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[Federal Register Volume 77, Number 89 (Tuesday, May 8, 2012)]
[Rules and Regulations]
[Pages 26948-26950]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-10829]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1169; Directorate Identifier 2010-NM-050-AD; 
Amendment 39-17040; AD 2012-09-05]
RIN 2120-AA64

Airworthiness Directives; Fokker Services B.V. Airplanes

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

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
2-Fokker Services B.V.2-Model F.28 Mark 0100 airplanes. This AD was 
prompted by reports of failure of the main fitting on Messier-Dowty 
main landing gear (MLG) units due to fatigue cracking in the area of 
the filler and bleeder holes, and failure of the sliding member due to 
fatigue cracking at the area of the chrome run-out/lower radius of the 
sliding tube portion of the sliding member. This AD requires 
modification and re-identification of the MLG units, or replacement of 
the MLG unit with a modified one. We are issuing this AD to detect and 
correct fatigue cracking of the main fitting or sliding member on the 
MLG, which could lead to failure of the MLG and possibly loss of 
control of the airplane during landing rollout.

DATES: This AD becomes effective June 12, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of June 12, 
2012.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
November 18, 2010 (75 FR 63042, October 14, 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 November 7, 2011 (76 
FR 68668). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    Since introduction of the F28 Mark 0100 aeroplane into airline 
service, there have been a number of occurrences with Messier-Dowty 
MLG [main landing gear] units where the main fitting failed, due to 
fatigue cracking in the area of the filler and bleeder holes, and 
occurrences where the sliding member failed, due to fatigue cracking 
at the area of chrome run-out/lower radius of the sliding tube 
portion of the sliding member.
    Investigation has revealed that the most probable cause of both 
the main fitting and sliding member cracks is high compressive 
stress during braking at higher deceleration levels outside the 
regular fatigue load spectrum. Starting at deceleration stress 
levels somewhat below limit load, the high compressive stress 
locally exceeds the elasticity limit of the material, leaving a 
residual tensile stress at release of the heavy braking load. 
Subsequently, this local residual tensile stress results in a 
negative effect on the fatigue life of the component.
    This condition, if not detected and corrected, could lead to 
failure of the MLG, possibly resulting in loss of control of the 
aeroplane during the landing rollout. To address this unsafe 
condition, the Civil Aviation Authority of the Netherlands (CAA-NL) 
issued AD NL-2005-012 (EASA approval 2005-6363) [which corresponds 
to FAA 2007-04-23, Amendment 39-14956 (72 FR 8615, February 27, 
2007)] to require repetitive inspections of the sliding member 
(Fokker Services SBF100-32-144) and AD NL-2006-003 (EASA approval 
2006-0041) to require repetitive inspections of the main fitting 
(Fokker Services SBF100-32-146). Messier-Dowty has now developed a 
modification, resulting in a strengthened sliding member and a 
strengthened main fitting, which is the terminating action for these 
repetitive inspections.
    For the reasons described above, this [EASA] AD requires the 
modification and reidentification of the affected MLG units, or 
replacement of the affected MLG units with modified units.
    This [EASA] AD has been revised to * * * state that modification 
of an aeroplane * * * also constitutes terminating action for the 
actions required by CAA-NL AD (BLA) 2002-115/2 dated October 8, 2004 
[which partially corresponds to FAA AD 2008-20-03, Amendment 39-
15682 (73 FR 56452, September 29, 2008)].
    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 (76 FR 68668, November 7, 
2011) or on the determination of the cost to the public.

Explanation of Change Made to This AD

    We have revised paragraph (h)(2) of this AD to correct a 
typographical error. This error resulted in a reference to paragraph 
(c) of this AD instead of paragraph (g) of this AD.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed except for 
minor editorial changes and/or format changes. We have determined that 
these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (76 FR 68668, November 7, 2011) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (76 FR 68668, November 7, 2011).

