repetitive replacements
and inspections. That NPRM also proposed to remove airplanes from the
applicability.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the one comment that has
been received on the NPRM.
Request To Provide Additional Terminating Action
Horizon Air requests that we revise paragraph (k) of the NPRM to
provide an additional terminating action by allowing replacement with a
new or overhauled uplock assembly having part number (P/N) 46500-9.
Paragraph (k) of the NPRM proposed only to allow replacement of uplock
assemblies having P/N 46500-3 or -5 with new or overhauled uplock
assemblies having P/N 46500-7. As justification, the commenter states
that P/N 46500-9 is the latest version of the uplock assembly. The
commenter also points out that Bombardier DHC-8 Service Bulletin 84-32-
46, dated July 4, 2006, provides instructions for modifying an uplock
assembly having P/N 46500-7 and reidentifying it as P/N 46500-9.
We agree to revise paragraph (k) of this AD to provide P/N 46500-9
as a terminating action. We have also revised paragraphs (g) and (i)(1)
of this AD to allow replacement with P/N 46500-9. Bombardier DHC-8
Service Bulletin 84-32-46 modifies an uplock assembly having P/N 46500-
7 by improving retention of the proximity sensor target. Therefore, we
have determined that a new or overhauled uplock assembly having P/N
46500-9 is also adequate for addressing the unsafe condition of this
AD.
Conclusion
We have carefully reviewed the available data, including the
comment that has been received, and determined that air safety and the
public interest require adopting the AD with the changes described
previously. We have determined that these changes will neither increase
the economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
The following table provides the estimated costs, at an average
labor rate of $80 per work hour, for U.S. operators to comply with this
AD.
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Number of
Work U.S.-
Action hours Parts Cost per airplane registered Fleet cost
airplanes
----------------------------------------------------------------------------------------------------------------
AFM revision (required by AD 2002- 1 None $80................. 21 $1,680.
08-05).
Replacement of uplock assemblies 4 \1\ $0 $320, per 21 $6,720 per
(required by AD 2002-08-05). replacement cycle. replacement cycle.
Inspection of uplock rollers 1 None $80................. 21 $1,680.
(required by AD 2002-08-05).
Inspections of uplock assemblies 5 None $400................ 21 $8,400.
and uplock rollers (new action).
Terminating action (new action)... 4 \1\ $0 $320................ 21 $6,720.
----------------------------------------------------------------------------------------------------------------
\1\ The parts manufacturer states that it will supply required parts to operators at no cost.
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 have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket. See the ADDRESSES
section for a location to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
[[Page 3349]]
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-12713 (67 FR 19101, April 18, 2002) and by adding
the following new airworthiness directive (AD):
2007-02-03 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment
39-14890. Docket No. FAA-2006-26050; Directorate Identifier 2006-NM-
078-AD.
Effective Date
(a) This AD becomes effective March 1, 2007.
Affected ADs
(b) This AD supersedes AD 2002-08-05.
Applicability
(c) This AD applies to Bombardier Model DHC-8-400 series
airplanes, certificated in any category; serial numbers 4001 and
4003 through 4087 inclusive; equipped with main landing gear (MLG)
uplock assembly part numbers (P/Ns) 46500-3 and -5.
Unsafe Condition
(d) This AD results from development of a terminating action. We
are issuing this AD to ensure that the flightcrew has the procedures
necessary to address failure of an MLG to extend following a gear-
down selection; and to detect and correct such failure, which could
result in a gear-up landing and possible injury to passengers and
crew.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Requirements of AD 2002-08-05
Revision of FAA-Approved Airplane Flight Manual (AFM)
(f) Within 3 days after April 23, 2002 (the effective date of AD
2002-08-05), amend all copies of the FAA-approved Bombardier Series
400 AFM, PSM 1-84-1A (for Models 400, 401, and 402), by adding the
following procedure to the Limitations section of the AFM and
opposite page 4-21-1 of the AFM; and advise all flightcrew members
of these changes. (The revision may be accomplished by inserting a
copy of this AD into the Limitations section of the AFM and affected
paragraphs of the AFM.):
``If ONE main landing gear fails to extend after performing
landing gear extension per normal procedures given in paragraph
4.3.7 and alternate extension procedures per paragraph 4.21.1 of the
AFM:
1. Visually confirm that the affected gear has not extended and
that the associated doors have opened.
2. Ensure No. 2 hydraulic system pressure and quantity are
normal and the following landing gear advisory lights are
illuminated: selector lever amber, gear green locked down (nose and
non-affected main gear), red gear unlocked (affected main gear) and
all amber doors open.
