[Federal Register Volume 61, Number 225 (Wednesday, November 20, 1996)]
[Rules and Regulations]
[Pages 58983-58985]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-29416]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-163-AD; Amendment 39-9822; AD 96-23-17]
RIN 2120-AA64
Airworthiness Directives; de Havilland Model DHC-8-102 and-103
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 de Havilland Model DHC-8-102 and -103 series
airplanes, that requires repetitive external inspections to detect
cracks in the skin exterior of the fuselage at floor level, and repair,
if necessary. This amendment also requires repetitive internal
inspections to detect cracks of the subject area, which terminates the
repetitive external inspections. This amendment is prompted by a report
that one of the tasks in the Maintenance Program Airworthiness
Limitations List inadvertently excluded certain airplanes from the
instructions for the
[[Page 58984]]
inspections. The actions specified by this AD are intended to prevent
undetected cracking of the frames and skin panels of the fuselage,
which could result in reduced structural integrity of the airplane.
DATES: Effective December 26, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 26, 1996.
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, New York Aircraft Certification Office,
Engine and Propeller Directorate, 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: Jon Hjelm, 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) 256-7523; 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 de Havilland Model DHC-8-
102 and-103 series airplanes was published in the Federal Register on
August 30, 1996 (61 FR 45914). That action proposed to require
repetitive external detailed visual inspections to detect cracks in the
left-and right-hand skin exterior of the fuselage at the floor level.
That action also proposed to require repetitive internal visual
inspections to detect cracks of the fuselage frames; initiation of
these inspections would constitute terminating action for the
repetitive external inspection requirements.
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
The FAA estimates that 80 de Havilland Model DHC-8-102 and-103
series airplanes of U.S. registry will be affected by this AD.
The required external inspections will take approximately 1 work
hour per airplane to accomplish, at an average labor rate of $60 per
work hour. Based on these figures, the cost impact of the AD on U.S.
operators is estimated to be $4,800, or $60 per airplane, per
inspection.
The required internal inspections will take approximately 3 work
hours per airplane to accomplish, at an average labor rate of $60 per
work hour. Based on these figures, the cost impact of the AD on U.S.
operators is estimated to be $14,400, or $180 per airplane, per
inspection.
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.
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:
96-23-17 De Havilland, Inc.: Amendment 39-9822. Docket 95-NM-163-AD.
Applicability: Model DHC-8-102 and -103 series airplanes having
serial numbers 101 through 180, inclusive; on which de Havilland
Modification 8/0427 has been installed, and on which Maintenance
Program Manual PSM 1-8-7, Task 5310/30C (Section 3-53, page 12,
dated August 10,1993) has not been accomplished; certificated in any
category.
Note 1: This AD applies to each airplane identified in the
preceding applicability provision, regardless of whether it has been
otherwise 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 undetected cracking of the frames and skin panels of
the fuselage, which could result in reduced structural integrity of
the airplane, accomplish the following:
(a) Prior to the accumulation of 15,343 total flight cycles, or
within 200 landings after the effective date of this AD, whichever
occurs later, perform an external detailed visual inspection to
detect cracks in the left-and right-hand skin exterior of the
fuselage at floor level, in accordance with paragraph III, External
Inspection, of the Accomplishment Instructions of de Havilland
Service Bulletin S.B. 8-53-48, dated August 26, 1994.
(1) If no crack is detected, repeat the external detailed visual
inspection thereafter at intervals not to exceed 750 landings.
(2) If any crack is detected, prior to further flight, perform
an internal visual inspection to detect cracks of the fuselage
frames in accordance with the service bulletin. Accomplishment of
this internal visual inspection constitutes terminating action for
the repetitive external detailed visual inspections required by of
paragraph (a)(1) of this AD.
(i) If no crack is detected during the internal inspection,
prior to further flight, repair the cracked area(s) found during the
[[Page 58985]]
external inspection, in accordance with the de Havilland DHC-8
Structural Repair Manual; or in accordance with a method approved by
Transport Canada; or in accordance with a method approved by the
Manager, New York Aircraft Certification Office (ACO), FAA, Engine
and Propeller Directorate. Repeat the internal inspection thereafter
at intervals specified in accordance with the Dash 8 Maintenance
Program Manual.
(ii) If any crack is detected during the internal inspection,
prior to further flight, repair all cracks found during both the
external and internal inspections, in accordance with the de
Havilland DHC-8 Structural Repair Manual, or in accordance with a
method approved by Transport Canada Aviation; or in accordance with
a method approved by the Manager, New York ACO, FAA, Engine and
Propeller Directorate. Repeat the internal inspection thereafter at
intervals specified in accordance with the Dash 8 Maintenance
Program Manual.
(b) Prior to the accumulation of 31,000 flight cycles, or within
12 months after the effective date of this AD, whichever occurs
later, perform an internal visual inspection to detect cracking of
the fuselage frames, in accordance with de Havilland Service
Bulletin S.B. 8-53-48, dated August 26, 1994. Accomplishment of the
internal visual inspection constitutes terminating action for the
repetitive external detailed visual inspections required by
paragraph (a)(1) of this AD.
(1) If no cracking is detected during the internal inspection,
repeat the internal inspection thereafter at intervals specified in
accordance with the Dash 8 Maintenance Program Manual.
(2) If any cracking is detected during the internal inspection,
prior to further flight, repair it in accordance with the de
Havilland DHC-8 Structural Repair Manual, or in accordance with a
method approved by Transport Canada Aviation; or in accordance with
a method approved by the Manager, New York ACO, FAA, Engine and
Propeller Directorate. Repeat the internal inspection thereafter at
intervals specified in accordance with the Dash 8 Maintenance
Program Manual.
(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.
(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.
(e) The inspections shall be done in accordance with de
Havilland Service Bulletin S.B. 8-53-48, dated August 26, 1994. 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, New York Aircraft Certification Office, Engine and
Propeller Directorate, 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.
(f) This amendment becomes effective on December 26, 1996.
Issued in Renton, Washington, on November 8, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-29416 Filed 11-19-96; 8:45 am]
BILLING CODE 4910-13-U
