[Federal Register: July 9, 2004 (Volume 69, Number 131)]
[Rules and Regulations]
[Page 41410-41411]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr09jy04-15]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NM-234-AD; Amendment 39-13724; AD 2004-14-15]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-400 Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to certain Bombardier Model DHC-8-400 airplanes. That
AD currently requires revising the Normal and Abnormal sections of the
airplane flight manual (AFM) to include procedures that enable the
flightcrew to determine if the main landing gear (MLG) is extended
before landing, and to take appropriate actions if necessary. This
amendment adds an airplane to the applicability, and requires replacing
the existing MLG downlock proximity sensors with new, improved sensors.
After the replacement, this action also requires removing from the AFM
the revision to the Normal and Abnormal sections required by the
existing AD. The actions specified by this AD are intended to prevent
failure of the MLG downlock proximity sensors on the same MLG at the
same time, which could result in the MLG's failure to extend during
landing, and cause injury to flightcrew and passengers. This action is
intended to address the identified unsafe condition.
DATES: Effective August 13, 2004.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of August 13, 2004.
ADDRESSES: The service information referenced in this AD may be
obtained from Bombardier, Inc., Bombardier Regional Aircraft Division,
123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. This
information may be examined at the Federal Aviation Administration
(FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue,
SW., Renton, Washington; or at the FAA, New York Aircraft Certification
Office, 1600 Stewart Avenue, Westbury, New York 11590; 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: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
FOR FURTHER INFORMATION CONTACT: Dan Parrillo, Aerospace Engineer,
Systems and Flight Test Branch, ANE-172, FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, Westbury, New York 11590;
telephone (516) 228-7305; fax (516) 794-5531.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 2001-11-10,
amendment 39-12253 (66 FR 30305, June 6, 2001), which is applicable to
certain Bombardier Model DHC-8-400 series airplanes, was published in
the Federal Register on May 7, 2004 (69 FR 25503). The action proposed
to require revising the Normal and Abnormal sections of the airplane
flight manual (AFM) to include procedures that enable the flightcrew to
determine if the main landing gear (MLG) is extended before landing,
and to take appropriate actions if necessary. That action also proposed
to require adding an airplane to the applicability, and replacing the
existing MLG downlock proximity sensors with new, improved sensors.
After the replacement, that action also proposed to require removing
from the AFM the revision to the Normal and Abnormal sections required
by the existing AD.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were submitted in response
to the proposal or the FAA's determination of the cost to the public.
Conclusion
The FAA has determined that air safety and the public interest
require the adoption of the rule as proposed.
Cost Impact
There are approximately 15 airplanes of U.S. registry that will be
affected by this AD.
The revision of the AFM that is currently required by AD 2001-11-10
takes approximately 1 work hour per airplane to accomplish, at an
average labor rate of $65 per work hour. Based on these figures, the
cost impact of the previously required actions on U.S. operators is
estimated to be $975, or $65 per airplane.
The replacement that is required by this new AD will take
approximately 4 work hours per airplane to accomplish, at an average
labor rate of $65 per work hour. Required parts will be provided free
of charge. Based on these figures, the cost impact of the new
requirements of this AD on U.S. operators is estimated to be $3,900, or
$260 per airplane.
The cost impact figures discussed above are based on assumptions
that no operator has yet accomplished any of the requirements of this
AD action, and that no operator would accomplish those actions in the
future if this AD were not adopted. The cost impact figures discussed
in AD rulemaking actions represent only the time necessary to perform
the specific actions actually required by the AD. These figures
typically do not include incidental costs, such as the time required to
gain access and close up, planning time, or time necessitated by other
administrative actions.
Regulatory Impact
The regulations adopted herein 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. Therefore, it
is determined that this final rule does not have federalism
implications under Executive Order 13132.
