82 FR 33004 - Airworthiness Directives; Fokker Services B.V. Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 137 (July 19, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 137 (July 19, 2017)
| Page Range | 33004-33007 | |
| FR Document | 2017-14583 |
[Federal Register Volume 82, Number 137 (Wednesday, July 19, 2017)] [Rules and Regulations] [Pages 33004-33007] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-14583] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-9389; Directorate Identifier 2014-NM-153-AD; Amendment 39-18953; AD 2017-14-09] 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 F28 Mark 0100 airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain wing fuel tank access panels are subject to widespread fatigue damage (WFD). This AD requires replacement of affected access panels and modification of the coamings of the associated access holes. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective August 23, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 23, 2017. ADDRESSES: For 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: [email protected]; Internet: http://www.myfokkerfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., [[Page 33005]] Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 9389. 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-2016- 9389; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800-647-5527) is Docket Management Facility, 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 Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 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 by adding an AD that would apply to all Fokker Services B.V. Model F28 Mark 0100 airplanes. The NPRM published in the Federal Register on November 17, 2016 (81 FR 81018) (``the NPRM''). The NPRM was prompted by an evaluation by the DAH indicating that certain wing fuel tank access panels are subject to WFD. The NPRM proposed to require replacement of affected access panels and modification of the coamings of the associated access holes. We are issuing this AD to prevent fatigue cracking in the wing structure, which could result in reduced structural integrity of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2014-0158, dated July 7, 2014 (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 Mark 0100 series airplanes. The MCAI states: Based on findings on test articles, fatigue-induced cracks may develop in the coamings of certain wing fuel tank access panels Part Number (P/N) D12395-403 and P/N D12450-403, installed on Fokker F28 Mark 0100 aeroplanes. To ensure the continued structural integrity with respect to fatigue, repetitive inspections were included in the Airworthiness Limitations Section (ALS) of the Instructions for Continued Airworthiness. Fokker Services also developed precautionary measures to reduce stress loads in the affected areas by replacement of the affected access panels with new panels, P/N D19701-401 and P/N D19701-403, having thinner skin, and a modification by introducing internal patches to the coamings of the affected access holes. These precautionary measures were introduced with Service Bulletins (SB) SBF100-57-027 and SBF100-57-028. As part of the Widespread Fatigue Damage re-evaluation, it was concluded that repetitive inspections through the ALS do not provide a sufficient level of protection against the fatigue-induced cracks. This condition, if not corrected, would affect the structural integrity of the lower wing skins of both outer wings in the areas surrounding the affected fuel tank access panels. For the reasons described above, this [EASA] AD requires replacement of the affected access panels and modification of the coamings of these access holes. Post-modification inspection requirements depend on the actual number of flight cycles accumulated at the moment of modification. Related detailed information is provided in SBF100-57-027 and SBF100-57-028, as well as in Fokker Services ALS Report SE-623 Issue 12. Fokker Services All Operators Message AOF100.178#05 provides additional information concerning the subject addressed by this [EASA] AD. 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-2016- 9389. In the NPRM, we incorrectly cited EASA AD 2016-0125, dated June 21, 2016. We do not address EASA AD 2016-0125 or its contents in this AD. 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. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this AD 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 correcting 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 the following service information: Fokker Service Bulletin SBF100-57-027, Revision 2, dated December 11, 2013, which provides instructions to replace certain fuel tank access panels. Fokker Service Bulletin SBF100-57-028, Revision 2, dated December 11, 2013, which provides instructions to modify the coamings of certain fuel tank access holes. 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 15 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Replacement and modification.......... 510 work-hours x $85 per $45,500 $88,850 $1,332,750 hour = $43,350. ---------------------------------------------------------------------------------------------------------------- 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 [[Page 33006]] 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. 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): 2017-14-09 Fokker Services B.V.: Amendment 39-18953; Docket No. FAA- 2016-9389; Directorate Identifier 2014-NM-153-AD. (a) Effective Date This AD is effective August 23, 2017. (b) Affected ADs None. (c) Applicability This AD applies to Fokker Services B.V. Model F28 Mark 0100 airplanes, certificated in any category, all serial numbers. