81 FR 26673 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 86 (May 4, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 86 (May 4, 2016)
| Page Range | 26673-26675 | |
| FR Document | 2016-10160 |
[Federal Register Volume 81, Number 86 (Wednesday, May 4, 2016)] [Rules and Regulations] [Pages 26673-26675] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-10160] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-3982; Directorate Identifier 2015-NM-098-AD; Amendment 39-18503; AD 2016-09-05] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 717-200 airplanes. This AD was prompted by multiple reports of the vertical stabilizer leading edge showing signs of fastener distress. This AD requires a detailed inspection for any distress of the vertical stabilizer leading edge skin, and related investigative and corrective actions if necessary. This AD also requires, for certain airplanes, repetitive detailed inspections of the spar cap for any loose and missing fasteners, repetitive eddy current testing high frequency (ETHF) and radiographic testing (RT) inspections of the spar cap for any crack, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct any crack in the vertical stabilizer leading edge and front spar cap, which may result in the structure becoming unable to support limit load, and may lead to the loss of the vertical stabilizer. DATES: This AD is effective June 8, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 8, 2016. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001; telephone: 206-544-5000, extension 2; fax: 206-766-5683; Internet: https://www.myboeingfleet.com. You may view this referenced 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-3982. 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-2015- 3982; 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 address for the Docket Office (phone: 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: Eric Schrieber, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5348; fax: 562-627-5210; email: [email protected]. 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 certain The Boeing Company Model 717-200 airplanes. The NPRM published in the Federal Register on October 6, 2015 (80 FR 60307) (``the NPRM''). The NPRM was prompted by multiple reports of the vertical stabilizer leading edge showing signs of fastener distress. The NPRM proposed to require a detailed inspection for any distress of the vertical stabilizer leading edge skin, and related investigative and corrective actions if necessary. The NPRM also proposed to require, for certain airplanes, repetitive detailed inspections of the spar cap for any loose and missing fasteners, repetitive ETHF and RT inspections of the spar cap for any crack, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct any crack in the vertical stabilizer leading edge and front spar cap, which may result in the structure becoming unable to support limit load, and may lead to the loss of the vertical stabilizer. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Boeing and an anonymous commenter indicated their support for the NPRM. Request To Add Credit for Previous Actions Boeing requested that we add a ``Credit for Previous Actions'' paragraph to the proposed AD that would give credit for prior accomplishment of the initial inspection in paragraph (g) of the NPRM. Boeing stated that operator structural inspection credit has been incorporated as a precedent in previous ADs. We agree with the commenter's request. Boeing MOM-MOM-14-0437- 01B(R1), dated July 3, 2014, provides the same action and level of safety for the initial inspection specified in this AD. We have revised this AD by adding new paragraph (j) of this AD to give credit for the initial inspection in paragraph (g) of this AD, if that inspection was performed before the effective date of this AD using Boeing MOM-MOM-14- 0437-01B(R1), dated July 3, 2014. We have redesignated the remaining paragraphs accordingly. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the change described previously [[Page 26674]] and minor editorial changes. We have determined that these minor changes:[Agr]re 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. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 717-55A0012, dated June 12, 2015. The service information describes procedures for a detailed inspection for any distress of the vertical stabilizer leading edge skin, a detailed inspection for any loose and missing fasteners of the spar cap, ETHF and RT inspections of the spar cap for any crack, and related investigative and corrective actions. 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 106 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspections for distress......... 