[Federal Register: September 26, 2006 (Volume 71, Number 186)]
[Proposed Rules]
[Page 56070-56072]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr26se06-20]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25904; Directorate Identifier 2006-NM-077-AD]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-100, -200, and -
300 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) that applies to certain Bombardier Model DHC-8-100, -
200, and -300 series airplanes. The existing AD currently requires
modification of the flight compartment door; repetitive inspections for
wear of the flight compartment door hinges following modification; and
repair or replacement of the hinges with new hinges if necessary. This
proposed AD would require using revised procedures for modifying and
inspecting the flight compartment door and would reduce the
applicability of the existing AD. This proposed AD results from a
determination that certain cockpit doors are no longer subject to the
existing requirements. We are proposing this AD to prevent failure of
the alternate release mechanism of the flight compartment door, which
could delay or impede the evacuation of the flightcrew during an
emergency. This failure also could result in the flightcrew not being
able to assist passengers in the event of an emergency.
DATES: We must receive comments on this proposed AD by October 26,
2006.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed AD.
DOT Docket Web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590.
Fax: (202) 493-2251.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Contact Bombardier, Inc., Bombardier Regional Aircraft Division,
123 Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada, for service
information identified in this proposed 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:
Comments Invited
We invite you to submit any relevant written data, views, or
arguments regarding this proposed AD. Send your comments to an address
listed in the ADDRESSES section. Include the docket number ``Docket No.
FAA-2006-25904; Directorate Identifier 2006-NM-077-AD'' at the
beginning of your comments. We specifically invite comments on the
overall regulatory, economic, environmental, and energy aspects of the
proposed AD. We will consider all comments received by the closing date
and may amend the proposed AD in light of those comments.
We will post all comments we receive, without change, to http://dms.dot.gov
, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this proposed AD. Using the search function of
that Web site, anyone can find and read the comments in any of our
dockets, including the name of the individual who sent the comment (or
signed the comment on behalf of an association, business, labor union,
etc.). You may review the DOT's complete Privacy Act Statement in the
Federal Register published on April 11, 2000 (65 FR 19477-78), or you
may visit http://dms.dot.gov.
Examining the Docket
You may examine the AD docket on the Internet at http://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 DOT
street address stated in the ADDRESSES section. Comments will be
available in the AD docket shortly after the Docket Management System
receives them.
Discussion
On March 30, 1999, we issued AD 99-08-04, amendment 39-11109 (64 FR
16803, April 7, 1999), for certain Bombardier Model DHC-8-100, -200,
and -300 series airplanes. That AD requires modification of the flight
compartment door; repetitive inspections for wear of the flight
compartment door hinges following modification; and repair or
replacement of the hinges with new hinges, if necessary. That AD
resulted from a report that the door lock mechanism of the flight
compartment door jammed and could not be opened using the alternate
release mechanism. We issued that AD to prevent failure of the
alternate release mechanism of the flight compartment door, which could
delay or impede the evacuation of the flightcrew during an emergency.
This failure also could result in the flightcrew not being able to
assist passengers in the event of an emergency.
Actions Since Existing AD Was Issued
Since we issued AD 99-08-04, various civil aviation authorities
have mandated the installation of reinforced flight compartment doors,
which negates the need for the modification required by paragraph (a)
of the existing AD (Modification 8/2337) for airplanes on which the
doors were installed in production. Modifications 8/2228, 8/2229, 8/
2231, 8/2232, 8Q100859, 8Q900267, 8Q420101, 8Q420143, 8Q200131, or
8Q420440 are equivalent to Modification 8/2337 (specified in paragraph
(a) of the existing AD) for the flight compartment door alternate
release mechanism. In addition, Bombardier has issued revised
procedures for modifying and inspecting the flight compartment door.