3. NOSE L/G RELEASE handle--Return to the stowed position.
4. LANDING GEAR ALTERNATE EXTENSION door--Close fully.
5. MAIN L/G RELEASE handle--Return to the stowed position.
6. LANDING GEAR ALTERNATE RELEASE door--Close fully.
7. LANDING GEAR lever--DN.
8. L/G DOWN SELECT INHIBIT SW--Normal and guarded. Check amber
doors open advisory lights out (nose and non-affected main gear) and
LDG GEAR INOP caution light out.
9. LANDING GEAR lever--UP Check all gear, door and LANDING GEAR
lever advisory lights out.
10. With minimum delay, LANDING GEAR lever--DN. Check 3 green
gear locked down advisory lights illuminate, all amber doors open,
red gear unlocked and selector lever amber advisory lights out.
11. Items 9 and 10 may be repeated in an effort to achieve 3
gear down and locked.
CAUTION
Should the LDG GEAR INOP caution light illuminate, or loss of
no. 2 hydraulic system pressure or quantity, or any abnormality in
landing gear system indication other than those associated with the
affected main landing gear be experienced, see paragraph 4.21.1
ALTERNATE LANDING GEAR EXTENSION.''
Accomplishing the actions specified in paragraph (k) of this AD
terminates the requirements of this paragraph, and after the
replacement has been done, the AFM limitation may be removed from
the AFM.
Replacement of Uplock Assembly With New Replacement Parts and
Requirements
(g) At the later of the times specified in paragraph (g)(1) or
(g)(2) of this AD: Replace the left and right MLG uplock assemblies,
P/N 46500-3, with new or overhauled uplock assemblies having P/N
46500-3, -5, -7, or -9 according to a method approved by either the
Manager, New York Aircraft Certification Office (ACO), FAA; or
Transport Canada Civil Aviation (TCCA) (or its delegated agent).
Using Tasks 32-31-21-000-801 and 32-31-21-400-801 of Chapter 32-31-
21 of Bombardier Q400 Dash 8 Aircraft Maintenance Manual (AMM), PSM
1-84-2, is one approved method. For any uplock assembly having P/N
46500-3, repeat the replacement thereafter at intervals not to
exceed 2,500 flight hours or 3,000 flight cycles, whichever occurs
earlier. For any uplock assembly having P/N 46500-5, do the actions
required by paragraph (i) of this AD. Replacing an uplock assembly
with a new or overhauled uplock assembly having P/N 46500-7 or -9
terminates the requirements of this paragraph, for that uplock
assembly only.
(1) Before the accumulation of 2,500 total flight hours or 3,000
total flight cycles on an uplock assembly, whichever occurs earlier;
or
(2) Within 14 days after April 23, 2002.
One-Time Inspection of MLG Uplock Rollers With Added Inspection
Definition
(h) Within 30 days after April 23, 2002, do a general visual
inspection of the left and right MLG uplock rollers for the presence
of an inner low friction (black-colored) liner, in accordance with
the Accomplishment Instructions of Bombardier DHC-8 Alert Service
Bulletin A84-32-15, dated February 4, 2002; and, before further
flight, do the actions required by paragraph (h)(1) or (h)(2) of
this AD.
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.''
Corrective Actions
(1) If a low friction liner is present, reinstall the existing
uplock roller; or install a new uplock roller, P/N 46575-1, having a
low friction liner; on the shock strut of the MLG in accordance with
the service bulletin.
(2) If a low friction liner is not present, replace the existing
uplock roller with a new uplock roller, P/N 46575-1, having a low
friction liner, on the shock strut of the MLG in accordance with the
service bulletin. After the effective date of this AD, if the low
friction liner is not present, replace the uplock roller in
accordance with paragraph (i)(2) of this AD.
Note 2: Bombardier DHC-8 Alert Service Bulletin A84-32-15, dated
February 4, 2002, references Chapter 32-11-01 of Bombardier Q400
Dash 8 AMM, PSM 1-84-2, as an additional source of service
information for procedures to replace an MLG uplock roller.
New Requirements of This AD
Repetitive Inspections and Replacement if Necessary of a Certain
Uplock Assembly
(i) For any MLG uplock assembly having P/N 46500-5, do the
inspections specified in paragraphs (i)(1) and (i)(2) of this AD at
the later of the following compliance times: Before the accumulation
of 2,500 total flight hours or 3,000 total flight cycles on the
uplock assembly, whichever occurs first; or within 90 days after the
effective date of this AD. Repeat the inspections thereafter at
intervals not to exceed 400 flight hours or 480 flight cycles,
whichever occurs first. Replacement of an uplock assembly in
accordance with paragraph (i)(1) of this AD terminates the
repetitive inspections of paragraphs (i)(1) and (i)(2) of this AD,
for that uplock assembly only.
