AD 2018-24-05

We are adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 airplanes. This AD was prompted by reports that filters, which are integral to certain T-unions in the landing gear hydraulic control system, disconnected from their housing and, in some cases, migrated. This AD requires replacing certain T- unions with an integral filter with T-unions without an integral filter. We are issuing this AD to address the unsafe condition on these products.

Final rule.

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):

2018-24-05 Fokker Services B.V.: Amendment 39-19509; Docket No. FAA- 2018-0707; Product Identifier 2018-NM-067-AD.

(a) Effective Date

This AD is effective January 2, 2019.

(b) Affected ADs

None.

(c) Applicability

This AD applies to Fokker Services B.V. Model F28 Mark 0070, 0100, 1000, 2000, 3000, and 4000 airplanes, certificated in any category, all manufacturer serial numbers.

(d) Subject

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

(e) Reason

This AD was prompted by reports thatfilters, which are integral to certain T-unions in the landing gear hydraulic control system, disconnected from their housing and, in some cases, migrated. We are issuing this AD to address flow reduction along the hydraulic circuit and the possible inability to completely extend one or both of the main landing gear legs, which could result in damage to the airplane during landing, and consequent injury to occupants.

(f) Compliance

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

(g) Definitions

For the purposes of this AD, the definitions in paragraphs (g)(1) through (g)(3) inclusive apply.
(1) An affected part is any hydraulic T-union with an integral filter, having part number (P/N) QA07596 or P/N QA07597, installed on the production line or introduced in-service by Fokker Service Bulletin SBF100-32-095 or Fokker Service Bulletin SBF28-32-154, as applicable.
(2) Group 1 airplanes are those that have an affected part installed.
(3) Group 2 airplanes are those that do not have an affected part installed.

(h) Required Actions

For Group 1 airplanes, within 24 months after the effective date of this AD, modify the airplane in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF28-32-166, dated February 21, 2018; or Fokker Service Bulletin SBF100-32-170, dated February 21, 2018; as applicable. The corresponding part numbers of affected (old) parts and replacement (new) parts are specified in figure 1 to paragraph (h) of this AD.

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(i) Parts Installation Prohibition

No person may install an affected part on any airplane, as of the time specified in paragraph (i)(1) or (i)(2) of this AD, as applicable.
(1) For Group 1 airplanes: After modification of the airplane as required by paragraph (h) of this AD.
(2) For Group 2 airplanes: From the effective date of this AD.

(j) Other FAA AD ProvisionsThe 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 (k)(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 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.

(k) Related Information

(1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2018-0076, dated April 6, 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-2018-0707.
(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.

(l) 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 SBF28-32-166, dated February 21, 2018.
(ii) Fokker Service Bulletin SBF100-32-170, dated February 21, 2018.
(3) For 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.

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 F28 airplanes. The NPRM published in the Federal Register on August 13, 2018 (83 FR 39918). The NPRM was prompted by reports that filters, which are integral to certain T-unions in the landing gear hydraulic control system, disconnected from their housing and, in some cases, migrated. The NPRM proposed to require replacing certain T- unions with an integral filter with T-unions without an integral filter.
We are issuing this AD to address flow reduction along the hydraulic circuit and the possible inability to completely extend one or both of the main landing gear legs, which could result in damage to the airplane during landing, and consequent injury to occupants.
The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2018-0076, dated April 6, 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 F28 airplanes. The MCAI states:

With [Fokker Service Bulletins] SBF100-32-095 and SBF28-32-154, Fokker Services introduced the option of installing a T-union with an integral filter into the landing gear hydraulic control system. On some F28 Mark 0070 and Mark 0100 aeroplanes, the affected part was installed on the production line. Since introduction, occurrences were reported where the T-union filter disconnected from its housing, and in some cases migrated. In one occurrence, the migrated filter caused a flow reduction and inability to retract one of the main landing gear (MLG) legs.
This condition, if not corrected, could lead to flow reduction along the hydraulic circuit and inability to completely extend one of the MLG legs, possibly resulting in damage to the aeroplane during landing, and consequent injury to occupants.
To address this potential unsafe condition, Fokker Services issued the applicable SB [Fokker Service Bulletin SBF28-32-166; and Fokker Service Bulletin SBF100-32-170] to provide instructions to replace the affected parts with improved parts. Fokker Services also cancelled the SBs that introduced the affected parts.
For the reason described above, this [EASA] AD requires replacement of the affected parts with T-unions without an integral filter. This [EASA] AD also prohibits the installation of affected parts.

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- 0707.

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 thepublic 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 SBF28-32-166, dated February 21, 2018; and Service Bulletin SBF100-32-170, dated February 21, 2018. This service information describes procedures for removal of certain T-unions with an integral filter and installation of T-unions without an integral filter. These documents are distinct since they apply to different airplane models in different configurations. 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.Costs of Compliance

We estimate that this AD affects 4 airplanes of U.S. registry. We estimate the following costs to comply with this AD:

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Estimated Costs ----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- 10 work-hour x $85 per hour = $850........................... $1,038 $1,888 $7,552 ----------------------------------------------------------------------------------------------------------------

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 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.