11 work-hours x $85 $0 $935 per inspection $99,110 per per hour = $935 cycle. inspection cycle. per inspection cycle. Repetitive inspections for 7 work-hours x $85 0 595 per inspection 63,070 per cracking and loose and missing per hour = $595 cycle. inspection cycle. fasteners. per inspection cycle. ---------------------------------------------------------------------------------------------------------------- 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. 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 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): 2016-09-05 The Boeing Company: Amendment 39-18503; Docket No. FAA- 2015-3982; Directorate Identifier 2015-NM-098-AD. (a) Effective Date This AD is effective June 8, 2016. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 717-200 airplanes, certificated in any category, as specified in Boeing Alert Service Bulletin 717-55A0012, dated June 12, 2015. (d) Subject Air Transport Association (ATA) of America Code 55, Stabilizers. (e) Unsafe Condition This AD was prompted by multiple reports of the vertical stabilizer leading edge showing signs of fastener distress. We are issuing this AD to detect and correct any crack in the vertical stabilizer leading edge and front spar cap, which may result in the structure becoming unable to support limit load, and may lead to the loss of the vertical stabilizer. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Initial Inspection Except as required by paragraph (i)(1) of this AD, at the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 717-55A0012, dated June 12, 2015: Do a detailed inspection for any distress of the vertical stabilizer leading edge skin and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 717-55A0012, dated June 12, 2015, except as required by paragraph (i)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. (h) Repetitive Inspections For all airplanes on which no cracking was found during any related investigative action required by paragraph (g) of this AD: At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 717-55A0012, dated June 12, 2015, do the actions specified in paragraphs (h)(1) and (h)(2) of this AD and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin [[Page 26675]] 717-55A0012, dated June 12, 2015, except as required by paragraph (i)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspection thereafter at the intervals specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 717-55A0012, dated June 12, 2015. (1) Do detailed inspections for any loose and missing fasteners of the vertical stabilizer leading edge as specified in ``Part 4'' of Boeing Alert Service Bulletin 717-55A0012, dated June 12, 2015. (2) Do eddy current testing high frequency (ETHF) and radiographic testing (RT) inspections for any crack of the vertical stabilizer spar cap as specified in ``Part 2'' of Boeing Alert Service Bulletin 717-55A0012, dated June 12, 2015; or do ETHF inspections for any crack of the vertical stabilizer spar cap as specified in ``Part 3'' of Boeing Alert Service Bulletin 717- 55A0012, dated June 12, 2015. (i) Exceptions to the Service Information (1) Where Boeing Alert Service Bulletin 717-55A0012, dated June 12, 2015 specifies a compliance time ``after the original issue date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) If any crack is found during any inspection required by this AD, and Boeing Alert Service Bulletin 717-55A0012, dated June 12, 2015, specifies to contact Boeing for appropriate action: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (j) Credit for Previous Actions This paragraph provides credit for the initial inspection specified in paragraph (g) of this AD, if that inspection was performed before the effective date of this AD using Boeing MOM-MOM- 14-0437-01B(R1), dated July 3, 2014, which is not incorporated by reference in this AD. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles Aircraft Certification Office (ACO), 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 ACO, send it to the attention of the person identified in paragraph (l) of this AD. Information may be emailed to: [email protected]. (2) 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. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (l) Related Information For more information about this AD, contact Eric Schrieber, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627- 5348; fax: 562-627-5210; email: [email protected]. (m) 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 the AD specifies otherwise. (i) Boeing Alert Service Bulletin 717-55A0012, dated June 12, 2015. (ii) Reserved. (3) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001; telephone: 206-544-5000, extension 2; fax: 206-766-5683; Internet: https://www.myboeingfleet.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 April 20, 2016. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-10160 Filed 5-3-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 86 / Wednesday, May 4, 2016 / Rules and Regulations 26673
13. The airbag system in the shoulder- repetitive eddy current testing high part 39 by adding an AD that would
