Document ID: FAA-2018-0956-0002
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Fokker Services B.V. Airplanes
Posted Date: 2019-03-04T05:00Z

[Federal Register Volume 84, Number 42 (Monday, March 4, 2019)]
[Rules and Regulations]
[Pages 7261-7264]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-03267]

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 Rules and Regulations
                                                 Federal Register
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  Federal Register / Vol. 84, No. 42 / Monday, March 4, 2019 / Rules 
and Regulations  

[[Page 7261]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0956; Product Identifier 2018-NM-041-AD; Amendment 
39-19568; AD 2019-03-16]
RIN 2120-AA64

Airworthiness Directives; Fokker Services B.V. Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Fokker Services B.V. Model F.27 Mark 100, 200, 300, 400, 500, 600, and 
700 airplanes. This AD was prompted by a report of a main landing gear 
(MLG) collapse due to a broken drag stay; an investigation revealed 
that the drag stay failure was due to fatigue cracks, introduced by 
incorrect machining of the affected drag stay tube during production. 
This AD requires an inspection of the drag stay unit to determine the 
signal indication, and related investigative and corrective actions if 
necessary. We are issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective April 8, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of April 8, 
2019.

ADDRESSES: For Fokker service information identified in this final 
rule, contact Fokker Services B.V., Technical Services Dept., P.O. Box 
1357, 2130 EL Hoofddorp, the Netherlands; telephone +31 (0)88-6280-350; 
fax +31 (0)88-6280-111; email technicalservices@fokker.com; internet 
http://www.myfokkerfleet.com. For Dowty Aerospace Landing Gear service 
information identified in this final rule, contact Safran Landing 
Systems, One Carbon Way, Walton, KY 41094; telephone (859) 525-8583; 
fax (859) 485-8827. You may view this service information at the FAA, 
Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For 
information on the availability of this material at the FAA, call 206-
231-3195. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0956.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0956; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this final rule, the regulatory evaluation, any comments received, and 
other information. The address for Docket Operations (phone: 800-647-
5527) is U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3226.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all Fokker Services B.V. 
Model F.27 Mark 100, 200, 300, 400, 500, 600, and 700 airplanes. The 
NPRM published in the Federal Register on November 8, 2018 (83 FR 
55825). The NPRM was prompted by a report of an MLG collapse due to a 
broken drag stay; an investigation revealed that the drag stay failure 
was due to fatigue cracks, introduced by incorrect machining of the 
affected drag stay tube during production. The NPRM proposed to require 
an inspection of the drag stay unit to determine the signal indication, 
and related investigative and corrective actions if necessary.
    We are issuing this AD to address fatigue cracking, which could 
lead to MLG collapse and result in damage to the airplane during 
landing and consequent injury to passengers.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2018-0015, dated January 25, 2018 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for all Fokker Services B.V. Model F.27 
Mark 100, 200, 300, 400, 500, 600, and 700 airplanes. The MCAI states:

    In 1993, an occurrence was reported concerning an MLG collapse 
due to a broken drag stay on a Fokker F27 Mark 500 RFV (rough field 
version/configuration). The investigation revealed that the drag 
stay failure was due to fatigue cracks, introduced by incorrect 
machining (not smooth, with a notch) of the affected drag stay tube 
bore during production.
    This condition, if not detected and corrected, could lead to MLG 
collapse, possibly resulting in damage to the aeroplane during 
landing and consequent injury to occupants.
    To address this unsafe condition, DALG [Dowty Aerospace Landing 
Gear] issued SB [service bulletin] 32-169B and SB 32-82W (both later 
revised), and Fokker Services issued SB F27/32-167, to provide 
inspection instructions. Consequently, the Civil Aviation Authority 
of the Netherlands (CAA-NL) issued AD (BLA) 93-169 (later revised) 
[which corresponded to FAA AD 97-04-08, Amendment 39-9932 (62 FR 
7924, February 21, 1997), and applies to certain Fokker Model F27 
Mark 050, 100, 200, 300, 400, 600, and 700 airplanes], requiring a 
one-time ultrasonic inspection to identify the type of drag stay 
tube installed (with stepped or straight bore) on each affected drag 
stay unit, inspection of the affected drag stay tubes for the 
presence of cracks, and, depending on findings, re-identification.
    After CAA-NL AD (BLA) 93-169/2 was issued, another occurrence 
was reported on an F27 Mark 500 RFV. Investigation results 
determined that the drag stay tube of the second occurrence had not 
been inspected as required by CAA-NL AD (BLA) 93-169, due to 
misinterpretation of the instructions of Fokker SB F27/32-167. 
Prompted by these findings, Fokker Services issued SB F27-32-171, 
providing additional inspection instructions, and CAA-NL issued AD 
NL-2005-003 (EASA approval 2005-3869) [which corresponds to FAA AD 
2006-25-06, Amendment 39-14847 (71 FR 71475, December 11, 2006) and 
applies to Fokker Services B.V. Model F.27 Mark 500 airplanes] to 
require repetitive inspections of the affected drag stay tubes to 
detect cracks and,

