[Federal Register Volume 75, Number 143 (Tuesday, July 27, 2010)]
[Proposed Rules]
[Pages 43876-43878]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-18399]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0701; Directorate Identifier 2010-NM-017-AD]
RIN 2120-AA64
Airworthiness Directives; Fokker Services B.V. Model F.28 Mark
0100 Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above that would supersede an existing AD. This
proposed AD results from mandatory continuing airworthiness information
(MCAI) originated 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:
Two reports have been received where, during inspection of the
vertical stabilizer of F28 Mark 0100 aeroplanes, one of the bolts
that connect the horizontal stabilizer control unit actuator with
the dog-links was found broken (one on the nut side & one on the
head side). In both occasions, the bolt shaft was still present in
the connection and therefore the horizontal stabilizer function was
not affected. If a single dog-link connection fails, the complete
stabilizer load is taken up by the remaining dog-link connection. *
* *
To address and correct this unsafe condition EASA [European
Aviation Safety Agency] issued AD 2007-0287 [corresponding FAA AD
2008-22-14] that required a one-time inspection of the affected
bolts, * * * and replacement of failed bolts with serviceable parts.
EASA AD 2007-0287 also required the installation of a tie wrap
through the lower bolts of the horizontal stabilizer control unit,
to keep the bolt in place in the event of a bolt head failure.
Recent examination revealed that the bolts failed due to stress
corrosion, attributed to excessive bolt torque. Investigation of the
recently failed bolts showed that the modification as required by AD
2007-0287 is not adequate.
* * * * *
Loss of horizontal stabilizer function could result in partial loss
of control of the airplane. The proposed AD would require actions that
are intended to address the unsafe condition described in the MCAI.
DATES: We must receive comments on this proposed AD by September 10,
2010.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For the Fokker service information identified in this proposed AD,
contact Fokker Services B.V., Technical Services Dept., P.O. Box 231,
2150 AE Nieuw-Vennep, the Netherlands; telephone +31 (0)252-627-350;
fax +31 (0)252-627-211; e-mail
[email protected]; Internet http://www.myfokkerfleet.com.
For the Goodrich service information identified in this proposed
AD, contact Goodrich Corporation, Landing Gear, 1400 South Service
Road, West Oakville L6L 5Y7, Ontario, Canada; telephone 905-825-1568;
e-mail [email protected]; Internet http://www.goodrich.com/TechPubs.
You may review copies of the referenced service information at the
FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at the
FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Operations office (telephone (800) 647-5527) is
in the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1137; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2010-0701;
Directorate Identifier 2010-NM-017-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We have lengthened the 30-day comment period for proposed ADs that
address MCAI originated by aviation authorities of other countries to
provide adequate time for interested parties to submit comments. The
comment period for these proposed ADs is now typically 45 days, which
is consistent with the comment period for domestic transport ADs.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On October 9, 2008, we issued AD 2008-22-14, Amendment 39-15710 (73
FR 70261, November 20, 2008). That AD required actions intended to
address an unsafe condition on the products listed above.
Since we issued AD 2008-22-14, we have received information that
the actions required in AD 2008-22-14 are insufficient to prevent the
unsafe condition from occurring. The European Aviation Safety Agency
(EASA), which is the Technical Agent for the Member States of the
European Community, has issued EASA Airworthiness Directive 2009-0216,
dated October 7, 2009 (referred to after this as ``the MCAI''), to
correct an unsafe condition for the specified products. The MCAI
states:
[[Page 43877]]
Two reports have been received where, during inspection of the
vertical stabilizer of F28 Mark 0100 aeroplanes, one of the bolts
that connect the horizontal stabilizer control unit actuator with
the dog-links was found broken (one on the nut side & one on the
head side). In both occasions, the bolt shaft was still present in
the connection and therefore the horizontal stabilizer function was
not affected. If a single dog-link connection fails, the complete
stabilizer load is taken up by the remaining dog-link connection.
Any failed connection should be detected and corrected at the next
scheduled inspection.
To address and correct this unsafe condition EASA issued AD
2007-0287 [corresponding FAA AD 2008-22-14] that required a one-time
inspection of the affected bolts, Part Number (P/N) 23233-1, and
replacement of failed bolts with serviceable parts. EASA AD 2007-
0287 also required the installation of a tie wrap through the lower
bolts of the horizontal stabilizer control unit, to keep the bolt in
place in the event of a bolt head failure.
Recent examination revealed that the bolts failed due to stress
corrosion, attributed to excessive bolt torque. Investigation of the
recently failed bolts showed that the modification as required by AD
2007-0287 is not adequate.
To address the stress corrosion, the manufacturer of the bolt,
Goodrich, has introduced a bolt with an improved corrosion
protection, P/N 23233-3, through Service Bulletin 23100-27-29.
For the reasons described above, this EASA AD retains the
requirements of AD 2007-0287, which is superseded, and adds the
requirement to replace the affected P/N 23233-1 bolts with improved
bolts. Concurrently, the tie-wrap must be removed.
Loss of horizontal stabilizer function could result in partial loss
of control of the airplane. You may obtain further information by
examining the MCAI in the AD docket.
