[Federal Register Volume 75, Number 9 (Thursday, January 14, 2010)]
[Rules and Regulations]
[Pages 2055-2057]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-102]



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Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 
Prices of new books are listed in the first FEDERAL REGISTER issue of each 
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Federal Register / Vol. 75, No. 9 / Thursday, January 14, 2010 / 
Rules and Regulations

[[Page 2055]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0763; Directorate Identifier 2007-NM-301-AD; 
Amendment 39-16170; AD 2010-01-11]
RIN 2120-AA64


Airworthiness Directives; Fokker Services B.V. Model F.28 Mark 
0070 and 0100 Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for 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:

    Excessive wear and tear of the backlash remover mechanism has 
been found several times on Goodrich Part Number (P/N) 23400-3B and 
P/N 23400-7 elevator booster control units (BCU), while corrosion 
has been found on some components in other BCU. The wear and tear 
may result in a (partly) blocked operation of the elevator system in 
the normal (hydraulic) mode, while any corrosion may result in 
deteriorated elevator control when the BCU is in MANUAL mode.
* * * * *
The unsafe condition is wear and tear, and corrosion of the backlash 
remover mechanism, which can cause a (partly) blocked operation of the 
elevator system in the normal (hydraulic) mode and deteriorated 
elevator control when the BCU is in MANUAL mode, which could result in 
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 18, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of February 18, 
2010.

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 September 1, 2009 
(74 FR 45139). That NPRM proposed to correct an unsafe condition for 
the specified products. The MCAI states:

    Excessive wear and tear of the backlash remover mechanism has 
been found several times on Goodrich Part Number (P/N) 23400-3B and 
P/N 23400-7 elevator booster control units (BCU), while corrosion 
has been found on some components in other BCU. The wear and tear 
may result in a (partly) blocked operation of the elevator system in 
the normal (hydraulic) mode, while any corrosion may result in 
deteriorated elevator control when the BCU is in MANUAL mode.
    Fokker Services and Goodrich determined that modification of the 
affected elevator BCU in accordance with Goodrich Component Service 
Bulletin (CSB) 23400-27-27 would correct this situation. * * *
    [I]t has been decided to require the inspection of aircraft 
fitted with BCU P/N 23400-3 and P/N 23400-5 (serial numbers MC-001 
through MC-288) and the modification of these units in accordance 
with Goodrich CSB 23400-27-15 (P/N change from 23400-3 to 23400-3B, 
or from 23400-5 to 23400-7, as applicable).
    Previously, CAA-Netherlands AD (BLA) 93-051/3 dated 29 April 
1994 [which corresponds to FAA AD 97-03-09] was issued, which 
requires a periodic inspection of P/N 23400-3 and P/N 23400-5 
elevator BCU that could be affected by corrosion, and allows 
modification of the BCU in accordance with Fokker Service Bulletin 
SBF100-27-061 (application of Goodrich CSB 23400-27-15) as 
(optional) terminating action for these inspections.
    * * * In addition, this AD requires the eventual replacement of 
all affected elevator BCU with modified units.
    This new AD does not cancel the repetitive inspection 
requirements of CAA-NL AD (BLA) 93-051/3 for BCU P/N 23400-3 and P/N 
23400-5 as long as these remain installed on any in-service 
aircraft.

The unsafe condition is wear and tear, and corrosion of the backlash 
remover mechanism, which can cause a (partly) blocked operation of the 
elevator system in the normal (hydraulic) mode and deteriorated 
elevator control when the BCU is in MANUAL mode, which could result in 
loss of control of the airplane. The required actions include 
inspecting the backlash remover of the elevator booster control unit to 
determine the displacement of the pivot bolt; and if necessary, 
replacing the elevator booster control unit. Depending on the 
measurement of the displacement, the compliance time for replacement 
ranges from before further flight to 3,000 flight cycles.
    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.

Explanation of Changes Made to This AD

    We have revised this AD to identify the legal name of the 
manufacturer as published in the most recent type certificate data 
sheet for the affected airplane models.