Costs of Compliance

    We estimate that this AD will affect 4 products of U.S. registry. 
We also estimate that it will take about 30 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 $520,000 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 $2,090,200, or $522,550 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

[[Page 26949]]

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 that 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);
    3. Will not affect intrastate aviation in Alaska; and
    4. 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 (76 FR 68668, November 7, 
2011), 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

    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:

2012-09-05 Fokker Services B.V.: Amendment 39-17040. Docket No. FAA-
2011-1169; Directorate Identifier 2010-NM-050-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective June 12, 
2012.

(b) Affected ADs

    This AD affects: AD 98-06-26, Amendment 39-10404 (63 FR 13502, 
March 20, 1998); AD 98-13-32, Amendment 39-10623 (63 FR 34581, June 
25, 1998); AD 2004-14-01, Amendment 39-13710 (69 FR 41391, July 9, 
2004); AD 2007-04-23, Amendment 39-14956 (72 FR 8615, February 27, 
2007); AD 2008-20-03, Amendment 39-15682 (73 FR 56452, September 29, 
2008); and AD 2010-21-12, Amendment 39-16472 (75 FR 63042, October 
14, 2010).

(c) Applicability

    This AD applies to Fokker Services B.V. Model F.28 Mark 0100 
airplanes, certificated in any category, all serial numbers, 
equipped with Messier-Dowty (formerly Dowty-Rotol, Dowty Aerospace 
Gloucester) main landing gear (MLG).

(d) Subject

    Air Transport Association (ATA) of America Code 32: Landing 
Gear.

(e) Reason

    This AD was prompted by reports of failure of the main fitting 
on Messier-Dowty MLG units due to fatigue cracking in the area of 
the filler and bleeder holes, and failure of the sliding member due 
to fatigue cracking at the area of the chrome run-out/lower radius 
of the sliding tube portion of the sliding member. We are issuing 
this AD to detect and correct fatigue cracking of the main fitting 
or sliding member on the MLG, which could lead to failure of the MLG 
and possibly loss of control of the airplane during landing rollout.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Inspection for Part Numbers

    Within 48 months after the effective date of this AD, do an 
inspection of the MLG to determine whether Messier-Dowty (formerly 
Dowty-Rotol, Dowty Aerospace Gloucester) MLG units having part 
number (P/N) 201072011, 201072012, 201072013, 201072014, 201072015, 
or 201072016 are installed on the airplane. A review of airplane 
maintenance records is acceptable in lieu of this inspection if the 
part number of the MLG unit can be conclusively determined from that 
review. If any of those part numbers is found, do the requirements 
of paragraph (h) of this AD.

(h) Replacement or Modification and Re-Identification if Certain Part 
Numbers Are Found

    If, during the inspection required by paragraph (g) of this AD, 
any Messier-Dowty (formerly Dowty-Rotol, Dowty Aerospace Gloucester) 
MLG units having P/N 201072011, 201072012, 201072013, 201072014, 
201072015, or 201072016 are found, within 48 months after the 
effective date of this AD, do the actions specified in paragraph 
(h)(1) or (h)(2) of this AD.
    (1) Replace each MLG unit having P/N 201072011, 201072012, 
201072013, 201072014, 201072015, or 201072016, with a MLG unit 
having P/N 201072017, P/N 201072019, or P/N 201072021 (for left-
hand), as applicable; or P/N 201072018, P/N 201072020 or P/N 
201072022 (for right-hand), as applicable; in accordance with the 
Accomplishment Instructions of Fokker Service Bulletin SBF100-32-
155, dated July 23, 2009, and do the actions required in paragraph 
(j) of this AD.
    (2) Modify and re-identify each affected MLG unit identified in 
paragraph (g) of this AD, in accordance with the Accomplishment 
Instructions of Messier-Dowty Service Bulletin F100-32-112, dated 
July 17, 2009, and do the actions required in paragraph (j) of this 
AD.

(i) Parts Installation

    As of the effective date of this AD, no person may install on 
any airplane a MLG unit having P/N 201072011, P/N 201072012, P/N 
201072013, P/N 201072014, P/N 201072015, or P/N 201072016.

(j) Removing Placard and Airplane Flight Manual Amendment

    After accomplishing the actions required by paragraph (h) of 
this AD, before further flight, remove the airplane flight manual 
amendment and placard that were installed as required by AD 2008-20-
03, Amendment 39-15682 (73 FR 56452, September 29, 2008).

