[Federal Register Volume 76, Number 25 (Monday, February 7, 2011)]
[Rules and Regulations]
[Pages 6523-6525]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-2006]
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Rules and Regulations
Federal Register
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This section of the FEDERAL REGISTER contains regulatory documents
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to and codified in the Code of Federal Regulations, which is published
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Federal Register / Vol. 76, No. 25 / Monday, February 7, 2011 / Rules
and Regulations
[[Page 6523]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-1152; Directorate Identifier 2009-CE-026-AD;
Amendment 39-16589; AD 2011-03-05]
RIN 2120-AA64
Airworthiness Directives; Dornier Luftfahrt GmbH Models Dornier
228-100, Dornier 228-101, Dornier 228-200, Dornier 228-201, Dornier
228-202, and Dornier 228-212 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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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:
The TC Holder received from operators, whose fleets are operated
in demanding operating-conditions and with very frequent Short Take-
Off and Landing (STOL) operations, reports of cracks located in the
web of fuselage frame 19. On 05 February 2007, EASA issued
Airworthiness Directive (AD) 2007-0028 which mandated Alert Service
Bulletin (ASB) 228-266 and required an inspection of the frame 19 on
all Dornier 228 aeroplanes. In addition, the TC Holder also
initiated a flight-test campaign including strain measurements as
well as finite element modelling and fatigue analyses to better
understand the stress distribution onto the frame 19 and the
associated structural components.
The results of these investigations confirmed that STOL
operations diminish extensively the fatigue life of the frame 19.
Fuselage frame 19 supports the rear attachment of the Main
Landing Gear (MLG). This condition, if not corrected, could cause
rupture of frame 19, leading to subsequent collapse of a MLG.
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective March 14, 2011.
On March 14, 2011, the Director of the Federal Register approved
the incorporation by reference of Dornier 228 Time Limits/Maintenance
Checks Manual, Temporary Revision No. 05-27, dated August 4, 2008,
listed in this AD.
As of June 26, 2007 (72 FR 28591, May 22, 2007), the Director of
the Federal Register approved the incorporation by reference of RUAG
Alert Service Bulletin No. ASB-228-266, dated December 1, 2006, listed
in this AD.
ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov 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 service information identified in this AD, contact RUAG
Aerospace Services GmbH, Dornier 228 Customer Support, P.O. Box 1253,
82231 Wessling, Germany; telephone: + 49 (0) 8153-302280; fax: + 49 (0)
8153-303030. You may review copies of the referenced service
information at the FAA, Small Airplane Directorate, 901 Locust, Kansas
City, Missouri 64106. For information on the availability of this
material at the FAA, call 816-329-4148.
FOR FURTHER INFORMATION CONTACT: Greg Davison, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4130; fax: (816) 329-4090.
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 November 18, 2010
(75 FR 70623), and proposed to supersede AD 2007-11-03, Amendment 39-
15060 (72 FR 28591; May 22, 2007). That NPRM proposed to correct an
unsafe condition for the specified products. The MCAI states that:
The TC Holder received from operators, whose fleets are operated
in demanding operating-conditions and with very frequent Short Take-
Off and Landing (STOL) operations, reports of cracks located in the
web of fuselage frame 19. On 05 February 2007, EASA issued
Airworthiness Directive (AD) 2007-0028 which mandated Alert Service
Bulletin (ASB) 228-266 and required an inspection of the frame 19 on
all Dornier 228 aeroplanes. In addition, the TC Holder also
initiated a flight-test campaign including strain measurements as
well as finite element modelling and fatigue analyses to better
understand the stress distribution onto the frame 19 and the
associated structural components.
The results of these investigations confirmed that STOL
operations diminish extensively the fatigue life of the frame 19.
Fuselage frame 19 supports the rear attachment of the Main
Landing Gear (MLG). This condition, if not corrected, could cause
rupture of frame 19, leading to subsequent collapse of a MLG.
For the reasons described above, this new AD requires
installation of reinforcements and butt straps on frame 19 at the
lower part of the fuselage for aeroplanes used in operations where
this frame may be subject to high stress and recurring inspections
of that frame for all aeroplanes.
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.
[[Page 6524]]
Costs of Compliance
We estimate that this AD will affect 17 products of U.S. registry.
We also estimate that it will take about 6 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour. Required parts will cost about $0 per product.
Based on these figures, we estimate the cost of this AD to the U.S.
operators to be $8,670 or $510 per product.
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 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 http://www.regulations.gov; 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
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 39-15060 (72 FR
28591; May 22, 2007) and adding the following new AD:
2011-03-05 Dornier Luftfahrt GmbH: Amendment 39-16589; Docket No.
FAA-2010-1152; Directorate Identifier 2009-CE-026-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective March
14, 2011.
Affected ADs
(b) This AD supersedes AD 2007-11-03, Amendment 39-15060.
Applicability
(c) This AD applies to Dornier Luftfahrt GmbH Model Dornier 228-
100, Dornier 228-101, Dornier 228-200, Dornier 228-201, Dornier 228-
202, and Dornier 228-212 airplanes, all serial numbers, that are
certificated in any category.
Subject
(d) Air Transport Association of America (ATA) Code 53:
Fuselage.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
The TC Holder received from operators, whose fleets are operated
in demanding operating-conditions and with very frequent Short Take-
Off and Landing (STOL) operations, reports of cracks located in the
web of fuselage frame 19. On 05 February 2007, EASA issued
Airworthiness Directive (AD) 2007-0028 which mandated Alert Service
Bulletin (ASB) 228-266 and required an inspection of the frame 19 on
all Dornier 228 aeroplanes. In addition, the TC Holder also
initiated a flight-test campaign including strain measurements as
well as finite element modelling and fatigue analyses to better
understand the stress distribution onto the frame 19 and the
associated structural components.