Relevant Service Information
Bombardier has issued Service Bulletin 8-52-39, Revision ``H,''
dated September 9, 2004. Revision ``H'' is similar to Revision ``D,''
dated February 27, 1998, which was cited in the existing AD as the
appropriate source of service information for accomplishing the
required actions. Among other things, Revision ``H'' revises the
procedures used for modifying and inspecting the flight compartment
door,
[[Page 56071]]
as specified in the original issue of Bombardier Service Bulletin 8-52-
39, dated October 31, 1996, and Revision ``A,'' of the service
bulletin. In addition, the effectivity specified in Revision ``H''
excludes airplanes on which new, improved flight compartment doors have
been installed in production.
Transport Canada Civil Aviation (TCCA), which is the airworthiness
authority for Canada, mandated the service information and issued
Canadian airworthiness directive CF-1996-20R4, dated August 10, 2005,
to ensure the continued airworthiness of these airplanes in Canada.
FAA's Determination and Requirements of the Proposed AD
These airplane models are manufactured in Canada and are type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Pursuant to this
bilateral airworthiness agreement, TCCA has kept the FAA informed of
the situation described above. We have examined TCCA's findings,
evaluated all pertinent information, and determined that AD action is
necessary for airplanes of this type design that are certificated for
operation in the United States.
This proposed AD would supersede AD 99-08-04 and would retain the
requirements of the existing AD, but would require using revised
procedures. This proposed AD would also reduce the applicability of the
existing AD.
Operators should note that Note 2 of AD 99-08-04 provides credit
for modification of the flight compartment door in accordance with
Bombardier Service Bulletin S.B. 8-52-39, dated August 30, 1996;
Revision ``A,'' dated October 31, 1996; Revision ``B,'' dated July 4,
1997; or Revision ``C,'' dated September 1, 1997; if the modification
is done before the effective date of AD 99-08-04. However, we have
determined that the modification and inspection procedures specified in
the original issue and Revision ``A,'' of the service bulletin are not
adequate due to a design deficiency detected after issuance of those
service bulletins. TCCA agrees with this finding.
Accordingly, we have re-identified Note 2 of the existing AD as
paragraph (i) of this proposed AD for formatting reasons. In addition,
we have revised the content of the new paragraph (i) to remove
references to the original issue and Revision ``A'' of the service
bulletin, and to provide credit for accomplishing the actions in
Revision ``E,'' dated May 10, 1999; Revision ``F,'' dated February 4,
2000; or Revision G, dated May 17, 2001.
Clarification of Alternative Method of Compliance (AMOC) Paragraph
We have revised this action to clarify the appropriate procedure
for notifying the principal inspector before using any approved AMOC on
any airplane to which the AMOC applies.
Change to Existing AD
This proposed AD would retain the requirements of AD 99-08-04.
Since AD 99-08-04 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
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Corresponding requirement
Requirement in AD 99-08-04 in this proposed AD
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paragraph (a)............................. paragraph (f).
paragraph (b)............................. paragraph (h).
paragraph (c)............................. paragraph (j).
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Costs of Compliance
This proposed AD would affect about 167 airplanes of U.S. registry.
The new actions of this proposed AD add no additional economic burden.
The current costs for this AD are repeated for the convenience of
affected operators, as follows:
The modification takes about 4 work hours per airplane, at an
average labor rate of $80 per work hour. The manufacturer states that
it will supply required parts to the operators at no cost. Based on
these figures, the estimated cost of the modification is $53,440, or
$320 per airplane.
The inspection takes about 2 work hours per airplane, at an average
labor rate of $80 per work hour. Based on these figures, the estimated
cost of the inspection is $26,720, or $160 per airplane, per inspection
cycle.
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 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 that the 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. 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, 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 Federal Aviation Administration (FAA) amends Sec. 39.13 by
removing amendment 39-11109 (64 FR 16803, April 7, 1999) and adding the
following new airworthiness directive (AD):
Bombardier, Inc. (Formerly de Havilland, Inc.): Docket No. FAA-2006-
25904; Directorate Identifier 2006-NM-077-AD.
[[Page 56072]]
Comments Due Date
(a) The FAA must receive comments on this AD action by October
26, 2006.
Affected ADs
(b) This AD supersedes AD 99-08-04.
