Document ID: FAA-2010-0701-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Fokker Services B.V. Model F.28 Mark 0100 Airplanes
Posted Date: 2010-07-27T04:00Z

[Federal Register: July 27, 2010 (Volume 75, Number 143)]
[Proposed Rules]               
[Page 43876-43878]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr27jy10-22]                         

=======================================================================
-----------------------------------------------------------------------

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).

-----------------------------------------------------------------------

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 
technicalservices.fokkerservices@stork.com; 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 jean.breed@goodrich.com; 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]
BILLING CODE 4910-13-P