For the reasons discussed above, I certify that this action (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. A final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from the Rules Docket at the location provided under the caption
ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, pursuant to the authority delegated to me by the
Administrator,
[[Page 41411]]
the Federal Aviation Administration amends part 39 of the Federal
Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. Section 39.13 is amended by removing amendment 39-12253 (66 FR
30305, June 6, 2001), and by adding a new airworthiness directive (AD),
amendment 39-13724, to read as follows:
2004-14-15 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment
39-13724. Docket 2002-NM-234-AD. Supersedes AD 2001-11-10, Amendment
39-12253.
Applicability: Model DHC-8-400 airplanes, serial numbers 4001
through 4055 inclusive; certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of the main landing gear (MLG) downlock
proximity sensors on the same MLG at the same time, which could
result in the MLG's failure to extend during landing, and cause
injury to flightcrew and passengers, accomplish the following:
Restatement of the Requirements of AD 2001-11-10
Airplane Flight Manual (AFM) Revision
(a) Within 14 days after June 21, 2001 (the effective date of AD
2001-11-10, amendment 39-12253), revise the Normal and Abnormal
sections of the airplane flight manual (AFM) by inserting the
following into Section 4.21, opposite page 4.21.1. This may be
accomplished by inserting a copy of this AD in the AFM.
Caution
If illumination of LEFT gear safe (green), and LEFT gear unsafe
(red), and landing gear handle (amber) advisory lights with the
landing gear handle in the up position.
Or
Illumination of RIGHT gear safe (green), and RIGHT gear unsafe
(red), and landing gear handle (amber) advisory lights with the
landing gear handle in the up position.
1. Perform an Alternate Landing Gear extension, See paragraph
4.21.
Warning
Selection of the gear down without following the Alternate
Landing Gear Extension procedure may result in the affected gear
being trapped inside the nacelle.
2. Visually inspect Main Landing Gear to confirm that it has
been extended.
Warning
A down and locked indication of the affected main landing gear
is not a valid indication of the gear position.
3. Insert hydraulic pump handle in socket and operate for a
minimum of 12 full strokes and ensure resistance to pump handle
movement.
4. Observe the LEFT gear safe (green) and RIGHT gear safe
(green) advisory lights are illuminated and the LEFT gear unsafe
(red) and RIGHT gear unsafe (red) and the landing handle (amber)
advisory lights are extinguished.''
New Requirements of This AD
Replacement
(b) Within 6 months after the effective date of this AD, replace
the left-hand and right-hand MLG downlock proximity sensors with
new, improved sensors having new part numbers, per the
Accomplishment Instructions of Bombardier Service Bulletin 84-32-09,
Revision A, dated November 20, 2001. Once the sensors have been
replaced, the AFM revision required by paragraph (a) of this AD must
be removed from the AFM.
Note 1: Bombardier Service Bulletin 84-32-09 references Menasco
Aerospace Service Bulletin 46400-32-09, dated May 15, 2001, as an
additional source of service information for accomplishment of the
replacement. The Menasco service bulletin is included in the
Bombardier service bulletin.
Replacements Accomplished per Previous Issue of Service Bulletin
(c) Replacements accomplished before the effective date of this
AD per Bombardier Service Bulletin 84-32-09, dated May 18, 2001, are
considered acceptable for compliance with the corresponding action
specified in this AD.
Alternative Methods of Compliance
(d) In accordance with 14 CFR 39.19, the Manager, New York
Aircraft Certification Office (ACO), FAA, is authorized to approve
alternative methods of compliance (AMOCs) for this AD.
Incorporation by Reference
(e) Unless otherwise specified in this AD, the actions shall be
done in accordance with Bombardier Service Bulletin 84-32-09,
Revision A, dated November 20, 2001. This incorporation by reference
was approved by the Director of the Federal Register in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from
Bombardier, Inc., Bombardier Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be
inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the FAA, New York Aircraft
Certification Office, 1600 Stewart Avenue, suite 410, Westbury, New
York; 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: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Note 2:
The subject of this AD is addressed in Canadian airworthiness
directive CF-2001-16R1, dated June 3, 2002.
Effective Date
(f) This amendment becomes effective on August 13, 2004.
Issued in Renton, Washington, on June 30, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-15509 Filed 7-8-04; 8:45 am]
BILLING CODE 4910-13-P