[Federal Register Volume 64, Number 139 (Wednesday, July 21, 1999)]
[Rules and Regulations]
[Pages 39001-39003]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-18197]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-CE-05-AD; Amendment 39-11226; AD 99-15-07]
RIN 2120-AA64
Airworthiness Directives; deHavilland Inc. Models DHC-2 Mk. I,
DHC-2 Mk. II, and DHC-2 Mk. III Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
applies to all deHavilland Inc. (deHavilland) Models DHC-2 Mk. I, DHC-2
Mk. II, and DHC-2 Mk. III airplanes. This AD requires repetitively
inspecting the rear fuselage bulkhead at Station 228 for cracks. This
AD also requires repairing any crack found or replacing any cracked
rear fuselage bulkhead in accordance with a repair or replacement
scheme obtained from the manufacturer through the Federal Aviation
Administration (FAA). This AD is the result of mandatory continuing
airworthiness information (MCAI) issued by the airworthiness authority
for Canada. The actions specified by this AD are intended to detect and
correct cracking of the rear fuselage bulkhead at Station 228, which
could result in structural damage of the fuselage to the point of
failure with consequent loss of airplane control.
DATES: Effective September 10, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of September 10, 1999.
ADDRESSES: Service information that applies to this AD may be obtained
from Bombardier Inc., Bombardier Regional Aircraft Division, Garratt
Boulevard, Downsview, Ontario, Canada M3K 1Y5; telephone: (416) 633-
7310. This information may also be examined at the Federal Aviation
Administration (FAA), Central Region, Office of the Regional Counsel,
Attention: Rules
[[Page 39002]]
Docket No. 99-CE-05-AD, Room 1558, 601 E. 12th Street, Kansas City,
Missouri 64106; or at the Office of the Federal Register, 800 North
Capitol Street, NW, suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Mr. James Delisio, Aerospace Engineer,
FAA, New York Aircraft Certification Office, 10 Fifth Street, 3rd
Floor, Valley Stream, New York 11581-1200; telephone: (516) 256-7521;
facsimile: (516) 568-2716.
SUPPLEMENTARY INFORMATION:
Events Leading to the Issuance of This AD
A proposal to amend part 39 of the Federal Aviation Regulations (14
CFR part 39) to include an AD that would apply to all deHavilland
Models DHC-2 Mk. I, DHC-2 Mk. II, and DHC-2 Mk. III airplanes was
published in the Federal Register as a notice of proposed rulemaking
(NPRM) on April 23, 1999 (64 FR 19932). The NPRM proposed to require
repetitively inspecting the rear fuselage bulkhead at Station 228 for
cracks. Accomplishment of the proposed repetitive inspections as
specified in the NPRM would be required in accordance with deHavilland
Beaver Service Bulletin 2/52, dated August 30, 1998, and deHavilland
Beaver Service Bulletin TB/60, dated August 30, 1998. The NPRM also
proposed to require repairing any crack found or replacing any cracked
rear fuselage bulkhead. Accomplishment of the proposed repair or
replacement as specified in the NPRM would be required in accordance
with a repair or replacement scheme obtained from the manufacturer
through the FAA.
The NPRM was the result of mandatory continuing airworthiness
information (MCAI) issued by the airworthiness authority for Canada.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposed rule or the FAA's determination of the cost to the public.
The FAA's Determination
After careful review of all available information related to the
subject presented above, the FAA has determined that air safety and the
public interest require the adoption of the rule as proposed except for
minor editorial corrections. The FAA has determined that these minor
corrections will not change the meaning of the AD and will not add any
additional burden upon the public than was already proposed.
Compliance Time of This AD
The compliance time of this AD is presented in both calendar time
and hours time-in-service (TIS). While cracks are generally a result of
classic fatigue (i.e., aging and cyclic operation), the FAA believes
that cracks could develop over time regardless of how often the
airplane is operated. In order to assure that rear fuselage bulkhead
cracking does not go undetected, a compliance time of specific hours
TIS and calendar time (whichever occurs first) is utilized.
Cost Impact
The FAA estimates that 350 airplanes in the U.S. registry will be
affected by this AD, that it will take approximately 1 workhour per
airplane to accomplish the initial inspection, and that the average
labor rate is approximately $60 an hour. Based on these figures, the
total cost impact of the initial inspection on U.S. operators is
estimated to be $21,000, or $60 per airplane.