[[Page 7262]]

depending on findings, rework or replacement.
    Since those SBs and [CAA-NL] ADs were issued, the applicable CMM 
[component maintenance manual] were changed, although with incorrect 
P/N information, as a result of which an affected drag stay tube 
with a non-conforming bore radius may inadvertently have been 
installed on an aeroplane. Prompted by these findings, the 
applicable CMM were corrected and re-issued, and SLS issued Service 
Letter (SL) F27-W-8 to inform the operators, and Fokker Services 
introduced the relevant corrections in the F27 Mark 100 through Mark 
700 Illustrated Parts Catalogue (IPC) in September 2017.
    Installation of an affected drag stay tube with a non-conforming 
bore radius, on an MLG drag stay unit that has been re-identified, 
i.e. not subject to the repetitive inspections as required by CAA-NL 
AD NL-2005-003, would reintroduce the unsafe condition as originally 
addressed by the SBs and ADs referred to above. To address this 
potential unsafe condition, Fokker Services issued SBF27-32-173 to 
provide instructions to inspect, remove/discard or re-identify the 
affected drag stay tubes.
    For the reasons described above, this [EASA] AD requires a one-
time inspection of the affected drag stay units to determine whether 
an affected drag stay tube is installed, repetitive inspections of 
those that have an affected drag stay tube installed, and, depending 
on findings, accomplishment of applicable corrective action(s) 
[which includes replacement of the drag stay tube].
    With the issuance of this [EASA] AD and [EASA] AD 2018-0016 
[dated January 25, 2018], the requirements of CAA-NL AD (BLA) 93-
169/2 dated 29 April 1994 are no longer necessary and that AD is 
also cancelled.

    EASA AD 2018-0016, dated January 25, 2018, applies to Model F.27 
Mark 500 airplanes and has been added to the Required Airworthiness 
Action List.
    You may examine the MCAI in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0956.

Comments

    We gave the public the opportunity to participate in developing 
this final rule. We received no comments on the NPRM or on the 
determination of the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this final rule as proposed, 
except for minor editorial changes. We have determined that these minor 
changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    Fokker Services B.V. has issued Service Bulletin SBF27-32-173, 
dated November 30, 2017. This service information describes procedures 
for an inspection of the drag stay unit to determine the signal 
indication, and related investigative and corrective actions if 
necessary. This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Other Related Service Information

    Dowty Aerospace Landing Gear issued Service Bulletin 32-82W, 
Revision 2, dated July 29, 1994; and Service Bulletin 32-169B, Revision 
2, dated July 29, 1994. This service information describes procedures 
for reworking the drag stay tube. These documents are distinct since 
they apply to different airplane models.
    This service information can be obtained from SAFRAN Landing 
Systems by the means identified in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 1 airplane of U.S. registry. We 
estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
2 work-hours x $85 per hour = $170...........................              $0             $170             $170
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this AD.

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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes and 
associated appliances to the Director of the System Oversight Division.

Regulatory Findings

    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

[[Page 7263]]

under the criteria of the Regulatory Flexibility Act.

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 airworthiness 
directive (AD):

2019-03-16 Fokker Services B.V. Airplanes: Docket No. FAA-2018-0956; 
Product Identifier 2018-NM-041-AD.