belt installation must be protected from frequency (ETHF) and radiographic apply to certain The Boeing Company
the effects of fire such that no hazard to testing (RT) inspections of the spar cap Model 717–200 airplanes. The NPRM
occupants will result. for any crack, and related investigative published in the Federal Register on
14. A means must be available for a and corrective actions if necessary. We October 6, 2015 (80 FR 60307) (‘‘the
crewmember to verify the integrity of are issuing this AD to detect and correct NPRM’’). The NPRM was prompted by
the airbag system in the shoulder-belt any crack in the vertical stabilizer multiple reports of the vertical stabilizer
activation system prior to each flight, or leading edge and front spar cap, which leading edge showing signs of fastener
it must be demonstrated to reliably may result in the structure becoming distress. The NPRM proposed to require
operate between inspection intervals. unable to support limit load, and may a detailed inspection for any distress of
The FAA considers that the loss of the lead to the loss of the vertical stabilizer. the vertical stabilizer leading edge skin,
airbag-system deployment function DATES: This AD is effective June 8, 2016. and related investigative and corrective
alone (i.e., independent of the The Director of the Federal Register actions if necessary. The NPRM also
conditional event that requires the approved the incorporation by reference proposed to require, for certain
airbag-system deployment) is a major- of a certain publication listed in this AD airplanes, repetitive detailed
failure condition. as of June 8, 2016. inspections of the spar cap for any loose
15. The inflatable material may not ADDRESSES: For service information and missing fasteners, repetitive ETHF
have an average burn rate of greater than identified in this final rule, contact and RT inspections of the spar cap for
2.5 inches/minute when tested using the Boeing Commercial Airplanes, any crack, and related investigative and
horizontal flammability test defined in Attention: Data & Services Management, corrective actions if necessary. We are
part 25, appendix F, part I, paragraph 3855 Lakewood Boulevard, MC D800– issuing this AD to detect and correct any
(b)(5). 0019, Long Beach, CA 90846–0001; crack in the vertical stabilizer leading
16. The airbag system in the shoulder telephone: 206–544–5000, extension 2; edge and front spar cap, which may
belt, once deployed, must not adversely fax: 206–766–5683; Internet: https:// result in the structure becoming unable
affect the emergency-lighting system www.myboeingfleet.com. You may view to support limit load, and may lead to
(i.e., block floor proximity lights to the this referenced service information at the loss of the vertical stabilizer.
extent that the lights no longer meet the FAA, Transport Airplane Comments
their intended function). Directorate, 1601 Lind Avenue SW.,
Issued in Renton, Washington, on April 27, Renton, WA. For information on the We gave the public the opportunity to
2016. availability of this material at the FAA, participate in developing this AD. The
Dionne Palermo, call 425–227–1221. It is also available following presents the comments
Acting Manager, Transport Airplane on the Internet at http:// received on the NPRM and the FAA’s
Directorate, Aircraft Certification Service. www.regulations.gov by searching for response to each comment. Boeing and
[FR Doc. 2016–10440 Filed 5–3–16; 8:45 am] and locating Docket No. FAA–2015– an anonymous commenter indicated
3982. their support for the NPRM.
BILLING CODE 4910–13–P
Examining the AD Docket Request To Add Credit for Previous
Actions
DEPARTMENT OF TRANSPORTATION You may examine the AD docket on
the Internet at http:// Boeing requested that we add a
Federal Aviation Administration www.regulations.gov by searching for ‘‘Credit for Previous Actions’’ paragraph
and locating Docket No. FAA–2015– to the proposed AD that would give
14 CFR Part 39 3982; or in person at the Docket credit for prior accomplishment of the
Management Facility between 9 a.m. initial inspection in paragraph (g) of the
[Docket No. FAA–2015–3982; Directorate
Identifier 2015–NM–098–AD; Amendment
and 5 p.m., Monday through Friday, NPRM. Boeing stated that operator
39–18503; AD 2016–09–05] except Federal holidays. The AD docket structural inspection credit has been
contains this AD, the regulatory incorporated as a precedent in previous
RIN 2120–AA64 evaluation, any comments received, and ADs.
other information. The address for the We agree with the commenter’s
Airworthiness Directives; The Boeing Docket Office (phone: 800–647–5527) is request. Boeing MOM–MOM–14–0437–
Company Airplanes Docket Management Facility, U.S. 01B(R1), dated July 3, 2014, provides
AGENCY: Federal Aviation Department of Transportation, Docket the same action and level of safety for
Administration (FAA), DOT. Operations, M–30, West Building the initial inspection specified in this
ACTION: Final rule.