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by an evaluation by the design approval holder indicating that certain wing fuel tank access panels are subject to widespread fatigue damage. We are issuing this AD to prevent fatigue cracking in the wing structure, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Modification and Replacement Within 63,000 flight cycles since first flight of the airplane, or within 90 days after the effective date of this AD, whichever occurs later, accomplish the actions specified in paragraphs (g)(1) and (g)(2) of this AD, as applicable. (1) For airplanes identified in Fokker Service Bulletin SBF100- 57-028, Revision 2, dated December 11, 2013: Modify the coamings of the fuel tank access holes at the access panel locations identified in, and in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-57-028, Revision 2, dated December 11, 2013. (2) For airplanes identified in Fokker Service Bulletin SBF100- 57-027, Revision 2, dated December 11, 2013: Replace access panels having part number D12395-403 and D12450-403 with new panels having part number D19701-401 and D19701-403, at the access panel locations identified in, and in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100-57-027, Revision 2, dated December 11, 2013. (h) Parts Installation Prohibition (1) For airplanes that, on the effective date of this AD, have an access panel with part number D12395-403 or D12450-403 installed at any of the affected locations: After accomplishing the actions required by paragraphs (g)(1) and (g)(2) of this AD, as applicable, no person may install, on any airplane, access panels having part number D12395-403 or D12450-403 at any access panel location as identified in Fokker Service Bulletin SBF100-57-027, Revision 2, dated December 11, 2013. (2) For airplanes that, on the effective date of this AD, do not have an access panel with part number D12395-403 or D12450-403 installed at any of the affected locations: As of the effective date of this AD, no person may install, on any airplane, access panels having part number D12395-403 or D12450-403 at any access panel location as identified in Fokker Service Bulletin SBF100-57-027, Revision 2, dated December 11, 2013. (i) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraph (g)(1) of this AD, if those actions were performed before the effective date of this AD using the service information specified in paragraph (i)(1)(i) or (i)(1)(ii) of this AD. (i) Fokker Service Bulletin SBF100-57-028, dated May 2, 1994. (ii) Fokker Service Bulletin SBF100-57-028, Revision 1, dated November 1, 1994. (2) This paragraph provides credit for actions required by paragraph (g)(2) of this AD, if those actions were performed before the effective date of this AD using the service information specified in paragraph (i)(2)(i) or (i)(2)(ii) of this AD. (i) Fokker Service Bulletin SBF100-57-027, dated September 13, 1993. (ii) Fokker Service Bulletin SBF100-57-027, Revision 1, dated May 2, 1994. (j) 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. 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 manager of the International Branch, send it to the attention of the person identified in paragraph (k)(2) of this AD. Information may be emailed to: [email protected]. 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 Branch, ANM-116, Transport Airplane Directorate, 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 2014-0158, dated July 7, 2014, 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-2016-9389. (2) For more information about this AD, contact Tom Rodriguez, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone 425-227-1137; fax 425-227-1149. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (l)(3) and (l)(4) of this AD. [[Page 33007]] (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 SBF100-57-027, Revision 2, dated December 11, 2013. (ii) Fokker Service Bulletin SBF100-57-028, Revision 2, dated December 11, 2013. (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: [email protected]; Internet: http://www.myfokkerfleet.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (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 Renton, Washington, on July 3, 2017. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-14583 Filed 7-18-17; 8:45 am] BILLING CODE 4910-13-P
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(g) Repetitive Inspections standards district office/certificate holding 1601 Lind Avenue SW., Renton, WA. For
Before exceeding 36,900 total flight cycles district office. information on the availability of this
since first flight of the airplane, or within (2) Contacting the Manufacturer: For any material at the FAA, call 425–227–1221.
2,100 flight cycles after the effective date of requirement in this AD to obtain corrective (5) You may view this service information
this AD, whichever occurs later: Do a actions from a manufacturer, the action must that is incorporated by reference at the
detailed inspection for cracking of the frame be accomplished using a method approved National Archives and Records
to cabin floor beam junction on the aft and by the Manager, International Branch, ANM– Administration (NARA). For information on
forward sides at frame (FR) 35.1 and FR 35.2 116, Transport Airplane Directorate, FAA; or the availability of this material at NARA, call
on the left-hand and right-hand sides, in EASA; or Airbus’s EASA DOA. If approved 202–741–6030, or go to: http://
accordance with the Accomplishment by the DOA, the approval must include the www.archives.gov/federal-register/cfr/ibr-
DOA-authorized signature. locations.html.
