AD 2008-11-11
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Viking Air Limited | DHC-2 Mk.I | Airworthiness Directives; Viking Air Limited Model DHC-2 Series Airplanes |
| aircraft | Viking Air Limited | DHC-2 Mk.II | Airworthiness Directives; Viking Air Limited Model DHC-2 Series Airplanes |
| aircraft | Viking Air Limited | DHC-2 Mk.III | Airworthiness Directives; Viking Air Limited Model DHC-2 Series Airplanes |
Unsafe Condition
Cracks have been reported in the front spar center web of the tailplane at the pick-up bracket and at lightening holes. If not detected early and repaired, these cracks may lead to failure of the tailplane.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Replace the tailplane front spar for airplanes with previously repaired cracks using stop-drilled holes. Visually inspect the front spar web in the area of lightening holes for cracks between the pick-up brackets for airplanes with lightening holes. Incorporate Modification 2/466 (installation of tailplane front spar without lightening holes) depending on inspection results. Install longer pick-up brackets (modification 2/436) for airplanes with serial numbers 1 through 100. Install a gusset plate on the rear face at each pick-up bracket (modification 2/758) for airplanes with serial numbers 1 through 317.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 12 calendar months, 200 hours time-in-service, or 24 calendar months after December 15, 1992, depending on the specific action required.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Viking Air Limited Model DHC-2 Series Airplanes, including Models DHC-2 Mk. I, DHC-2 Mk. II, and DHC-2 Mk. III, all serial numbers, certificated in any category.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:
Document Text
Show stored source text (verify against official source)
[Federal Register Volume 73, Number 118 (Wednesday, June 18, 2008)]
[Rules and Regulations]
[Pages 34611-34613]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: E8-13478]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0393 Directorate Identifier 2008-CE-011-AD;
Amendment 39-15533; AD 2008-11-11]
RIN 2120-AA64
Airworthiness Directives; Viking Air Limited Model DHC-2 Series
Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for the products listed above. This AD results from mandatory
continuing airworthiness information (MCAI) issued by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:
Cracks have been reported in the front spar center web of the
tailplane at the pick-up bracket and at lightening holes. If not
detected early and repaired, these cracks may lead to failure of the
tailplane.
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective July 23, 2008.
On July 23, 2008, the Director of the Federal Register approved the
incorporation by reference of Viking DHC-2 Beaver Service Bulletin 2/
47, Revision E, dated January 23, 2007, listed in this AD.
As of December 15, 1992 (57 FR 53254, November 9, 1992), the
Director of the Federal Register approved the incorporation by
reference of deHavilland Technical News Sheet B55, dated August 1,
1952; and Bombardier de Havilland DHC-2 (Beaver) Service Bulletin 2/47
Revision C, revised September 4, 1992, listed in this AD.
ADDRESSES: You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> or in person at the Docket Management Facility,
U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Pong Lee, Aerospace Engineer, FAA, New
York Certification Office, 1600 Stewart Avenue, Suite 410, Westbury,
New York 11590; telephone: (516) 228-7324; fax: (516) 794-5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on April 2, 2008 (73 FR
17937), and proposed to supersede AD 92-24-02, Amendment 39-8407 (57 FR
53254, November 9, 1992). That NPRM proposed to correct an unsafe
condition for the specified products. The MCAI states:
Cracks have been reported in the front spar center web of the
tailplane at the pick-up bracket and at lightening holes. If not
detected early and repaired, these cracks may lead to failure of the
tailplane. This revision is issued to reflect the new requirement to
inspect the tailplane front spar web behind the pick-up brackets
using fluorescent penetrant inspection (FPI) instead of the visual
inspection method used previously.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD as proposed.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a NOTE within the AD.
Costs of Compliance
Based on the service information, we estimate that this AD will
affect 396 products of U.S. registry. We also estimate that it will
take about 10 work-hours per product to comply with basic requirements
of this AD. The average labor rate is $80 per work-hour.
Based on these figures, we estimate the cost of this AD to the U.S.
operators to be $316,800 or $800 per product.