The results of these investigations confirmed that STOL
operations diminish extensively the fatigue life of the frame 19.
Fuselage frame 19 supports the rear attachment of the Main
Landing Gear (MLG). This condition, if not corrected, could cause
rupture of frame 19, leading to subsequent collapse of a MLG.
For the reasons described above, this new AD requires
installation of reinforcements and butt straps on frame 19 at the
lower part of the fuselage for aeroplanes used in operations where
this frame may be subject to high stress and recurring inspections
of that frame for all aeroplanes.
Actions and Compliance
(f) Unless already done, do the following actions:
(1) For all airplanes, within 25 hours time-in-service (TIS)
after June 26, 2007 (the effective date of AD 2007-11-03), visually
inspect the affected fuselage frame 19 using the instructions in
Dornier 228 RUAG Alert Service Bulletin No. ASB-228-266, dated
December 1, 2006.
(2) If any crack is found during the inspection required in
paragraph (f)(1) of this AD, before further flight, contact RUAG
Aerospace Services GmbH, Dornier 228 Customer Support, P.O. Box
1253, 82231 Wessling, Germany; telephone: +49-(0)8153-30-2280; fax:
+49-(0)8153-30-3030; e-mail: [email protected] for
FAA-approved repair instructions and incorporate the repair on the
airplane.
(3) After accomplishment of paragraph (f)(1) or (f)(2) of this
AD, as applicable, repetitively thereafter do Structural Significant
Item (SSI) Task No. 53.37 of Structure Inspection Program of Dornier
228 Time Limits/Maintenance Checks Manual, Temporary Revision No.
05-27, dated August 4, 2008, at intervals not to exceed 2,400
landings or 72 months, whichever occurs first.
(g) If the number of landings is unknown, calculate the
compliance times of landings in this AD by using hours TIS. Multiply
the number of hours TIS by 0.8 to come up with the number of
landings. For the purpose of this AD:
(1) 800 landings equals 1,000 hours TIS; and
(2) 1,600 landings equals 2,000 hours TIS.
FAA AD Differences
Note: This AD differs from the MCAI and/or service information
as follows:
(1) The MCAI requires different compliance times for airplanes
operated in different conditions. The FAA is not able to enforce
compliance times based on airplane operations since there is no way
of determining the amount of operations in different conditions. To
ensure the unsafe condition is addressed adequately and timely, we
are requiring the inspection for all airplanes following a guideline
combining number of landings and life limits.
[[Page 6525]]
(2) The service information allows flight with known cracks
provided they do not exceed a certain limit. FAA policy does not
allow flight with cracks in primary structure. Since the fuselage is
considered primary structure, we are mandating repair before further
flight after any crack is found.
Other FAA AD Provisions
(h) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Standards 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: Greg Davison, Aerospace Engineer, FAA, Small
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4130; fax: (816) 329-4090. 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, a federal agency may not conduct or sponsor, and a person
is not required to respond to, nor shall a person be subject to a
penalty for failure to comply with a collection of information
subject to the requirements of the Paperwork Reduction Act unless
that collection of information displays a current valid OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 5 minutes per response, including the
time for reviewing instructions, completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Comments concerning the accuracy of this
burden and suggestions for reducing the burden should be directed to
the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer, AES-200.
Related Information
(i) Refer to MCAI European Aviation Safety Agency (EASA) AD No.:
2009-0085, dated April 14, 2009; RUAG Alert Service Bulletin No.
ASB-228-266, dated December 1, 2006; and Dornier 228 Time Limits/
Maintenance Checks Manual, Temporary Revision No. 05-27, dated
August 4, 2008, for related information. For service information
related to this AD, contact RUAG Aerospace Services GmbH, Dornier
228 Customer Support, P.O. Box 1253, 82231 Wessling, Germany;
telephone: + 49 (0) 8153-302280; fax: + 49 (0) 8153-303030. You may
review copies of the referenced service information at the FAA,
Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106.
For information on the availability of this material at the FAA,
call 816-329-4148.
Material Incorporated by Reference
(h) You must use RUAG Alert Service Bulletin No. ASB-228-266,
dated December 1, 2006; and Dornier 228 Time Limits/Maintenance
Checks Manual, Temporary Revision No. 05-27, dated August 4, 2008,
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 Dornier 228 Time Limits/Maintenance
Checks Manual, Temporary Revision No. 05-27, dated August 4, 2008,
under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) On June 26, 2007 (72 FR 28591, May 22, 2007), the Director
of the Federal Register previously approved the incorporation by
reference of RUAG Alert Service Bulletin No. ASB-228-266, dated
December 1, 2006.
(3) For service information identified in this AD, contact RUAG
Aerospace Services GmbH, Dornier 228 Customer Support, P.O. Box
1253, 82231 Wessling, Germany; telephone: + 49 (0) 8153-302280; fax:
+ 49 (0) 8153-303030.
(4) You may review copies of the referenced service information
at the FAA, Small Airplane Directorate, 901 Locust, Kansas City,
Missouri 64106. For information on the availability of this material
at the FAA, call 816-329-4148.
(5) You may also review copies of the service information
incorporated by reference for this AD 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: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Kansas City, Missouri, on January 25, 2011.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-2006 Filed 2-4-11; 8:45 am]
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