Ground Floor, Room W12–140, 1200 AD. We have revised this AD by adding
New Jersey Avenue SE., Washington, new paragraph (j) of this AD to give
SUMMARY: We are adopting a new DC 20590. credit for the initial inspection in
airworthiness directive (AD) for certain FOR FURTHER INFORMATION CONTACT: Eric paragraph (g) of this AD, if that
The Boeing Company Model 717–200 Schrieber, Aerospace Engineer, inspection was performed before the
airplanes. This AD was prompted by Airframe Branch, ANM–120L, FAA, Los effective date of this AD using Boeing
multiple reports of the vertical stabilizer Angeles Aircraft Certification Office MOM–MOM–14–0437–01B(R1), dated
leading edge showing signs of fastener (ACO), 3960 Paramount Boulevard, July 3, 2014. We have redesignated the
asabaliauskas on DSK3SPTVN1PROD with RULES
distress. This AD requires a detailed Lakewood, CA 90712–4137; phone: remaining paragraphs accordingly.
inspection for any distress of the 562–627–5348; fax: 562–627–5210;
Conclusion
vertical stabilizer leading edge skin, and email: Eric.Schrieber@faa.gov.
related investigative and corrective SUPPLEMENTARY INFORMATION: We reviewed the relevant data,
actions if necessary. This AD also considered the comments received, and
requires, for certain airplanes, repetitive Discussion determined that air safety and the
detailed inspections of the spar cap for We issued a notice of proposed public interest require adopting this AD
any loose and missing fasteners, rulemaking (NPRM) to amend 14 CFR with the change described previously
VerDate Sep<11>2014 17:12 May 03, 2016 Jkt 238001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 E:\FR\FM\04MYR1.SGM 04MYR1](https://thefederalregister.org/doc/81_FR_26759/page/1.svg)
![26674 Federal Register / Vol. 81, No. 86 / Wednesday, May 4, 2016 / Rules and Regulations
and minor editorial changes. We have Related Service Information Under 1 investigative and corrective actions.
determined that these minor changes: CFR Part 51 This service information is reasonably
• Are consistent with the intent that available because the interested parties
was proposed in the NPRM for We reviewed Boeing Alert Service have access to it through their normal
correcting the unsafe condition; and Bulletin 717–55A0012, dated June 12, course of business or by the means
• Do not add any additional burden 2015. The service information describes identified in the ADDRESSES section.
upon the public than was already procedures for a detailed inspection for
any distress of the vertical stabilizer Costs of Compliance
proposed in the NPRM.
We also determined that these leading edge skin, a detailed inspection We estimate that this AD affects 106
changes will not increase the economic for any loose and missing fasteners of airplanes of U.S. registry.
burden on any operator or increase the the spar cap, ETHF and RT inspections We estimate the following costs to
scope of this AD. of the spar cap for any crack, and related comply with this AD:
ESTIMATED COSTS
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
Inspections for distress .......................... 11 work-hours × $85 per hour = $935 $0 $935 per inspection $99,110 per inspec-
per inspection cycle. cycle. tion cycle.
Repetitive inspections for cracking and 7 work-hours × $85 per hour = $595 0 595 per inspection 63,070 per inspec-
loose and missing fasteners. per inspection cycle. cycle. tion cycle.
We have received no definitive data (2) Is not a ‘‘significant rule’’ under category, as specified in Boeing Alert Service
that would enable us to provide cost DOT Regulatory Policies and Procedures Bulletin 717–55A0012, dated June 12, 2015.
estimates for the on-condition actions (44 FR 11034, February 26, 1979), (d) Subject
specified in this AD. (3) Will not affect intrastate aviation Air Transport Association (ATA) of
in Alaska, and America Code 55, Stabilizers.