Instructions of the Airbus service information
(3) Required for Compliance (RC): Except
specified in paragraphs (g)(1), (g)(2), (g)(3), Issued in Renton, Washington, on June 29,
as required by paragraph (h) of this AD: If
and (g)(4) of this AD. Repeat the inspection 2017.
any service information contains procedures
of the frame to cabin floor beam junction on
or tests that are identified as RC, those Michael Kaszycki,
the aft and forward sides at FR 35.1 and FR
procedures and tests must be done to comply Acting Manager, Transport Airplane
35.2 on the left-hand and right-hand sides
with this AD; any procedures or tests that are Directorate, Aircraft Certification Service.
thereafter at intervals not to exceed 15,300
not identified as RC are recommended. Those
flight cycles. [FR Doc. 2017–14588 Filed 7–18–17; 8:45 am]
procedures and tests that are not identified
(1) Airbus Service Bulletin A320–53–1317, BILLING CODE 4910–13–P
as RC may be deviated from using accepted
dated December 15, 2015 (FR 35.1 right-hand
methods in accordance with the operator’s
side).
maintenance or inspection program without
(2) Airbus Service Bulletin A320–53–1318, DEPARTMENT OF TRANSPORTATION
obtaining approval of an AMOC, provided
dated October 9, 2015 (FR 35.1 left-hand
the procedures and tests identified as RC can
side). Federal Aviation Administration
be done and the airplane can be put back in
(3) Airbus Service Bulletin A320–53–1319,
an airworthy condition. Any substitutions or
dated October 9, 2015 (FR 35.2 right-hand
changes to procedures or tests identified as 14 CFR Part 39
side).
RC require approval of an AMOC.
(4) Airbus Service Bulletin A320–53–1320, [Docket No. FAA–2016–9389; Directorate
dated October 9, 2015 (FR 35.2 left-hand (j) Related Information Identifier 2014–NM–153–AD; Amendment
side). (1) Refer to Mandatory Continuing 39–18953; AD 2017–14–09]
(h) Repair Airworthiness Information (MCAI) EASA AD
RIN 2120–AA64
2016–0105, dated June 6, 2016, for related
If any crack is found during any inspection
information. This MCAI may be found in the
required by paragraph (g) of this AD: Before
AD docket on the Internet at http:// Airworthiness Directives; Fokker
further flight, repair using a method www.regulations.gov by searching for and Services B.V. Airplanes
approved by the Manager, International locating Docket No. FAA–2016–9498.
Branch, ANM–116, Transport Airplane AGENCY: Federal Aviation
(2) For more information about this AD,
Directorate, FAA; or the European Aviation contact Sanjay Ralhan, Aerospace Engineer, Administration (FAA), Department of
Safety Agency (EASA); or Airbus’s EASA International Branch, ANM–116, Transport Transportation (DOT).
Design Organization Approval (DOA). Airplane Directorate, FAA, 1601 Lind ACTION: Final rule.
Although the service information specified in Avenue SW., Renton, WA 98057–3356;
paragraph (g) of this AD specifies to contact telephone: 425–227–1405; fax: 425–227– SUMMARY: We are adopting a new
Airbus for repair instructions, and specifies 1149. Information may be emailed to: 9- airworthiness directive (AD) for all
that action as ‘‘RC’’ (Required for ANM-116-AMOC-REQUESTS@faa.gov. Fokker Services B.V. Model F28 Mark
Compliance), this AD requires repair as (3) Service information identified in this
specified in this paragraph. Repair of an 0100 airplanes. This AD was prompted
AD that is not incorporated by reference is by an evaluation by the design approval
airplane as required by this paragraph does available at the addresses specified in
not constitute terminating action for the paragraphs (k)(3) and (k)(4) of this AD.
holder (DAH) indicating that certain
repetitive actions required by paragraph (g) of wing fuel tank access panels are subject
this AD, unless otherwise specified in the (k) Material Incorporated by Reference to widespread fatigue damage (WFD).
instructions provided by the Manager, (1) The Director of the Federal Register This AD requires replacement of
International Branch, ANM–116, Transport approved the incorporation by reference affected access panels and modification
Airplane Directorate, FAA; or EASA; or (IBR) of the service information listed in this of the coamings of the associated access
Airbus’s EASA DOA. paragraph under 5 U.S.C. 552(a) and 1 CFR holes. We are issuing this AD to address
part 51.
(i) Other FAA AD Provisions the unsafe condition on these products.