(a) Effective Date

    This AD is effective April 8, 2019.

(b) Affected ADs

    This AD affects AD 2006-25-06, Amendment 39-14847 (71 FR 71475, 
December 11, 2006) (``AD 2006-25-06'') and AD 97-04-08, Amendment 
39-9932 (62 FR 7924, February 21, 1997) (``AD 97-04-08'').

(c) Applicability

    This AD applies to all Fokker Services B.V. Model F.27 Mark 100, 
200, 300, 400, 500, 600, and 700 airplanes, certificated in any 
category.

(d) Subject

    Air Transport Association (ATA) of America Code 32, Main landing 
gear.

(e) Reason

    This AD was prompted by a report of a main landing gear (MLG) 
collapse due to a broken drag stay; an investigation revealed that 
the drag stay failure was due to fatigue cracks, introduced by 
incorrect machining of the affected drag stay tube during 
production. We are issuing this AD to address fatigue cracking, 
which could lead to MLG collapse and result in damage to the 
airplane during landing and consequent injury to passengers.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Definitions

    (1) For purposes of this AD, an affected drag stay unit is 
SAFRAN Landing Systems (previously Messier-Dowty, Dowty Aerospace) 
MLG drag stay unit, part number (P/N) 200261001, P/N 200261002, P/N 
200261003, P/N 200261004, P/N 200485001, P/N 200485002, P/N 
200485003, P/N 200485004, P/N 200684001, P/N 200684002, P/N 
200684003, or P/N 200684004.
    (2) For purposes of this AD, an affected drag stay tube is a 
SAFRAN Landing Systems (previously Messier-Dowty, Dowty Aerospace) 
MLG drag stay tube, P/N 200259300, which has a change in section 
(stepped bore).

(h) Configuration Verification of the Drag Stay Units

    Within 12 months after the effective date of this AD, do an 
ultrasonic inspection of each affected drag stay unit to determine 
the configuration of the drag stay tube, in accordance with step F. 
of the Accomplishment Instructions of Fokker Service Bulletin SBF27-
32-173, dated November 30, 2017.

(i) Re-Identification of an Affected Drag Stay Unit

    (1) If, during the inspection required by paragraph (h) of this 
AD, an affected drag stay unit is found to have a straight bore drag 
stay tube, P/N 200485300, installed: Before further flight, re-
identify that affected drag stay unit in accordance with step I.(2), 
I.(3), or I.(4), as applicable, of the Accomplishment Instructions 
of Fokker Service Bulletin SBF27-32-173, dated November 30, 2017.
    (2) If, during the inspection required by paragraph (h) of this 
AD, an affected drag stay unit is found to have an affected drag 
stay tube, P/N 200259300, installed with a correct radius: Before 
further flight, re-identify the affected drag stay unit in 
accordance with step J.(1), J.(2), or J.(3), as applicable, of the 
Accomplishment Instructions of Fokker Service Bulletin SBF27-32-173, 
dated November 30, 2017.
    (3) If, during the inspection required by paragraph (h) of this 
AD, an affected drag stay unit is found to have an affected drag 
stay tube, P/N 200259300, installed with an incorrect radius: Before 
further flight, re-identify the affected drag stay unit in 
accordance with step K.(1), K.(2), or K.(3), as applicable, of the 
Accomplishment Instructions of Fokker Service Bulletin SBF27-32-173, 
dated November 30, 2017.