Authority for This Rulemaking (4) Will not have a significant
economic impact, positive or negative, (e) Unsafe Condition
Title 49 of the United States Code
specifies the FAA’s authority to issue on a substantial number of small entities This AD was prompted by multiple reports
under the criteria of the Regulatory of the vertical stabilizer leading edge
rules on aviation safety. Subtitle I,
Flexibility Act. showing signs of fastener distress. We are
section 106, describes the authority of issuing this AD to detect and correct any
the FAA Administrator. Subtitle VII: List of Subjects in 14 CFR Part 39 crack in the vertical stabilizer leading edge
Aviation Programs, describes in more and front spar cap, which may result in the
Air transportation, Aircraft, Aviation
detail the scope of the Agency’s structure becoming unable to support limit
safety, Incorporation by reference,
authority. load, and may lead to the loss of the vertical
Safety. stabilizer.
We are issuing this rulemaking under
the authority described in Subtitle VII, Adoption of the Amendment (f) Compliance
Part A, Subpart III, Section 44701: Accordingly, under the authority Comply with this AD within the
‘‘General requirements.’’ Under that delegated to me by the Administrator, compliance times specified, unless already
section, Congress charges the FAA with the FAA amends 14 CFR part 39 as done.
promoting safe flight of civil aircraft in follows: (g) Initial Inspection
air commerce by prescribing regulations
Except as required by paragraph (i)(1) of
for practices, methods, and procedures PART 39—AIRWORTHINESS
this AD, at the applicable time specified in
the Administrator finds necessary for DIRECTIVES paragraph 1.E., ‘‘Compliance,’’ of Boeing
safety in air commerce. This regulation Alert Service Bulletin 717–55A0012, dated
is within the scope of that authority ■ 1. The authority citation for part 39 June 12, 2015: Do a detailed inspection for
because it addresses an unsafe condition continues to read as follows: any distress of the vertical stabilizer leading
that is likely to exist or develop on Authority: 49 U.S.C. 106(g), 40113, 44701. edge skin and do all applicable related
products identified in this rulemaking investigative and corrective actions, in
§ 39.13 [Amended] accordance with the Accomplishment
action.
■ 2. The FAA amends § 39.13 by adding Instructions of Boeing Alert Service Bulletin
Regulatory Findings 717–55A0012, dated June 12, 2015, except as
the following new airworthiness required by paragraph (i)(2) of this AD. Do all
This AD will not have federalism directive (AD): applicable related investigative and
implications under Executive Order 2016–09–05 The Boeing Company: corrective actions before further flight.
13132. This AD will not have a Amendment 39–18503; Docket No. (h) Repetitive Inspections
substantial direct effect on the States, on FAA–2015–3982; Directorate Identifier
2015–NM–098–AD. For all airplanes on which no cracking was
the relationship between the national found during any related investigative action
government and the States, or on the
asabaliauskas on DSK3SPTVN1PROD with RULES
(a) Effective Date required by paragraph (g) of this AD: At the
distribution of power and This AD is effective June 8, 2016. applicable time specified in paragraph 1.E.,
responsibilities among the various ‘‘Compliance,’’ of Boeing Alert Service
levels of government. (b) Affected ADs Bulletin 717–55A0012, dated June 12, 2015,
For the reasons discussed above, I None. do the actions specified in paragraphs (h)(1)
and (h)(2) of this AD and do all applicable
certify that this AD: (c) Applicability related investigative and corrective actions,
(1) Is not a ‘‘significant regulatory This AD applies to The Boeing Company in accordance with the Accomplishment
action’’ under Executive Order 12866, Model 717–200 airplanes, certificated in any Instructions of Boeing Alert Service Bulletin
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717–55A0012, dated June 12, 2015, except as ACO, to make those findings. To be We are adopting a new
SUMMARY:
required by paragraph (i)(2) of this AD. Do all approved, the repair method, modification airworthiness directive (AD) for certain
applicable related investigative and deviation, or alteration deviation must meet Turbomeca S.A. Astazou XIV B and H
corrective actions before further flight. the certification basis of the airplane, and the
Repeat the applicable inspection thereafter at approval must specifically refer to this AD.
turboshaft engines. This AD requires a
the intervals specified in paragraph 1.E., one-time inspection of the front surface
‘‘Compliance,’’ of Boeing Alert Service (l) Related Information of the 3rd stage turbine for a groove.