(2) You must use this service information
The following provisions also apply to this as applicable to do the actions required by DATES: This AD is effective August 23,
AD: this AD, unless this AD specifies otherwise. 2017.
(1) Alternative Methods of Compliance (i) Airbus Service Bulletin A320–53–1317, The Director of the Federal Register
(AMOCs): The Manager, International dated December 15, 2015. approved the incorporation by reference
Branch, ANM–116, Transport Airplane (ii) Airbus Service Bulletin A320–53–1318, of certain publications listed in this AD
Directorate, FAA, has the authority to dated October 9, 2015.
approve AMOCs for this AD, if requested
as of August 23, 2017.
(iii) Airbus Service Bulletin A320–53–
using the procedures found in 14 CFR 39.19. 1319, dated October 9, 2015. ADDRESSES: For service information
In accordance with 14 CFR 39.19, send your (iv) Airbus Service Bulletin A320–53– identified in this final rule, contact
request to your principal inspector or local 1320, dated October 9, 2015. Fokker Services B.V., Technical
Flight Standards District Office, as (3) For service information identified in Services Dept., P.O. Box 1357, 2130 EL
appropriate. If sending information directly this AD, contact Airbus, Airworthiness Hoofddorp, the Netherlands; telephone:
to the International Branch, send it to the
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Office—EIAS, 1 Rond Point Maurice +31 (0)88–6280–350; fax: +31 (0)88–
attention of the person identified in Bellonte, 31707 Blagnac Cedex, France; 6280–111; email: technicalservices@
paragraph (j)(2) of this AD. Information may telephone: +33 5 61 93 36 96; fax: +33 5 61
be emailed to: 9-ANM-116-AMOC- 93 44 51; email: account.airworth-
fokker.com; Internet: http://
REQUESTS@faa.gov. Before using any eas@airbus.com; Internet: http:// www.myfokkerfleet.com. You may view
approved AMOC, notify your appropriate www.airbus.com. this referenced service information at
principal inspector, or lacking a principal (4) You may view this service information the FAA, Transport Airplane
inspector, the manager of the local flight at the FAA, Transport Airplane Directorate, Directorate, 1601 Lind Avenue SW.,
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Renton, WA. For information on the The European Aviation Safety Agency You may examine the MCAI in the
availability of this material at the FAA, (EASA), which is the Technical Agent AD docket on the Internet at http://
call 425–227–1221. It is also available for the Member States of the European www.regulations.gov by searching for
on the Internet at http:// Union, has issued EASA AD 2014–0158, and locating Docket No. FAA–2016–
www.regulations.gov by searching for dated July 7, 2014 (referred to after this 9389. In the NPRM, we incorrectly cited
and locating Docket No. FAA–2016– as the Mandatory Continuing EASA AD 2016–0125, dated June 21,
9389. Airworthiness Information, or ‘‘the 2016. We do not address EASA AD
Examining the AD Docket MCAI’’), to correct an unsafe condition 2016–0125 or its contents in this AD.
for all Fokker Services B.V. Model F28
You may examine the AD docket on Comments
Mark 0100 series airplanes. The MCAI
the Internet at http:// states: We gave the public the opportunity to
www.regulations.gov by searching for participate in developing this AD. We
and locating Docket No. FAA–2016– Based on findings on test articles, fatigue-
induced cracks may develop in the coamings received no comments on the NPRM or
9389; or in person at the Docket on the determination of the cost to the
of certain wing fuel tank access panels Part
Management Facility between 9 a.m. Number (P/N) D12395–403 and P/N D12450– public.
and 5 p.m., Monday through Friday, 403, installed on Fokker F28 Mark 0100
except Federal holidays. The AD docket aeroplanes.
Conclusion
contains this AD, the regulatory To ensure the continued structural We reviewed the relevant data and
evaluation, any comments received, and integrity with respect to fatigue, repetitive determined that air safety and the
other information. The street address for inspections were included in the public interest require adopting this AD
the Docket Office (telephone 800–647– Airworthiness Limitations Section (ALS) of as proposed except for minor editorial
5527) is Docket Management Facility, the Instructions for Continued Airworthiness.
changes. We have determined that these
U.S. Department of Transportation, Fokker Services also developed
precautionary measures to reduce stress minor changes:
Docket Operations, M–30, West
loads in the affected areas by replacement of • Are consistent with the intent that
Building Ground Floor, Room W12–140,
the affected access panels with new panels, was proposed in the NPRM for
1200 New Jersey Avenue SE.,
P/N D19701–401 and P/N D19701–403, correcting the unsafe condition; and
Washington, DC 20590.
having thinner skin, and a modification by • Do not add any additional burden
FOR FURTHER INFORMATION CONTACT: Tom introducing internal patches to the coamings upon the public than was already
Rodriguez, Aerospace Engineer, of the affected access holes. proposed in the NPRM.