(1) Do a detailed dimensional inspection of the surface of the
uplock hatch lower jaw for the presence of a wear groove and measure
the wear groove depth to an accuracy of 0.001 inch, according to a
method approved by either the Manager, New York ACO; or TCCA (or its
delegated agent). Using Task 32-31-21-220-801 of the Bombardier Q400
Dash 8 AMM, PSM 1-84-2, is one approved
[[Page 3350]]
method. If the groove depth exceeds 0.007 inch, before further
flight, replace the uplock assembly with a new or serviceable uplock
assembly, P/N 46500-7 or -9, according to a method approved by
either the Manager, New York ACO; or TCCA (or its delegated agent).
Using Tasks 32-31-21-000-801 and 32-31-21-400-801 of Chapter 32-31-
21 of the Bombardier Q400 Dash 8 AMM, PSM 1-84-2, is one approved
method.
(2) Do a general visual inspection of the uplock roller, P/N
46575-1, of the MLG uplock assembly to ensure that it rotates
freely. If the uplock roller does not rotate freely, before further
flight, replace the uplock roller with a new uplock roller, P/N
46575-1, in accordance with Bombardier Temporary Revision (TR) 32-
191 and Bombardier TR 32-192, both dated May 29, 2006, both to
Bombardier Q400 Dash 8 AMM.
(j) When the information in Bombardier TR 32-191 and Bombardier
TR 32-192, both dated May 29, 2006, is included in the AMM, the AMM
is approved as an acceptable method of compliance for the
replacement specified in paragraph (i)(2) of this AD.
Optional Terminating Action for AFM Revision, Repetitive
Replacements, and Repetitive Inspections
(k) Replacing the left and right MLG uplock assemblies having P/
N 46500-3 or -5 with new or overhauled uplock assemblies having P/N
46500-7 or -9 according to a method approved by either the Manager,
New York Aircraft Certification Office (ACO), FAA; or Transport
Canada Civil Aviation (TCCA) (or its delegated agent); terminates
the requirements of paragraphs (f), (g), (h), and (i) of this AD, as
applicable. Using Tasks 32-31-21-000-801 and 32-31-21-400-801 of
Chapter 32-31-21 of Bombardier Q400 Dash 8 Aircraft Maintenance
Manual (AMM), PSM 1-84-2, is one approved method. After the
replacements have been done, the AFM limitation required by
paragraph (f) of this AD may be removed from the AFM.
Alternative Methods of Compliance (AMOCs)
(l)(1) The Manager, New York ACO, has the authority to approve
AMOCs for this AD, if requested in accordance with the procedures
found in 14 CFR 39.19.
(2) Before using any AMOC approved in accordance with Sec.
39.19 on any airplane to which the AMOC applies, notify the
appropriate principal inspector in the FAA Flight Standards
Certificate Holding District Office.
(3) AMOCs approved previously in accordance with AD 2002-08-05,
are approved as AMOCs for the corresponding provisions of this AD.
Related Information
(m) Canadian airworthiness directive CF-2002-13R2, dated May 19,
2005, also addresses the subject of this AD.
Material Incorporated by Reference
(n) You must use the service information listed in Table 1 of
this AD to perform the actions that are required by this AD, unless
the AD specifies otherwise.
Table 1.--Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Service information Revision level Date
----------------------------------------------------------------------------------------------------------------
Bombardier DHC-8 Alert Service Bulletin Original........................... February 4, 2002.
A84-32-15.
Bombardier Temporary Revision 32-191 to Original........................... May 29, 2006.
the Bombardier Q400 Dash 8 Aircraft
Maintenance Manual.
Bombardier Temporary Revision 32-192 to Original........................... May 29, 2006.
the Bombardier Q400 Dash 8 Aircraft
Maintenance Manual.
----------------------------------------------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of Bombardier Temporary Revision 32-191,
dated May 29, 2006, to the Bombardier Q400 Dash 8 Aircraft
Maintenance Manual; and Bombardier Temporary Revision 32-192, dated
May 29, 2006, to the Bombardier Q400 Dash 8 Aircraft Maintenance
Manual; in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
(2) On April 23, 2002 (67 FR 19101, April 18, 2002), the
Director of the Federal Register approved the incorporation by
reference of Bombardier DHC-8 Alert Service Bulletin A84-32-15,
dated February 4, 2002.
(3) Contact Bombardier, Inc., Bombardier Regional Aircraft
Division, 123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada,
for a copy of this service information. You may review copies at the
Docket Management Facility, U.S. Department of Transportation, 400
Seventh Street, SW., Room PL-401, Nassif Building, Washington, DC;
on the Internet at https://dms.dot.gov; or at the National Archives
and Records Administration (NARA). For information on the
availability of this material at the NARA, call (202) 741-6030, or
go to https://www.archives.gov/federal_register/code_of_
federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on January 5, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-909 Filed 1-24-07; 8:45 am]
BILLING CODE 4910-13-P