Applicability
(c) This AD applies to Bombardier Model DHC-8-100, -200 and -300
series airplanes, certificated in any category; equipped with a
flight compartment door installation having part number (P/N)
82510074-(*), 82510294-(*), 82510310-001, 8Z4597-001, H85250010-(*),
82510700-(*), or 82510704-(*); except P/Ns 82510704-502 and
82510704-503.
Note 1: (*) denotes all dash numbers.
Unsafe Condition
(d) This AD results from a determination that certain cockpit
doors are no longer subject to the existing requirements. We are
issuing this AD to prevent failure of the alternate release
mechanism of the flight compartment door, which could delay or
impede the evacuation of the flightcrew during an emergency. This
failure also could result in the flightcrew not being able to assist
passengers in the event of an emergency.
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.
Modification
(f) Except as required by paragraph (g) of this AD: Within 90
days after May 12, 1999 (the effective date of AD 99-08-04), modify
the lower hinge assembly and main door latch (Modification 8/2337)
of the flight compartment door, in accordance with Bombardier
Service Bulletin S.B. 8-52-39, Revision ``D,'' dated February 27,
1998; or Revision ``H,'' dated September 9, 2004. After the
effective date of this AD, only Revision ``H'' may be used for
accomplishing the modification.
(g) For airplanes on which the modification required by
paragraph (f) of this AD was done before the effective date of this
AD in accordance with Bombardier Service Bulletin S.B. 8-52-39,
dated August 30, 1996; or Revision ``A,'' dated October 31, 1996:
Within 90 days after the effective date of this AD, do the
modification required by paragraph (f) of this AD in accordance with
Bombardier Service Bulletin 8-52-39, Revision ``H,'' dated September
9, 2004.
Inspection
(h) Within 800 flight hours after doing the modification
required by paragraph (g) of this AD: Inspect the hinge areas around
the hinge pin holes of the flight compartment door for wear in
accordance with Bombardier Service Bulletin S.B. 8-52-39, Revision
``D,'' dated February 27, 1998; or Revision ``H,'' dated September
9, 2004. After the effective date of this AD, only Revision ``H''
may be used for accomplishing the inspection.
(1) If no wear is detected, or if the wear is less than or equal
to 0.020 inch in depth, repeat the inspection thereafter at
intervals not to exceed 800 flight hours.
(2) If any wear is detected and its dimension around the hinge
pin holes is less than 0.050 inch and greater than 0.020 inch in
depth, prior to further flight, perform the applicable corrective
actions specified in the service bulletin. Repeat the inspection
thereafter at intervals not to exceed 800 flight hours.
(3) If any wear is detected and its dimension around the hinge
pin holes is greater than or equal to 0.050 inch in depth, prior to
further flight, replace the worn hinges with new hinges in
accordance with the service bulletin. Repeat the inspection
thereafter at intervals not to exceed 800 flight hours.
Credit for Actions Accomplished Previously
(i) Modifications and inspections done before the effective date
of this AD in accordance with Bombardier Service Bulletin S.B. 8-52-
39, Revision ``B,'' dated July 4, 1997; Revision ``C,'' dated
September 1, 1997; Revision ``E,'' dated May 10, 1999; Revision
``F,'' dated February 4, 2000; or Revision G, dated May 17, 2001;
are considered acceptable for compliance with the modification and
inspections required by this AD.
Alternative Methods of Compliance (AMOCs)
(j)(1) The Manager, New York Aircraft Certification Office, FAA,
has the authority to approve AMOCs for this AD, if requested in
accordance with the procedures found in 14 CFR 39.19.
(2) AMOCs approved previously in accordance with AD 99-08-04 are
approved as AMOCs for the corresponding provisions of paragraphs
(f), (g), (h), and (i) of this AD.
(3) 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.
Related Information
(k) Canadian airworthiness directive CF-1996-20R4, dated August
10, 2005, also addresses the subject of this AD.
Issued in Renton, Washington, on September 15, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 06-8233 Filed 9-25-06; 8:45 am]
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