International Branch, ANM–116, These precautionary measures were
Transport Airplane Directorate, FAA, introduced with Service Bulletins (SB) Related Service Information Under 1
1601 Lind Avenue SW., Renton, WA SBF100–57–027 and SBF100–57–028. As CFR Part 51
98057–3356; telephone 425–227–1137; part of the Widespread Fatigue Damage re-
evaluation, it was concluded that repetitive Fokker Services B.V. has issued the
fax 425–227–1149.
inspections through the ALS do not provide following service information:
SUPPLEMENTARY INFORMATION:
a sufficient level of protection against the • Fokker Service Bulletin SBF100–
Discussion fatigue-induced cracks. 57–027, Revision 2, dated December 11,
We issued a notice of proposed This condition, if not corrected, would 2013, which provides instructions to
affect the structural integrity of the lower replace certain fuel tank access panels.
rulemaking (NPRM) to amend 14 CFR wing skins of both outer wings in the areas
part 39 by adding an AD that would • Fokker Service Bulletin SBF100–
surrounding the affected fuel tank access
apply to all Fokker Services B.V. Model 57–028, Revision 2, dated December 11,
panels.
F28 Mark 0100 airplanes. The NPRM For the reasons described above, this 2013, which provides instructions to
published in the Federal Register on [EASA] AD requires replacement of the modify the coamings of certain fuel tank
November 17, 2016 (81 FR 81018) (‘‘the affected access panels and modification of access holes.
NPRM’’). The NPRM was prompted by the coamings of these access holes. This service information is reasonably
an evaluation by the DAH indicating Post-modification inspection requirements available because the interested parties
that certain wing fuel tank access panels depend on the actual number of flight cycles have access to it through their normal
are subject to WFD. The NPRM accumulated at the moment of modification. course of business or by the means
proposed to require replacement of Related detailed information is provided in identified in the ADDRESSES section.
SBF100–57–027 and SBF100–57–028, as well
affected access panels and modification as in Fokker Services ALS Report SE–623 Costs of Compliance
of the coamings of the associated access Issue 12.
holes. We are issuing this AD to prevent Fokker Services All Operators Message We estimate that this AD affects 15
fatigue cracking in the wing structure, AOF100.178#05 provides additional airplanes of U.S. registry.
which could result in reduced structural information concerning the subject addressed We estimate the following costs to
integrity of the airplane. by this [EASA] AD. comply with this AD:
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Replacement and modification ....................... 510 work-hours × $85 per hour = $43,350 .... $45,500 $88,850 $1,332,750
mstockstill on DSK30JT082PROD with RULES
Authority for This Rulemaking section 106, describes the authority of We are issuing this rulemaking under
the FAA Administrator. ‘‘Subtitle VII: the authority described in ‘‘Subtitle VII,
Title 49 of the United States Code Aviation Programs,’’ describes in more Part A, Subpart III, Section 44701:
specifies the FAA’s authority to issue detail the scope of the Agency’s General requirements.’’ Under that
rules on aviation safety. Subtitle I, authority. section, Congress charges the FAA with
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promoting safe flight of civil aircraft in (c) Applicability (i) Credit for Previous Actions
air commerce by prescribing regulations This AD applies to Fokker Services B.V. (1) This paragraph provides credit for
for practices, methods, and procedures Model F28 Mark 0100 airplanes, certificated actions required by paragraph (g)(1) of this
the Administrator finds necessary for in any category, all serial numbers. AD, if those actions were performed before
safety in air commerce. This regulation the effective date of this AD using the service
(d) Subject information specified in paragraph (i)(1)(i) or
is within the scope of that authority
because it addresses an unsafe condition Air Transport Association (ATA) of (i)(1)(ii) of this AD.
America Code 57, Wings. (i) Fokker Service Bulletin SBF100–57–
that is likely to exist or develop on
028, dated May 2, 1994.
products identified in this rulemaking (e) Reason (ii) Fokker Service Bulletin SBF100–57–
action. This AD was prompted by an evaluation by 028, Revision 1, dated November 1, 1994.