Relevant Service Information
Fokker Services B.V. has issued Fokker Service Bulletin SBF100-27-
092, dated April 27, 2009. Goodrich has issued Service Bulletin 23100-
27-29, dated November 14, 2008. The actions described in this service
information are intended to correct the unsafe condition identified in
the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
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 proposed 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 proposed AD.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 4 products of U.S. registry.
The actions that are required by AD 2008-22-14 and retained in this
proposed AD take about 3 work-hours per product, at an average labor
rate of $85 per work-hour. Based on these figures, the estimated cost
of the currently required actions is $255 per product.
We estimate that it would take about 7 work-hours per product to
comply with the new basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Required parts would cost about $1,550
per product. Where the service information lists required parts costs
that are covered under warranty, we have assumed that there will be no
charge for these costs. As we do not control warranty coverage for
affected parties, some parties may incur costs higher than estimated
here. Based on these figures, we estimate the cost of the proposed AD
on U.S. operators to be $8,580, or $2,145 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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the 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 proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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. The FAA amends Sec. 39.13 by removing Amendment 39-15710 (73 FR
70261, November 20, 2008) and adding the following new AD:
Fokker Services B.V.: Docket No. FAA-2010-0701; Directorate
Identifier 2010-NM-017-AD.
Comments Due Date
(a) We must receive comments by September 10, 2010.
Affected ADs
(b) This AD supersedes AD 2008-22-14, Amendment 39-15710.
[[Page 43878]]
Applicability
(c) This AD applies to Fokker Services B.V. Model F.28 Mark 0100
airplanes, certificated in any category, all serial numbers.
Subject
(d) Air Transport Association (ATA) of America Code 27: Flight
Controls.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Two reports have been received where, during inspection of the
vertical stabilizer of F28 Mark 0100 aeroplanes, one of the bolts
that connect the horizontal stabilizer control unit actuator with
the dog-links was found broken (one on the nut side & one on the
head side). In both occasions, the bolt shaft was still present in
the connection and therefore the horizontal stabilizer function was
not affected. If a single dog-link connection fails, the complete
stabilizer load is taken up by the remaining dog-link connection. *
* *
To address and correct this unsafe condition EASA [European
Aviation Safety Agency] issued AD 2007-0287 [corresponding FAA AD
2008-22-14] that required a one-time inspection of the affected
bolts, * * * and replacement of failed bolts with serviceable parts.
EASA AD 2007-0287 also required the installation of a tie wrap
through the lower bolts of the horizontal stabilizer control unit,
to keep the bolt in place in the event of a bolt head failure.
Recent examination revealed that the bolts failed due to stress
corrosion, attributed to excessive bolt torque. Investigation of the
recently failed bolts showed that the modification as required by AD
2007-0287 is not adequate.
* * * * *
Loss of horizontal stabilizer function could result in partial
loss of control of the airplane.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2008-22-14
Actions and Compliance
(g) Unless already done, within 6 months after December 26, 2008
(the effective date of AD 2008-22-14), do the following actions.
(1) Perform a one-time inspection (integrity check) for failure
of the lower bolts of the stabilizer control unit dog-links, in
accordance with the Accomplishment Instructions of Fokker Service
Bulletin SBF100-27-091, dated August 31, 2007. If a failed bolt is
found, before further flight, replace the bolt with a serviceable
bolt in accordance with the Accomplishment Instructions of the
service bulletin.
(2) Install a tie-wrap through the lower bolts of the stabilizer
control unit, in accordance with the Accomplishment Instructions of
Fokker Service Bulletin SBF100-27-091, dated August 31, 2007.
New Requirements of This AD: Actions
(h) Within 30 months after the effective date of this AD, do the
actions specified in paragraphs (h)(1) and (h)(2) of this AD
concurrently. Accomplishing the actions of both paragraphs (h)(1)
and (h)(2) of this AD terminates the actions required by paragraph
(g) of this AD.
(1) Remove the tie-wrap, P/N MS3367-2-9, from the lower bolts of
the horizontal stabilizer control unit, in accordance with the
Accomplishment Instructions of Fokker Service Bulletin SBF100-27-
092, dated April 27, 2009.
(2) Remove the lower bolts, P/N 23233-1, of the horizontal
stabilizer control unit and install bolts, P/N 23233-3, in
accordance with the Accomplishment Instructions of Goodrich Service
Bulletin 23100-27-29, dated November 14, 2008.
(i) After accomplishing the requirements of paragraph (h) of
this AD, do not install a bolt having P/N 23233-1 or a tie-wrap
having P/N MS3367-2-9.
FAA AD Differences
Note 1: This AD differs from the MCAI and/or service information
as follows: No difference.
Other FAA AD Provisions
(j) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, 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: Tom
Rodriguez, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 227-1137; fax (425) 227-1149.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your principal maintenance inspector (PMI) or
principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
(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
(k) Refer to MCAI EASA Airworthiness Directive 2009-0216, dated
October 7, 2009; Fokker Service Bulletin SBF100-27-091, dated August
31, 2007; Fokker Service Bulletin SBF100-27-092, dated April 27,
2009; and Goodrich Service Bulletin 23100-27-29, dated November 14,
2008; for related information.
Issued in Renton, Washington, on July 21, 2010.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-18399 Filed 7-26-10; 8:45 am]
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