These figures only take into the account the costs of the initial
inspection and do not take into account the costs of the repetitive
inspections or the cost of any repair or replacement necessary if any
rear fuselage bulkhead is found cracked. The FAA has no way of
determining the number of repetitive inspections each owner/operator
will incur over the life of his/her affected airplane or the number of
airplanes that will have a cracked rear fuselage bulkhead and need
repair or replacement.
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 copy of the final evaluation prepared for this
action is contained in the Rules Docket. A copy of it may be obtained
by contacting 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 a new airworthiness directive
(AD) to read as follows:
99-15-07 DeHavilland Inc.: Amendment 39-11226; Docket No. 99-CE-05-
AD.
Applicability: Models DHC-2 Mk. I, DHC-2 Mk. II, and DHC-2 Mk.
III airplanes, all serial numbers, 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 (d) 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 in the body of this AD, unless
already accomplished.
To detect and correct cracking of the rear fuselage bulkhead at
Station 228, which could result in structural damage of the fuselage
to the point of failure with consequent loss of airplane control,
accomplish the following:
(a) Within the next 400 hours time-in-service (TIS) after the
effective date of this AD or within the next 12 calendar months
after the effective date of this AD, whichever occurs first, and
thereafter at intervals not to exceed 2,000 hours TIS or 5 years,
whichever occurs first, inspect the rear fuselage bulkhead at
Station 228 for cracks. Inspect in accordance with the
Accomplishment Instructions section of whichever of the following
service bulletins that is applicable:
(1) For the Models DHC-2 Mk. I and DHC-2 Mk. II airplanes:
deHavilland Beaver
[[Page 39003]]
Service Bulletin 2/52, dated August 30, 1998; or
(2) For the Model DHC-2 Mk. III airplanes: deHavilland Beaver
Service Bulletin TB/60, dated August 30, 1998.
(b) If any crack(s) is/are found in the rear fuselage bulkhead
at Station 228 during any inspection required by paragraph (a) of
this AD, prior to further flight, accomplish the following:
(1) Obtain a repair or replacement scheme from the manufacturer
through the FAA, New York Aircraft Certification Office (ACO), 10
Fifth Street, 3rd Floor, Valley Stream, New York 11581-1200;
facsimile: (516) 568-2716.
(2) Incorporate this repair or replacement scheme.
(c) 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.
(d) An alternative method of compliance or adjustment of the
initial or repetitive compliance times that provides an equivalent
level of safety may be approved by the Manager, New York ACO, 10
Fifth Street, 3rd Floor, Valley Stream, New York 11581-1200. The
request shall be forwarded through an appropriate FAA Maintenance
Inspector, who may add comments and then send it to the Manager, New
York ACO.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the New York ACO.
(e) Questions or technical information related to deHavilland
Beaver Service Bulletin TB/60, dated August 30, 1998, and
deHavilland Beaver Service Bulletin 2/52, dated August 30, 1998,
should be directed to Bombardier Inc., Bombardier Regional Aircraft
Division, Garratt Boulevard, Downsview, Ontario, Canada M3K 1Y5;
telephone: (416) 633-7310. This service information may be examined
at the FAA, Central Region, Office of the Regional Counsel, Room
1558, 601 E. 12th Street, Kansas City, Missouri 64106.
(f) The inspections required by this AD shall be done in
accordance with deHavilland Beaver Service Bulletin TB/60, dated
August 30, 1998, or deHavilland Beaver Service Bulletin 2/52, dated
August 30, 1998. 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, Canada M3K 1Y5. Copies may be inspected at the FAA, Central
Region, Office of the Regional Counsel, Room 1558, 601 E. 12th
Street, Kansas City, Missouri, or at the Office of the Federal
Register, 800 North Capitol Street, NW, suite 700, Washington, DC.
Note 3: The subject of this AD is addressed in Canadian AD No.
CF-98-38, dated October 15, 1998.
(g) This amendment becomes effective on September 10, 1999.
Issued in Kansas City, Missouri, on July 12, 1999.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 99-18197 Filed 7-20-99; 8:45 am]
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