Regulatory Findings the design approval holder indicating that (2) This paragraph provides credit for
certain wing fuel tank access panels are actions required by paragraph (g)(2) of this
We determined that this AD will not subject to widespread fatigue damage. We are AD, if those actions were performed before
have federalism implications under issuing this AD to prevent fatigue cracking in the effective date of this AD using the service
Executive Order 13132. This AD will the wing structure, which could result in information specified in paragraph (i)(2)(i) or
not have a substantial direct effect on reduced structural integrity of the airplane. (i)(2)(ii) of this AD.
the States, on the relationship between (i) Fokker Service Bulletin SBF100–57–
(f) Compliance 027, dated September 13, 1993.
the national government and the States, Comply with this AD within the (ii) Fokker Service Bulletin SBF100–57–
or on the distribution of power and compliance times specified, unless already 027, Revision 1, dated May 2, 1994.
responsibilities among the various done.
levels of government. (j) Other FAA AD Provisions
(g) Modification and Replacement The following provisions also apply to this
For the reasons discussed above, I
certify that this AD: Within 63,000 flight cycles since first flight AD:
of the airplane, or within 90 days after the (1) Alternative Methods of Compliance
1. Is not a ‘‘significant regulatory (AMOCs): The Manager, International
effective date of this AD, whichever occurs
action’’ under Executive Order 12866; Branch, ANM–116, Transport Airplane
later, accomplish the actions specified in
2. Is not a ‘‘significant rule’’ under the paragraphs (g)(1) and (g)(2) of this AD, as Directorate, FAA, has the authority to
DOT Regulatory Policies and Procedures applicable. approve AMOCs for this AD, if requested
(44 FR 11034, February 26, 1979); (1) For airplanes identified in Fokker using the procedures found in 14 CFR 39.19.
3. Will not affect intrastate aviation in Service Bulletin SBF100–57–028, Revision 2, In accordance with 14 CFR 39.19, send your
Alaska; and dated December 11, 2013: Modify the request to your principal inspector or local
coamings of the fuel tank access holes at the Flight Standards District Office, as
4. Will not have a significant appropriate. If sending information directly
access panel locations identified in, and in
economic impact, positive or negative, to the manager of the International Branch,
accordance with the Accomplishment
on a substantial number of small entities Instructions of Fokker Service Bulletin send it to the attention of the person
under the criteria of the Regulatory SBF100–57–028, Revision 2, dated December identified in paragraph (k)(2) of this AD.
Flexibility Act. 11, 2013. Information may be emailed to: 9-ANM-116-
(2) For airplanes identified in Fokker AMOC-REQUESTS@faa.gov. Before using
List of Subjects in 14 CFR Part 39 any approved AMOC, notify your appropriate
Service Bulletin SBF100–57–027, Revision 2,
Air transportation, Aircraft, Aviation principal inspector, or lacking a principal
dated December 11, 2013: Replace access
inspector, the manager of the local flight
safety, Incorporation by reference, panels having part number D12395–403 and
standards district office/certificate holding
Safety. D12450–403 with new panels having part
district office.
number D19701–401 and D19701–403, at the
Adoption of the Amendment (2) Contacting the Manufacturer: For any
access panel locations identified in, and in
requirement in this AD to obtain corrective
Accordingly, under the authority accordance with the Accomplishment actions from a manufacturer, the action must
Instructions of Fokker Service Bulletin
delegated to me by the Administrator, be accomplished using a method approved
SBF100–57–027, Revision 2, dated December by the Manager, International Branch, ANM–
the FAA amends 14 CFR part 39 as 11, 2013.
follows: 116, Transport Airplane Directorate, FAA; or
(h) Parts Installation Prohibition the European Aviation Safety Agency
PART 39—AIRWORTHINESS (EASA); or Fokker Services B.V.’s EASA
(1) For airplanes that, on the effective date
DIRECTIVES Design Organization Approval (DOA). If
of this AD, have an access panel with part
approved by the DOA, the approval must
number D12395–403 or D12450–403 include the DOA-authorized signature.