Conclusion

    We reviewed the available data, and determined that air safety and 
the public interest require adopting the AD with the changes described 
previously. We determined that these changes will not increase the 
economic burden on any operator or increase the scope of the AD.

[[Page 2056]]

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 2 products of U.S. registry. 
We also estimate that it will take about 13 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $80 per work-hour. Required parts will cost about $189 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 parts. 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 $2,458, or $1,229 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.

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 adding the following new AD:

2010-01-11 Fokker Services B.V.: Amendment 39-16170. Docket No. FAA-
2009-0763; Directorate Identifier 2007-NM-301-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective February 
18, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Fokker Services B.V. Model F.28 Mark 0070 
and Mark 0100 airplanes, all serial numbers, certificated in any 
category.

Subject

    (d) Air Transport Association (ATA) of America Code 27: Flight 
Controls.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    Excessive wear and tear of the backlash remover mechanism has 
been found several times on Goodrich Part Number (P/N) 23400-3B and 
P[sol]N 23400-7 elevator booster control units (BCU), while 
corrosion has been found on some components in other BCU. The wear 
and tear may result in a (partly) blocked operation of the elevator 
system in the normal (hydraulic) mode, while any corrosion may 
result in deteriorated elevator control when the BCU is in MANUAL 
mode.
    Fokker Services and Goodrich determined that modification of the 
affected elevator BCU in accordance with Goodrich Component Service 
Bulletin (CSB) 23400-27-27 would correct this situation. * * *
    [I]t has been decided to require the inspection of aircraft 
fitted with BCU P/N 23400-3 and P/N 23400-5 (serial numbers MC-001 
through MC-288) and the modification of these units in accordance 
with Goodrich CSB 23400-27-15 (P/N change from 23400-3 to 23400-3B, 
or from 23400-5 to 23400-7, as applicable).
    Previously, CAA-Netherlands AD (BLA) 93-051/3 dated 29 April 
1994 [which corresponds to FAA AD 97-03-09] was issued, which 
requires a periodic inspection of P/N 23400-3 and P/N 23400-5 
elevator BCU that could be affected by corrosion, and allows 
modification of the BCU in accordance with Fokker Service Bulletin 
SBF100-27-061 (application of Goodrich CSB 23400-27-15) as 
(optional) terminating action for these inspections.
    * * * In addition, this AD requires the eventual replacement of 
all affected elevator BCU with modified units.
    This new AD does not cancel the repetitive inspection 
requirements of CAA-NL AD (BLA) 93-051/3 for BCU P/N 23400-3 and P/N 
23400-5 as long as these remain installed on any in-service 
aircraft.

The unsafe condition is wear and tear, and corrosion of the backlash 
remover mechanism, which can cause a (partly) blocked operation of 
the elevator system in the normal (hydraulic) mode and deteriorated 
elevator control when the BCU is in MANUAL mode, which could result 
in loss of control of the airplane. The required actions include 
inspecting the backlash remover of the elevator booster control unit 
to determine the displacement of the pivot bolt; and if necessary, 
replacing the elevator booster control unit. Depending on the 
measurement of the displacement, the compliance time for replacement 
ranges from before further flight to 3,000 flight cycles.

Actions and Compliance

    (f) Unless already done, do the following actions.

[[Page 2057]]

    (1) For airplanes equipped with booster control unit P/N 23400-
3B, 23400-7, 23400-3, or 23400-5, within 12 months after the 
effective date of this AD, perform a one-time inspection of the 
elevator booster control unit in accordance with Part 1 of the 
Accomplishment Instructions of Fokker Service Bulletin SBF100-27-
088, dated June 4, 2007.
    (2) At the time specified in Table 1 of this AD, and depending 
on the result of the inspection required by paragraph (f)(1) of this 
AD, replace the elevator booster control unit with a modified unit 
having P/N 23400-3B or P/N 23400-7, in accordance with Part 2 of the 
Accomplishment Instructions of Fokker Service Bulletin SBF100-27-
088, dated June 4, 2007. The replacement part must be modified in 
accordance with Goodrich Service Bulletin 23400-27-27, Revision 1, 
dated September 14, 2007.