Bulletin 717–55A0012, dated June 12, 2015. For more information about this AD, This AD was prompted by a report of a
(1) Do detailed inspections for any loose contact Eric Schrieber, Aerospace Engineer, crack on the 3rd stage turbine wheel.
and missing fasteners of the vertical stabilizer Airframe Branch, ANM–120L, FAA, Los We are issuing this AD to prevent cracks
leading edge as specified in ‘‘Part 4’’ of Angeles ACO, 3960 Paramount Boulevard, in the 3rd stage turbine wheel, failure of
Boeing Alert Service Bulletin 717–55A0012, Lakewood, CA 90712–4137; phone: 562–627–
the engine, in-flight shutdown, and loss
dated June 12, 2015. 5348; fax: 562–627–5210; email:
(2) Do eddy current testing high frequency Eric.Schrieber@faa.gov. of control of the helicopter.
(ETHF) and radiographic testing (RT) DATES: This AD becomes effective June
(m) Material Incorporated by Reference
inspections for any crack of the vertical 8, 2016.
stabilizer spar cap as specified in ‘‘Part 2’’ of (1) The Director of the Federal Register The Director of the Federal Register
Boeing Alert Service Bulletin 717–55A0012, approved the incorporation by reference approved the incorporation by reference
dated June 12, 2015; or do ETHF inspections (IBR) of the service information listed in this of a certain publication listed in this AD
for any crack of the vertical stabilizer spar paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51. as of June 8, 2016.
cap as specified in ‘‘Part 3’’ of Boeing Alert
Service Bulletin 717–55A0012, dated June (2) You must use this service information ADDRESSES: For service information
12, 2015. as applicable to do the actions required by identified in this final rule, contact
this AD, unless the AD specifies otherwise. Turbomeca S.A., 40220 Tarnos, France;
(i) Exceptions to the Service Information (i) Boeing Alert Service Bulletin 717– phone: 33 (0)5 59 74 40 00; fax: 33 (0)5
(1) Where Boeing Alert Service Bulletin 55A0012, dated June 12, 2015. 59 74 45 15. You may view this service
717–55A0012, dated June 12, 2015 specifies (ii) Reserved.
information at the FAA, Engine &
a compliance time ‘‘after the original issue (3) For Boeing service information
date of this service bulletin,’’ this AD identified in this AD, contact Boeing Propeller Directorate, 1200 District
requires compliance within the specified Commercial Airplanes, Attention: Data & Avenue, Burlington, MA. For
compliance time after the effective date of Services Management, 3855 Lakewood information on the availability of this
this AD. Boulevard, MC D800–0019, Long Beach, CA material at the FAA, call 781–238–7125.
(2) If any crack is found during any 90846–0001; telephone: 206–544–5000, It is also available on the Internet at
inspection required by this AD, and Boeing extension 2; fax: 206–766–5683; Internet: http://www.regulations.gov by searching
Alert Service Bulletin 717–55A0012, dated https://www.myboeingfleet.com. for and locating Docket No. FAA–2015–
June 12, 2015, specifies to contact Boeing for (4) You may view this service information 7490.