■ 1. The authority citation for part 39 installed at any of the affected locations:
continues to read as follows: After accomplishing the actions required by (k) Related Information
Authority: 49 U.S.C. 106(g), 40113, 44701. paragraphs (g)(1) and (g)(2) of this AD, as (1) Refer to Mandatory Continuing
applicable, no person may install, on any Airworthiness Information (MCAI) EASA AD
§ 39.13 [Amended] airplane, access panels having part number 2014–0158, dated July 7, 2014, for related
D12395–403 or D12450–403 at any access information. This MCAI may be found in the
■ 2. The FAA amends § 39.13 by adding panel location as identified in Fokker Service AD docket on the Internet at http://
the following new airworthiness Bulletin SBF100–57–027, Revision 2, dated www.regulations.gov by searching for and
directive (AD): December 11, 2013. locating Docket No. FAA–2016–9389.
2017–14–09 Fokker Services B.V.: (2) For airplanes that, on the effective date (2) For more information about this AD,
Amendment 39–18953; Docket No. of this AD, do not have an access panel with contact Tom Rodriguez, Aerospace Engineer,
part number D12395–403 or D12450–403 International Branch, ANM–116, Transport
mstockstill on DSK30JT082PROD with RULES
FAA–2016–9389; Directorate Identifier
2014–NM–153–AD. installed at any of the affected locations: As Airplane Directorate, FAA, 1601 Lind
of the effective date of this AD, no person Avenue SW., Renton, WA 98057–3356;
(a) Effective Date may install, on any airplane, access panels telephone 425–227–1137; fax 425–227–1149.
This AD is effective August 23, 2017. having part number D12395–403 or D12450– (3) Service information identified in this
403 at any access panel location as identified AD that is not incorporated by reference is
(b) Affected ADs in Fokker Service Bulletin SBF100–57–027, available at the addresses specified in
None. Revision 2, dated December 11, 2013. paragraphs (l)(3) and (l)(4) of this AD.
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![Federal Register / Vol. 82, No. 137 / Wednesday, July 19, 2017 / Rules and Regulations 33007
(l) Material Incorporated by Reference the cover assembly of the heel rest for Register on December 20, 2016 (81 FR
(1) The Director of the Federal Register both the Captain and the First Officer’s 92753). The NPRM was prompted by a
approved the incorporation by reference rudder pedals, and corrective action if report of an aborted takeoff because the
(IBR) of the service information listed in this necessary. We are issuing this AD to rudder pedals were not operating
paragraph under 5 U.S.C. 552(a) and 1 CFR address the unsafe condition on these correctly. Investigation revealed a
part 51. products. protruding screw in the rudder pedal
(2) You must use this service information heel rest adjacent to the pedals. It was
as applicable to do the actions required by DATES: This AD is effective August 23,
2017. determined that the screws in the cover
this AD, unless this AD specifies otherwise.
(i) Fokker Service Bulletin SBF100–57– The Director of the Federal Register assembly of the heel rest for both the
027, Revision 2, dated December 11, 2013. approved the incorporation by reference Captain and the First Officer’s rudder
(ii) Fokker Service Bulletin SBF100–57– of a certain publication listed in this AD pedals might not have been properly
028, Revision 2, dated December 11, 2013. as of August 23, 2017. torqued. The NPRM proposed to require
(3) For service information identified in a torque check of the screws in the cover
ADDRESSES: For service information
this AD, contact Fokker Services B.V., assembly of the heel rest for both the
Technical Services Dept., P.O. Box 1357, identified in this final rule, contact
Captain and the First Officer’s rudder
2130 EL Hoofddorp, the Netherlands; Boeing Commercial Airplanes,
pedals, and corrective action if
telephone: +31 (0)88–6280–350; fax: +31 Attention: Data & Services Management,
necessary. We are issuing this AD to
(0)88–6280–111; email: technicalservices@ P.O. Box 3707, MC 2H–65, Seattle, WA
detect and correct a protruding screw in
fokker.com; Internet: http:// 98124–2207; telephone 206–544–5000,
www.myfokkerfleet.com. the cover assembly of the heel rest of a
extension 1; fax 206–766–5680; Internet
(4) You may view this service information rudder pedal. A protruding screw could
https://www.myboeingfleet.com. You
at the FAA, Transport Airplane Directorate, restrict rudder pedal motion and reduce
may view this referenced service
1601 Lind Avenue SW., Renton, WA. For differential braking control during
information on the availability of this
information at the FAA, Transport
takeoff or landing, which could cause a
material at the FAA, call 425–227–1221. Airplane Directorate, 1601 Lind Avenue
high speed runway excursion.