In addition, we estimate that any necessary follow-on actions would
take about 48 work-hours and require parts costing $1,854, for a cost
of $5,694 per product. We have no way of determining the number of
products that may need these actions.
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
[[Page 34612]]
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 determined that this AD will not have federalism implications
under Executive Order 13132. This AD 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.
For the reasons discussed above, I certify this AD:
(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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD Docket.
Examining the AD Docket
You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a>; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains the NPRM, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Office (telephone (800) 647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 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. The FAA amends Sec. 39.13 by removing Amendment 39-8407 (57 FR
53254, November 9, 1992), and adding the following new AD:
2008-11-11 Viking Air Limited: Amendment 39-15533; Docket No. FAA-
2008-0393; Directorate Identifier 2008-CE-011-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective July 23,
2008.
Affected ADs
(b) This AD supersedes AD 92-24-02, Amendment 39-8407.
Applicability
(c) This AD applies to Models DHC-2 Mk. I, DHC-2 Mk. II, and
DHC-2 Mk. III airplanes, all serial numbers, certificated in any
category.
Subject
(d) Air Transport Association of America (ATA) Code 55:
Stabilizers.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Cracks have been reported in the front spar center web of the
tailplane at the pick-up bracket and at lightening holes. If not
detected early and repaired, these cracks may lead to failure of the
tailplane. This revision is issued to reflect the new requirement to
inspect the tailplane front spar web behind the pick-up brackets
using fluorescent penetrant inspection (FPI) instead of the visual
inspection method used previously.
Actions and Compliance
(f) Unless already done, do the following:
(1) For airplanes with cracks that have been previously repaired
with stop-drilled holes: Within the next 12 calendar months after
December 15, 1992 (the compliance date retained from AD 92-24-02),
replace the tailplane front spar following Bombardier de Havilland
DHC-2 (Beaver) Service Bulletin 2/47 Revision C, revised September
4, 1992.
(2) For airplanes with lightening holes (without modification 2/
466): Within the next 200 hours time-in-service (TIS) after December
15, 1992 (the compliance date retained from AD 92-24-02), visually
inspect the front spar web in the area of the lightening holes for
cracks between the pickup brackets.
(i) If cracks are found, before further flight, incorporate
Modification 2/466: installation of tailplane front spar without
lightening holes, following Bombardier de Havilland DHC-2 (Beaver)
Service Bulletin 2/47 Revision C, revised September 4, 1992; or
Viking DHC-2 Beaver Service Bulletin 2/47, Revision E, dated January
23, 2007.
(ii) If cracks are not found, within the next 24 calendar months
after December 15, 1992 (the compliance date retained from AD 92-24-
02), incorporate Modification 2/466: installation of tailplane front
spar without lightening holes, following Bombardier de Havilland
DHC-2 (Beaver) Service Bulletin 2/47 Revision C, revised September
4, 1992; or Viking DHC-2 Beaver Service Bulletin 2/47, Revision E,
dated January 23, 2007.
Note 1: Modification 2/466, installation of tailplane front spar
without lightening holes, is referenced in AD 92-24-02 and
Bombardier de Havilland DHC-2 (Beaver) Service Bulletin 2/47
Revision C, revised September 4, 1992; and Viking DHC-2 Beaver
Service Bulletin 2/47, Revision E, dated January 23, 2007.
Accomplishment of AD 92-24-02 or this AD incorporates modification
2/466.
(3) For the following airplanes: Within the next 24 calendar
months after December 15, 1992 (the compliance date retained from AD
92-24-02), do the following:
(i) For airplanes having serial numbers (S/Ns) 1 through 100:
Install longer pick-up brackets (modification 2/436) following
deHavilland Technical News Sheet B55, dated August 1, 1952.
Note 2: Modification 2/436 was incorporated at manufacture on
airplanes beginning with S/N 101. Other airplanes may have
incorporated this modification in the field.
(ii) For airplanes having S/N 1 through 317: Install a gusset
plate on the rear face at each of the pick-up brackets (modification
2/758) following deHavilland Technical News Sheet B55, dated August
1, 1952.