                     Table 1--Replacement Parameters
------------------------------------------------------------------------
                Dimension A                        Replace within
------------------------------------------------------------------------
A < 0.12 millimeters (mm).................  Not applicable.
0.12 mm <= A < 0.5 mm.....................  3,000 flight cycles.
0.5 mm <= A < 1.0 mm......................  2,000 flight cycles.
1.0 mm <= A < 1.5 mm......................  1,000 flight cycles.
1.5 mm <= A < 2.0 mm......................  500 flight cycles.
2.0 mm <= A < 2.5 mm......................  125 flight cycles.
A >= 2.5 mm...............................  Before further flight.
------------------------------------------------------------------------

     (3) Within 60 months after the effective date of this AD, 
replace all remaining unmodified elevator booster control units 
having P/N 23400-3B or P/N 23400-7 with modified units, in 
accordance with Part 2 of the Accomplishment Instructions of Fokker 
Service Bulletin SBF100-27-088, dated June 4, 2007. The replacement 
part must be modified in accordance with Goodrich Service Bulletin 
23400-27-27, Revision 1, dated September 14, 2007.
    (4) Within 60 months after the effective date of this AD, 
replace all remaining elevator booster control units having P/N 
23400-3 or P/N 23400-5 with modified units having P/N 23400-3B or P/
N 23400-7, in accordance with Part 2 of the Accomplishment 
Instructions of Fokker Service Bulletin SBF100-27-088, dated June 4, 
2007. The replacement part must be modified in accordance with 
Goodrich Service Bulletin 23400-27-27, Revision 1, dated September 
14, 2007.
    (5) As of 12 months after the effective date of this AD, no 
person may install a Goodrich P/N 23400-3B, P/N 23400-7, P/N 23400-3 
or P/N 23400-5 elevator booster control unit on any airplane, unless 
the conditions of paragraph (f)(5)(i) or (f)(5)(ii), as applicable, 
are met.
    (i) The unit has been inspected in accordance with paragraph 
(f)(1) of this AD, and the applicable action(s) required by 
paragraph (f)(2) is accomplished at the time specified in that 
paragraph.
    (ii) The unit having P/N 23400-3B or P/N 23400-7 has been 
modified in accordance with Goodrich Service Bulletin 23400-27-27, 
Revision 1, dated September 14, 2007.
    (6) As of 60 months after the effective date of this AD, no 
person may install a Goodrich P/N 23400-3 or P/N 23400-5 elevator 
booster control unit on any airplane.

FAA AD Differences

    Note 1: 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, 
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

    (h) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2009-0032, dated February 17, 2009; Fokker Service 
Bulletin SBF100-27-088, dated June 4, 2007; and Goodrich Service 
Bulletin 23400-27-27, Revision 1, dated September 14, 2007; for 
related information.

Material Incorporated by Reference

    (i) You must use Fokker Service Bulletin SBF100-27-088, dated 
June 4, 2007; and Goodrich Service Bulletin 23400-27-27, Revision 1, 
dated September 14, 2007; as applicable; 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 this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) 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 
<a href="/cdn-cgi/l/email-protection#493d2c2a2127202a28253a2c3b3f202a2c3a672f2622222c3b3a2c3b3f202a2c3a093a3d263b22672a2624"><span class="__cf_email__" data-cfemail="f38796909b9d9a90929f809681859a909680dd959c98989681809681859a909680b380879c8198dd909c9e">[email protected]</span></a>; Internet http://www.myfokkerfleet.com.
    (3) 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[dash]mail <a href="/cdn-cgi/l/email-protection#e18b84808fcf8393848485a1868e8e8593888289cf828e8c"><span class="__cf_email__" data-cfemail="751f10141b5b170710101135121a1a11071c161d5b161a18">[email protected]</span></a>; 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 or 425-227-1152.
    (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 28, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-102 Filed 1-13-10; 8:45 am]
BILLING CODE 4910-13-P


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