(5) You may view this service information SW., Renton, WA. For information on
that is incorporated by reference at the the availability of this material at the Comments
National Archives and Records FAA, call 425–227–1221. It is also We gave the public the opportunity to
Administration (NARA). For information on available on the Internet at http:// participate in developing this AD. The
the availability of this material at NARA, call www.regulations.gov by searching for
202–741–6030, or go to: http://
following presents the comments
and locating Docket No. FAA–2016– received on the NPRM and the FAA’s
www.archives.gov/federal-register/cfr/ibr- 9506.
locations.html. response to each comment.
Issued in Renton, Washington, on July 3, Examining the AD Docket Support for the NPRM
2017. You may examine the AD docket on Boeing, Air Line Pilots Association,
Dionne Palermo, the Internet at http:// International, and Tyler Myers
Acting Manager, Transport Airplane www.regulations.gov by searching for supported the intent of the NPRM.
Directorate, Aircraft Certification Service. and locating Docket No. FAA–2016–
[FR Doc. 2017–14583 Filed 7–18–17; 8:45 am] 9506; or in person at the Docket Request To Allow Credit for Previously
BILLING CODE 4910–13–P Management Facility between 9 a.m. Accomplished Actions
and 5 p.m., Monday through Friday, United Airlines noted that the NPRM
except Federal holidays. The AD docket did not address whether or not the final
DEPARTMENT OF TRANSPORTATION contains this AD, the regulatory rule would allow operators to take
evaluation, any comments received, and credit for accomplishment of the actions
Federal Aviation Administration other information. The address for the in Boeing Alert Service Bulletin 737–
Docket Office (phone: 800–647–5527) is 25A1732, Revision 1, dated August 15,
14 CFR Part 39 Docket Management Facility, U.S. 2016 (‘‘BASB 737–25A1732, Revision
[Docket No. FAA–2016–9506; Directorate Department of Transportation, Docket 1’’), if completed prior to the effective
Identifier 2016–NM–090–AD; Amendment Operations, M–30, West Building date of the final rule. We infer that the
39–18957; AD 2017–14–13] Ground Floor, Room W12–140, 1200 commenter is requesting that the final
New Jersey Avenue SE., Washington, rule include a statement that
RIN 2120–AA64 DC 20590. accomplishment of the actions specified
Airworthiness Directives; The Boeing FOR FURTHER INFORMATION CONTACT: in BASB 737–25A1732, Revision 1,
Company Airplanes Kelly McGuckin, Aerospace Engineer, prior to the effective date of the final
Systems and Equipment Branch, ANM– rule is acceptable for compliance with
AGENCY: Federal Aviation 130S, FAA, Seattle Aircraft Certification the requirements of the final rule.
Administration (FAA), DOT. Office (ACO), 1601 Lind Avenue SW., We agree with the commenter that
ACTION: Final rule. Renton, WA 98057–3356; phone: 425– operators should be able to take credit
917–6490; fax: 425–917–6590; email: for accomplishment of the actions in
SUMMARY: We are adopting a new Kelly.McGuckin@faa.gov. BASB 737–25A1732, Revision 1, prior
airworthiness directive (AD) for certain SUPPLEMENTARY INFORMATION: to the effective date of this AD. This
The Boeing Company Model 737–600, allowance was provided in paragraph (f)
–700, –700C, –800, –900, and –900ER Discussion of the proposed AD in the statement
mstockstill on DSK30JT082PROD with RULES
series airplanes. This AD was prompted We issued a notice of proposed ‘‘Comply with this AD within the
by a report of an aborted takeoff because rulemaking (NPRM) to amend 14 CFR compliance times specified unless
the rudder pedals were not operating part 39 by adding an AD that would already done.’’ However, since the
correctly. Investigation revealed a apply to certain The Boeing Company NPRM was issued, Boeing has
protruding screw in the rudder pedal Model 737–600, –700, –700C, –800, published, and we have reviewed,
heel rest adjacent to the pedals. This AD –900, and –900ER series airplanes. The Boeing Alert Service Bulletin 737–
requires a torque check of the screws in NPRM published in the Federal 25A1732, Revision 2, dated April 13,
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Document Created: 2017-07-19 06:17:09
Document Modified: 2017-07-19 06:17:09
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective August 23, 2017. | |
| Contact | Tom Rodriguez, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1137; fax 425-227-1149. | |
| FR Citation | 82 FR 33004 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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