Note 3: Modification 2/758 was incorporated at manufacture on
airplanes beginning with S/N 318. Other airplanes may have
incorporated this modification in the field.
(4) For all airplanes: Within 200 hours time-in-service (TIS)
after July 23, 2008 (the effective date of this AD) and repetitively
thereafter at intervals not to exceed every 24 months, remove the
tailplane front spar pick-up brackets and do a fluorescent penetrant
inspection of the tailplane front spar web for cracks in the area of
the pick-up brackets following Appendix A of Viking DHC-2 Beaver
Service Bulletin 2/47, Revision E, dated January 23, 2007.
(5) For all airplanes: If during any of the inspections required
in paragraph (f)(4) of this AD cracks are found, before further
flight, replace the tailplane front spar following Viking DHC-2
Beaver Service Bulletin 2/47, Revision E, dated January 23, 2007.
The 24-month repetitive fluorescent penetrant inspection is still
required.
Note 4: The replacement and modifications required by this AD do
not terminate the 24-month repetitive fluorescent penetrant
inspection required by paragraph (f)(4) of this AD.
(6) For all airplanes: If any cracks are found as a result of
the inspections required by this AD, use the following contact
information to report your results: Viking Air Limited, Technical
Support, 9574 Hampden road, Sidney, British-Columbia, Canada, V8L
5V5; telephone: regional 250-656-7227, North America 1-800-0663-
8444, or international 1-800-6727-6727; fax: 250-656-0673; e-mail:
<a href="/cdn-cgi/l/email-protection#542031373c3a3d3735387a272124243b262014223d3f3d3a33353d267a373b39"><span class="__cf_email__" data-cfemail="c0b4a5a3a8aea9a3a1aceeb3b5b0b0afb2b480b6a9aba9aea7a1a9b2eea3afad">[email protected]</span></a>.
[[Page 34613]]
FAA AD Differences
Note 5: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, New
York Aircraft Certification Office, FAA, has the authority to
approve AMOCs for this AD, if requested using the procedures found
in 14 CFR 39.19. Send information to ATTN: Pong Lee, Aerospace
Engineer, FAA, New York Certification Office, 1600 Stewart Avenue,
Suite 410, Westbury, New York 11590; telephone: (516) 228-7324; fax:
(516) 794-5531. Before using any approved AMOC on any airplane to
which the AMOC applies, notify your appropriate principal inspector
(PI) in the FAA Flight Standards District Office (FSDO), or lacking
a PI, your local FSDO.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(h) Refer to Transport Canada AD CF-1991-42R1, dated March 13,
2007; and Viking DHC-2 Beaver Service Bulletin No. 2/47, Revision E,
dated January 23, 2007, for related information.
Material Incorporated by Reference
(i) You must use Bombardier de Havilland DHC-2 (Beaver) Service
Bulletin 2/47 Revision C, revised September 4, 1992; deHavilland
Technical News Sheet B55, dated August 1, 1952; and Viking DHC-2
Beaver Service Bulletin 2/47, Revision E, dated January 23, 2007, to
do the actions required by this AD, unless the AD specifies
otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of Viking DHC-2 Beaver Service Bulletin
2/47, Revision E, dated January 23, 2007, under 5 U.S.C. 552(a) and
1 CFR part 51.
(2) On December 15, 1992 (57 FR 53254, November 9, 1992), the
Director of the Federal Register previously approved the
incorporation by reference of deHavilland Technical News Sheet B55,
dated August 1, 1952; and Bombardier de Havilland DHC-2 (Beaver)
Service Bulletin 2/47 Revision C, revised September 4, 1992.
(3) For service information identified in this AD, contact
Viking Air Limited, 9574 Hampden Road, Sidney, B.C., Canada V8L 5V5
or R.W. Martin, Inc., 37552 Winchester Road, Hangar 20, Murrieta,
California 92563.
(4) You may review copies at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri
64106; 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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.
Issued in Kansas City, Missouri, on June 10, 2008.
Kim Smith,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. E8-13478 Filed 6-17-08; 8:45 am]
BILLING CODE 4910-13-P
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Retrieved: Apr 4, 2026
Rights: U.S. Government Public Domain
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