(j) Inspection and Corrective Action for Certain Drag Stay Unit Part 
Numbers

    For affected drag stay units having P/N 200261002, P/N 
200261003, P/N 200485002, P/N 200485003, P/N 200684002, or P/N 
200684003: Within 12 months after the effective date of this AD, do 
an ultrasonic inspection of the affected drag stay tube for any 
cracking, in accordance with step G. of the Accomplishment 
Instructions of Fokker Service Bulletin SBF27-32-173, dated November 
30, 2017.
    (1) If, during the ultrasonic inspection, a crack indication is 
found, before further flight, replace the affected drag stay tube 
with a serviceable part, in accordance with step H. of the 
Accomplishment Instructions of Fokker Service Bulletin SBF27-32-173, 
dated November 30, 2017.
    (2) For affected drag stay units having P/N 200261002, P/N 
200485002, or P/N 200684002 (drag stay units with incorrect bore 
radius drag stay tubes): If, during the ultrasonic inspection, no 
indication of cracking is found, within 1,500 flight cycles after 
that inspection, and, thereafter, at intervals not to exceed 1,500 
flight cycles until the next scheduled MLG overhaul, repeat the 
ultrasonic inspection of the affected drag stay tube in accordance 
with step G. of the Accomplishment Instructions of Fokker Service 
Bulletin SBF27-32-173, dated November 30, 2017.

(k) Parts Installation Limitation

    As of the effective date of this AD, no person may install, on 
any airplane, a drag stay unit (which includes installation of a 
replacement MLG), unless it has been determined that no affected 
drag stay tube is installed; or the installed affected drag stay 
tube has been reworked during the MLG overhaul in accordance with 
the instructions of Appendix B of Dowty Aerospace Landing Gear 
Service Bulletin 32-82W, Revision 2, dated July 29, 1994 (for Model 
F.27 Mark 500 airplanes), or Dowty Aerospace Landing Gear Service 
Bulletin 32-169B, Revision 2, dated July 29, 1994 (for Model F.27 
Mark 100, 200, 300, 400, 600, and 700 airplanes), as applicable; or 
has passed an inspection (confirmed correct bore radius) in 
accordance with the Accomplishment Instructions of Fokker Service 
Bulletin SBF27-32-173, dated November 30, 2017. For the purpose of 
this AD, removal of an MLG or an affected drag stay unit from an 
airplane and re-installing that MLG or drag stay unit on the same 
airplane is not ``installation.''

(l) Terminating Action for Other ADs

    Accomplishing the actions required by this AD terminates all 
requirements of AD 2006-25-06 and AD 97-04-08.

(m) Credit for Previous Actions

    This paragraph provides credit for the applicable actions 
specified in paragraph (k) of this AD, if those actions were 
performed before the effective date of this AD using Dowty Aerospace 
Landing Gear Service Bulletin 32-82W, Revision 1, dated September 
10, 1993, or Dowty Aerospace Landing Gear Service Bulletin 32-169B, 
Revision 1, dated September 10, 1993.

(n) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Section, send it to the attention of 
the person identified in paragraph (o)(2) of this AD. Information 
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 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.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved

[[Page 7264]]

by the Manager, International Section, Transport Standards Branch, 
FAA; or the European Aviation Safety Agency (EASA); or Fokker 
Services B.V.'s EASA Design Organization Approval (DOA). If approved 
by the DOA, the approval must include the DOA-authorized signature.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2018-0015, dated January 25, 2018, for related 
information. This MCAI may be found in the AD docket on the internet 
at http://www.regulations.gov by searching for and locating Docket 
No. FAA-2018-0956.
    (2) For more information about this AD, contact Tom Rodriguez, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 
and fax 206-231-3226.
    (3) Dowty Aerospace Landing Gear service information identified 
in this AD, and not incorporated by reference, is available from 
Safran Landing Systems, One Carbon Way, Walton, KY 41094; telephone 
(859) 525-8583; fax (859) 485-8827.

(p) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Fokker Service Bulletin SBF27-32-173, dated November 30, 
2017.
    (ii) [Reserved]
    (3) For Fokker service information identified in this AD, 
contact Fokker Services B.V., Technical Services Dept., P.O. Box 
1357, 2130 EL Hoofddorp, the Netherlands; telephone +31 (0)88-6280-
350; fax +31 (0)88-6280-111; email technicalservices@fokker.com; 
internet http://www.myfokkerfleet.com.
    (4) You may view this service information at the FAA, Transport 
Standards Branch, 2200 South 216th St., Des Moines, WA. For 
information on the availability of this material at the FAA, call 
206-231-3195.
    (5) You may view this 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/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on February 14, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-03267 Filed 3-1-19; 8:45 am]
 BILLING CODE 4910-13-P