appropriate action: Before further flight, at the FAA, Transport Airplane Directorate,
repair using a method approved in 1601 Lind Avenue SW., Renton, WA. For Examining the AD Docket
accordance with the procedures specified in information on the availability of this
paragraph (k) of this AD. material at the FAA, call 425–227–1221. You may examine the AD docket on
(5) You may view this service information the Internet at http://
(j) Credit for Previous Actions that is incorporated by reference at the www.regulations.gov by searching for
This paragraph provides credit for the National Archives and Records and locating Docket No. FAA–2015–
initial inspection specified in paragraph (g) Administration (NARA). For information on 7490; or in person at the Docket
of this AD, if that inspection was performed the availability of this material at NARA, call Management Facility between 9 a.m.
before the effective date of this AD using 202–741–6030, or go to: http:// and 5 p.m., Monday through Friday,
Boeing MOM–MOM–14–0437–01B(R1), www.archives.gov/federal-register/cfr/ibr-
dated July 3, 2014, which is not incorporated locations.html.
except Federal holidays. The AD docket
by reference in this AD. contains this AD, the mandatory
Issued in Renton, Washington, on April 20, continuing airworthiness information
(k) Alternative Methods of Compliance 2016. (MCAI), the regulatory evaluation, any
(AMOCs) John P. Piccola, Jr., comments received, and other
(1) The Manager, Los Angeles Aircraft Acting Manager, Transport Airplane information. The address for the Docket
Certification Office (ACO), FAA, has the Directorate, Aircraft Certification Service. Office (phone: 800–647–5527) is
authority to approve AMOCs for this AD, if [FR Doc. 2016–10160 Filed 5–3–16; 8:45 am]
requested using the procedures found in 14
Document Management Facility, U.S.
CFR 39.19. In accordance with 14 CFR 39.19, BILLING CODE 4910–13–P Department of Transportation, Docket
send your request to your principal inspector Operations, M–30, West Building
or local Flight Standards District Office, as Ground Floor, Room W12–140, 1200
appropriate. If sending information directly DEPARTMENT OF TRANSPORTATION New Jersey Avenue SE., Washington,
to the manager of the ACO, send it to the DC 20590.
attention of the person identified in Federal Aviation Administration
FOR FURTHER INFORMATION CONTACT:
paragraph (l) of this AD. Information may be
emailed to: 9-ANM-LAACO-AMOC- 14 CFR Part 39 Wego Wang, Aerospace Engineer,
Requests@faa.gov. Engine Certification Office, FAA, Engine
(2) Before using any approved AMOC, [Docket No. FAA–2015–7490; Directorate & Propeller Directorate, 1200 District
notify your appropriate principal inspector, Identifier 2015–NE–40–AD; Amendment 39– Avenue, Burlington, MA 01803; phone:
or lacking a principal inspector, the manager 18500; AD 2016–09–02] 781–238–7134; fax: 781–238–7199;
asabaliauskas on DSK3SPTVN1PROD with RULES
of the local flight standards district office/ RIN 2120–AA64 email: wego.wang@faa.gov.
certificate holding district office.
SUPPLEMENTARY INFORMATION:
(3) An AMOC that provides an acceptable Airworthiness Directives; Turbomeca
level of safety may be used for any repair, S.A. Turboshaft Engines Discussion
modification, or alteration required by this
AD if it is approved by the Boeing AGENCY: Federal Aviation We issued a notice of proposed
Commercial Airplanes Organization Administration (FAA), DOT. rulemaking (NPRM) to amend 14 CFR
Designation Authorization (ODA) that has part 39 by adding an AD that would
ACTION: Final rule.
been authorized by the Manager, Los Angeles apply to the specified products. The
VerDate Sep<11>2014 17:12 May 03, 2016 Jkt 238001 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 E:\FR\FM\04MYR1.SGM 04MYR1](https://thefederalregister.org/doc/81_FR_26759/page/3.svg)
Document Created: 2016-05-04 01:23:13
Document Modified: 2016-05-04 01:23:13
| 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 June 8, 2016. | |
| Contact | Eric Schrieber, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5348; fax: 562-627-5210; email: [email protected] | |
| FR Citation | 81 FR 26673 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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