[Federal Register Volume 64, Number 66 (Wednesday, April 7, 1999)]
[Rules and Regulations]
[Pages 16803-16805]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-8328]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-04-AD; Amendment 39-11109; AD 99-08-04]
RIN 2120-AA64
Airworthiness Directives; Bombardier Model DHC-8-100, -200, and -
300 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Bombardier Model DHC-8-100, -200, and -300 series
airplanes, that 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 amendment is prompted by a report that
the door lock mechanism of the flight compartment door jammed and could
not be opened using the alternate release mechanism. The actions
specified by this AD are intended to prevent failure of the alternate
release mechanism of the flight
[[Page 16804]]
compartment door, which could delay or impede the evacuation of the
flightcrew during an emergency. Such failure also could result in the
flightcrew not being able to assist passengers in the event of an
emergency.
DATES: Effective May 12, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of May 12, 1999.
ADDRESSES: The service information referenced in this AD may be
obtained from Bombardier, Inc., Bombardier Regional Aircraft Division,
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, Engine and Propeller Directorate, New York
Aircraft Certification Office, 10 Fifth Street, Third Floor, Valley
Stream, New York; or at the Office of the Federal Register, 800 North
Capitol Street, NW., suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Ezra Sasson, Aerospace Engineer,
Systems and Equipment Branch, ANE-172, FAA, New York Aircraft
Certification Office, Engine and Propeller Directorate, 10 Fifth
Street, Third Floor, Valley Stream, New York 11581; telephone (516)
256-7520; fax (516) 568-2716.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to certain Bombardier Model DHC-8-
100, -200, and -300 series airplanes was published as a supplemental
notice of proposed rulemaking (NPRM) in the Federal Register on August
5, 1998 (63 FR 41741). That action proposed to require 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.
Comments Received
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
Support for Proposed Rule
One commenter supports the proposed rule.
Request to Revise Applicability Statement
One commenter requests that the applicability statement of the
proposed AD be revised to reflect the effectivity listing specified in
Bombardier Service Bulletin S.B. 8-52-39, Revision `D,' dated February
27, 1998 (i.e., Model DHC-8 series airplanes having serial numbers 003
through 433 inclusive, except serial numbers 269, 408, and 413). The
commenter points out that paragraph (a) of the proposed AD requires
accomplishment of the modification specified in the subject service
bulletin.
The FAA does not concur with the commenter's request. The
applicability statement of the original NPRM [which was published in
the Federal Register on July 11, 1997 (62 FR 37170)] read, ``Model DHC-
8-100, -200, and -300 series airplanes having serial numbers 3 through
433 inclusive, excluding serial numbers 269, 408, and 418; certificated
in any category.'' The FAA revised the applicability of the
supplemental NPRM in consonance with the Canadian airworthiness
directive CF-96-20R2, dated July 16, 1997. This revision was made
because the supplemental NPRM was revised to add repetitive inspections
for wear of the flight compartment door hinges following accomplishment
of the required modification. These new repetitive inspections must be
accomplished on all affected airplanes having serial numbers 3 and
subsequent, regardless of whether the airplane has been modified.
Explanation of Changes Made to Supplemental NPRM
The FAA has revised the final rule to reflect the corporate name
change of de Havilland, Inc. to Bombardier, Inc.
Conclusion
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the changes described
previously. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Interim Action
This is considered to be interim action. The manufacturer has
advised the FAA that it currently is developing a modification that
will eliminate the need for the repetitive inspections for wear of the
flight compartment door hinges. Once this modification is developed,
approved, and available, the FAA may consider additional rulemaking.
Cost Impact
The FAA estimates that 133 Bombardier Model DHC-8-100, -200, and -
300 series airplanes of U.S. registry will be affected by this AD.
It will take approximately 4 work hours per airplane to accomplish
the required modification, at an average labor rate of $60 per work
hour. Required parts will be provided by the manufacturer at no cost to
operators. Based on these figures, the cost impact of the modification
required by this AD on U.S. operators is estimated to be $31,920, or
$240 per airplane.
It will take approximately 2 work hours per airplane to accomplish
the required inspection, at an average labor rate of $60 per work hour.
Based on these figures, the cost impact of the inspection required by
this AD on U.S. operators is estimated to be $15,960, or $120 per
airplane, per inspection cycle.
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.
Regulatory Impact
The regulations adopted herein will not have substantial direct
effects 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, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
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.
[[Page 16805]]
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new
airworthiness directive:
99-08-04 Bombardier, Inc. (Formerly de Havilland, Inc.): Amendment
39-11109. Docket 97-NM-04-AD.
Applicability: Model DHC-8-100, -200, and -300 series airplanes
having serial numbers 3 and subsequent; certificated in any
category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
modified, altered, or repaired in the area subject to the
requirements of this AD. For airplanes that have been modified,
altered, or repaired so that the performance of the requirements of
this AD is affected, the owner/operator must request approval for an
alternative method of compliance in accordance with paragraph (c) of
this AD. The request should include an assessment of the effect of
the modification, alteration, or repair on the unsafe condition
addressed by this AD; and, if the unsafe condition has not been
eliminated, the request should include specific proposed actions to
address it.
Compliance: Required as indicated, unless accomplished
previously.
To prevent failure of the alternate release mechanism of the
flight compartment door, which could delay or impede the evacuation
of the flightcrew and passengers during an emergency, accomplish the
following:
(a) Within 90 days after the effective date of this AD, 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.
Note 2: Modification of the flight compartment door accomplished
prior to the effective date of this AD 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; is considered acceptable for
compliance with the modification required by paragraph (a) of this
AD.
(b) Within 800 flight hours after accomplishment of the
modification required by paragraph (a) 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 `C,' dated September 1, 1997, or Revision `D,' dated
February 27, 1998.
(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.
Alternative Methods of Compliance
(c) An alternative method of compliance or adjustment of the
compliance time that provides an acceptable level of safety may be
used if approved by the Manager, New York Aircraft Certification
Office (ACO), FAA, Engine and Propeller Directorate. Operators shall
submit their requests through an appropriate FAA Principal
Maintenance Inspector, who may add comments and then send it to the
Manager, New York ACO.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the New York ACO.
Special Flight Permits
(d) 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 requirements of this AD can be accomplished.
Incorporation by Reference
(e) The actions shall be done in accordance with Bombardier
Service Bulletin S.B. 8-52-39, Revision `C,' dated September 1,
1997, and Bombardier Service Bulletin S.B. 8-52-39, Revision `D,'
dated February 27, 1998; as applicable. 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, 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, Engine and
Propeller Directorate, New York Aircraft Certification Office, 10
Fifth Street, Third Floor, Valley Stream, New York; or at the Office
of the Federal Register, 800 North Capitol Street, NW., suite 700,
Washington, DC.
Note 4: The subject of this AD is addressed in Canadian
airworthiness directive CF-96-20R2, dated July 16, 1997.
(f) This amendment becomes effective on May 12, 1999.
Issued in Renton, Washington, on March 30, 1999.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-8328 Filed 4-6-99; 8:45 am]
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