(k) Prior or Concurrent Actions

    Prior to or concurrently with the action (replacement or 
modification) required by paragraph (h) of this AD, accomplish the 
following actions:
    (1) Install the torque link spacer with changed outer diameter, 
in accordance with the Accomplishment Instructions of Fokker Service 
Bulletin SBF100-32-097, dated September 30, 1995.
    (2) Remove, if installed, the water spray deflectors, in 
accordance with the Accomplishment Instructions of Fokker Service 
Bulletin SBF100-32-132, dated December 5, 2001.
    (3) Replace all P/N AE70690E, P/N AE70691E, P/N AE99111E, and P/
N AE99119E brake quick-disconnect couplings with improved units, in 
accordance with Part 2 of the Accomplishment Instructions of Fokker 
Service Bulletin SBF100-32-156, Revision 1, dated June 29, 2009. 
Accomplishing the actions required by this

[[Page 26950]]

paragraph terminates the requirements of AD 2010-21-12, Amendment 
39-16472 (75 FR 63042, October 14, 2010), for that airplane only.

(l) ADs Affected by Accomplishment of Paragraph (h) of This AD

    Accomplishing the actions required by paragraph (h) of this AD 
terminates the requirements of the following ADs for that airplane 
only: AD 98-06-26, Amendment 39-10404 (63 FR 13502, March 20, 1998); 
AD 98-13-32, Amendment 39-10623 (63 FR 34581, June 25, 1998); AD 
2007-04-23, Amendment 39-14956 (72 FR 8615, February 27, 2007); and 
AD 2008-20-03, Amendment 39-15682 (73 FR 56452, September 29, 2008).

(m) Other AD Affected by Accomplishment of Paragraph (h) of This AD

    Accomplishing the actions required by paragraph (h) of this AD 
terminates the requirements of AD 2004-14-01, Amendment 39-13710 (69 
FR 41391, July 9, 2004), for that airplane only.

(n) Other FAA AD Provisions

    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, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
local flight standards district office/certificate holding 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.

(o) Related Information

    Refer to MCAI European Aviation Safety Agency (EASA) 
Airworthiness Directive 2009-0269R1, dated March 11, 2010, and the 
service information identified in paragraphs (o)(1) through (o)(5) 
of this AD, for related information.
    (1) Fokker Service Bulletin SBF100-32-097, dated September 30, 
1995.
    (2) Fokker Service Bulletin SBF100-32-132, dated December 5, 
2001.
    (3) Fokker Service Bulletin SBF100-32-155, dated July 23, 2009.
    (4) Fokker Service Bulletin SBF100-32-156, Revision 1, dated 
June 29, 2009.
    (5) Messier-Dowty Service Bulletin F100-32-112, dated July 17, 
2009.

(p) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the following service 
information under 5 U.S.C. 552(a) and 1 CFR part 51 on the date 
specified.
    (2) You must use the following service information to do the 
actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
June 12, 2012.
    (i) Fokker Service Bulletin SBF100-32-097, dated September 30, 
1995.
    (ii) Fokker Service Bulletin SBF100-32-132, dated December 5, 
2001.
    (iii) Fokker Service Bulletin SBF100-32-155, dated July 23, 
2009.
    (iv) Messier-Dowty Service Bulletin F100-32-112, dated July 17, 
2009.
    (4) The following service information was approved for IBR 
November 18, 2010 (75 FR 63042, October 14, 2010).
    (i) Fokker Service Bulletin SBF100-32-156, Revision 1, dated 
June 29, 2009.
    (5) 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; email 
technicalservices.fokkerservices@stork.com; Internet  http://www.myfokkerfleet.com.
    (6) For Messier-Dowty service information identified in this AD, 
contact Messier Services Americas, Customer Support Center, 45360 
Severn Way, Sterling, Virginia 20166-8910; telephone 703-450-8233; 
fax 703-404-1621; Internet https://techpubs.services.messier-dowty.com.
    (7) 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.
    (8) 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 an NARA facility, 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 April 26, 2012.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-10829 Filed 5-7-12; 8:45 am]
BILLING CODE 4910-13-P
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