[Federal Register Volume 76, Number 3 (Wednesday, January 5, 2011)]
[Rules and Regulations]
[Pages 423-426]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-32990]
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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;
Amendment 39-16561; AD 2011-01-08]
RIN 2120-AA64
Airworthiness Directives; Fokker Services B.V. Model F.28 Mark
0100 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)
that applies to the products listed above. This 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. We are issuing this AD to require actions to
correct the unsafe condition on these products.
DATES: This AD becomes effective February 9, 2011.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of February 9,
2011.
[[Page 424]]
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
December 26, 2008 (73 FR 70261, November 20, 2008).
ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
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:
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 July 27, 2010 (75 FR
43876), and proposed to supersede AD 2008-22-14, Amendment 39-15710 (73
FR 70261, November 20, 2008). That NPRM proposed to correct an unsafe
condition for the specified products. The 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.
Any failed connection should be detected and corrected at the next
scheduled inspection.
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, 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.
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 our FAA policies. Any such differences
are highlighted in a Note within the AD.
Costs of Compliance
We estimate that this AD will affect about 4 products of U.S.
registry.
The actions that are required by AD 2008-22-14 and retained in this
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 will take about 7 work-hours per product to
comply with the new basic requirements of this AD. The average labor
rate is $85 per work-hour. Required parts will 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 this AD to the
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 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 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 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 Operations office
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 Operations office (telephone (800) 647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
[[Page 425]]
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 39-15710 (73 FR
70261, November 20, 2008) and adding the following new AD:
2011-01-08 Fokker Services B.V.: Amendment 39-16561. Docket No. FAA-
2010-0701; Directorate Identifier 2010-NM-017-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective February
9, 2011.
Affected ADs
(b) This AD supersedes AD 2008-22-14, Amendment 39-15710.
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 that
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 differences.
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: 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
(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.
Material Incorporated by Reference
(l) You must use the applicable service information contained in
Table 1 of this AD to do the actions required by this AD, unless the
AD specifies otherwise.
[[Page 426]]
Table 1--All Material Incorporated by Reference
------------------------------------------------------------------------
Document Date
------------------------------------------------------------------------
Fokker Service Bulletin SBF100-27- August 31, 2007.
091.
Fokker Service Bulletin SBF100-27- April 27, 2009.
092.
Goodrich Service Bulletin 23100-27- November 14, 2008.
29.
------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of Fokker Service Bulletin SBF100-27-092,
dated April 27, 2009; and Goodrich Service Bulletin 23100-27-29,
dated November 14, 2008; under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) The Director of the Federal Register previously approved the
incorporation by reference of Fokker Service Bulletin SBF100-27-091,
dated August 31, 2007, on December 26, 2008 (73 FR 70261, November
20, 2008).
(3) For Fokker service information identified in this 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 Goodrich service information identified
in this 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.
(4) You may review copies of the 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.
(5) You may also review copies of the service information that
is incorporated by reference 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 Renton, Washington, on December 17, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-32990 Filed 1-4-11; 8:45 am]
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