Federal Aviation Administration (FAA), DOT.
Final rule; request for comments.
The FAA is adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. This AD was prompted by a report that corrosion was found on the horizontal flange on the front spar lower boom, between the rebate strap and the lower boom, and
This AD becomes effective July 9, 2021.
The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 9, 2021.
The FAA must receive comments on this AD by August 9, 2021.
You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:
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For material incorporated by reference (IBR) in this AD, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email
You may examine the AD docket on the internet at
Tom Rodriguez, Aerospace Engineer, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3226; email
EASA, which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2021–0014, dated January 13, 2021 (EASA AD 2021–0014) (also referred to as the Mandatory Continuing Airworthiness Information, or the MCAI), to correct an unsafe condition for all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes.
This AD was prompted by a report that corrosion was found on the horizontal flange on the front spar lower boom, between the rebate strap and the lower boom, and resulted in bulging. The FAA is issuing this AD to address corrosion on the horizontal flange, which could lead to reduced structural integrity of the wing torsion box structure. See the MCAI for additional background information.
EASA AD 2021–0014 specifies procedures for doing a detailed visual inspection to detect any bulging, loose, and missing countersunk fastener heads at the LH and RH outer wing lower skin of the front spar between wing station (WSTA) 10110 and WSTA 11190; and applicable on-condition actions. On-condition actions include repetitive detailed visual inspections of the LH and RH outer wing lower skin, at the front spar between WSTA 10110 and WSTA 11190, if bulging between 0.5 mm and 3 mm is found; a detailed visual inspection to detect corrosion at the front spar lower boom and rebate strap if any bulging, loose, or missing countersunk fastener head, or bulging in excess of 3 mm, is found; and repair of any corrosion damage. EASA AD 2021–0014 also specifies reporting inspection findings. This material is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the
This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to the FAA's bilateral agreement with the State of Design Authority, the FAA has been notified of the unsafe condition described in the MCAI referenced above. The FAA is issuing this AD because the FAA evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design.
This AD requires accomplishing the actions specified in EASA AD 2021–0014 described previously, as incorporated by reference, except for any differences identified as exceptions in the regulatory text of this AD.
In the FAA's ongoing efforts to improve the efficiency of the AD process, the FAA developed a process to use certain civil aviation authority (CAA) ADs as the primary source of information for compliance with requirements for corresponding FAA ADs. The FAA has been coordinating this process with other manufacturers and CAAs. As a result, EASA AD 2021–0014 is incorporated by reference in this AD. This AD, therefore, requires compliance with EASA AD 2021–0014 in its entirety, through that incorporation, except for any differences identified as exceptions in the regulatory text of this AD. Using common terms that are the same as the heading of a particular section in EASA AD 2021–0014 does not mean that operators need comply only with that section. For example, where the AD requirement refers to “all required actions and compliance times,” compliance with this AD requirement is not limited to the section titled “Required Action(s) and Compliance Time(s)” in the EASA AD. Service information specified in EASA AD 2021–0014 that is required for compliance with it is available at
Section 553(b)(3)(B) of the Administrative Procedure Act (APA) (5 U.S.C. 551
There are currently no domestic operators of these products. Accordingly, notice and opportunity for prior public comment are unnecessary, pursuant to 5 U.S.C. 553(b)(3). In addition, for the foregoing reason, the FAA finds that good cause exists pursuant to 5 U.S.C. 553(d) for making this amendment effective in less than 30 days.
The FAA invites you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under
Except for Confidential Business Information (CBI) as described in the following paragraph, and other information as described in 14 CFR 11.35, the FAA will post all comments received, without change, to
CBI is commercial or financial information that is both customarily and actually treated as private by its owner. Under the Freedom of Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public disclosure. If your comments responsive to this AD contain commercial or financial information that is customarily treated as private, that you actually treat as private, and that is relevant or responsive to this AD, it is important that you clearly designate the submitted comments as CBI. Please mark each page of your submission containing CBI as “PROPIN.” The FAA will treat such marked submissions as confidential under the FOIA, and they will not be placed in the public docket of this AD. Submissions containing CBI should be sent to Tom Rodriguez, Aerospace Engineer, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3226; email
The requirements of the RFA do not apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt a rule without prior notice and comment. Because the FAA has determined that it has good cause to adopt this rule without notice and comment, RFA analysis is not required.
Currently, there are no affected U.S.-registered airplanes. If an affected airplane is imported and placed on the U.S. Register in the future, the FAA provides the following cost estimates to comply with this AD:
The FAA estimates that it takes about 1 work-hour per product to comply with the reporting requirement in this AD. The average labor rate is $85 per hour. Based on these figures, the FAA estimates the cost of reporting the inspection results to be $85 per product.
The FAA has received no definitive data on which to base the cost estimates for the on-condition actions and repairs specified in this AD.
A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this AD is 2120–0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to Information Collection Clearance Officer, Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth, TX 76177–1524.
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.
The FAA is 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.
The FAA 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, and
(2) Will not affect intrastate aviation in Alaska.
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:
49 U.S.C. 106(g), 40113, 44701.
This airworthiness directive (AD) becomes effective July 9, 2021.
None.
This AD applies to all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes, certificated in any category.
Air Transport Association (ATA) of America Code 57, Wings.
This AD was prompted by a report that corrosion was found on the horizontal flange on the front spar lower boom, between the rebate strap and the lower boom, and resulted in bulging. The FAA is issuing this AD to address corrosion on the horizontal flange, which could lead to reduced structural integrity of the wing torsion box structure.
Comply with this AD within the compliance times specified, unless already done.
Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, European Union Aviation Safety Agency (EASA) AD 2021–0014, dated January 13, 2021 (EASA AD 2021–0014).
(1) Where EASA AD 2021–0014 refers to its effective date, this AD requires using the effective date of this AD.
(2) Where paragraph (2) of EASA AD 2021–0014 requires additional actions for bulging “between 0.5 mm and 3 mm,” this AD requires those additional actions for bulging 0.5 mm or more and 3.0 mm or less.
(3) The “Remarks” section of EASA AD 2021–0014 does not apply to this AD.
(4) Paragraph (5) of EASA AD 2021–0014 specifies to report inspection results within a certain compliance time. For this AD, report the inspection results of each inspection accomplished in this AD at the applicable time specified in paragraph (h)(4)(i) or (ii) of this AD.
(i) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection.
(ii) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD.
The following provisions also apply to this AD:
(1)
(2)
For more information about this AD, contact Tom Rodriguez, Aerospace Engineer, Large Aircraft Section, International Validation Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3226; email
(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) European Union Aviation Safety Agency (EASA) AD 2021–0014, dated January 13, 2021.
(ii) [Reserved]
(3) For EASA AD 2021–0014, contact EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 8999 000; email
(4) You may view this material at the FAA, Airworthiness Products Section, Operational Safety Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. This material may be found in the AD docket on the internet at
(5) You may view this material that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, email