81 FR 9749 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 38 (February 26, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 38 (February 26, 2016)
| Page Range | 9749-9751 | |
| FR Document | 2016-03886 |
[Federal Register Volume 81, Number 38 (Friday, February 26, 2016)] [Rules and Regulations] [Pages 9749-9751] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-03886] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-3146; Directorate Identifier 2014-NM-249-AD; Amendment 39-18411; AD 2016-04-17] 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 777-200 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the skin lap splices at certain stringers in certain fuselage sections are subject to widespread fatigue damage (WFD) on aging Model 777 airplanes that have accumulated at least 45,000 total flight cycles. This AD requires inspections to detect cracking of fuselage skin lap splices in certain fuselage sections, and corrective actions if necessary; modification of left-side and right-side lap splices; and post-modification repetitive inspections for cracks in the modified lap splices, and corrective actions if necessary. We are issuing this AD to detect and correct fatigue cracking of the skin lap splices, and consequent risk of sudden decompression and the inability to sustain limit flight and pressure loads. DATES: This AD is effective April 1, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 1, 2016. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; 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- 3146. 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- 3146; 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 Lin, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6412; fax: 425-917-6590; 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 777-200 series airplanes. The NPRM published in the Federal Register on August 25, 2015 (80 FR 51488) (``the NPRM''). The NPRM was prompted by an evaluation by the DAH indicating that the skin lap splices at certain stringers in certain fuselage sections are subject to WFD on aging airplanes (airplanes that have accumulated at least 45,000 total flight cycles). The NPRM proposed to require inspections to detect cracking of fuselage skin lap splices in certain fuselage sections, and corrective actions if necessary; modification of left- side and right-side lap splices; and post-modification repetitive inspections for cracks in the modified lap splices, and corrective actions if necessary. We are issuing this AD to detect and correct fatigue cracking of the skin lap splices, and consequent risk of sudden decompression and the inability to sustain limit flight and pressure loads. 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. Support for the NPRM An anonymous commenter expressed support for the NPRM. Request To Revise WFD Criteria Definition Boeing requested that we revise the NPRM to specify that DAH analysis indicates that potential multi-site damage that could lead to WFD does not occur until at least 45,000 total flight cycles on aging Model 777 airplanes. We agree with the commenter's request. We have revised the SUMMARY and Discussion sections of this final rule and paragraph (e) of this AD to specify that this AD was prompted by an evaluation by the DAH indicating that the skin lap splices at certain stringers in certain fuselage sections are subject to WFD on aging Model 777 airplanes that have accumulated at least 45,000 total flight cycles. 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 changes described previously and 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. We also determined that these changes will not increase the economic [[Page 9750]] 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 777-53A0052, dated October 10, 2014. The service bulletin describes procedures for inspections to detect cracking of fuselage skin lap splices, modification to the skin lap splices, repetitive inspections for cracks in the modified lap splices, and repairs. 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 21 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 ---------------------------------------------------------------------------------------------------------------- Inspection and modification.... 2,713 work-hours x $85 $0 $230,605.......... $4,842,705. per hour = $230,605. Post-modification inspection... 1,391 work-hours x $85 0 $118,235 per $2,482,935 per per hour = $118,235 inspection cycle. inspection cycle. 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. According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all available costs in our cost estimate. 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): 2016-04-17 The Boeing Company: Amendment 39-18411; Docket No. FAA- 2015-3146; Directorate Identifier 2014-NM-249-AD. (a) Effective Date This AD is effective April 1, 2016. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 777-200 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 777-53A0052, dated October 10, 2014. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder indicating that the skin lap splices at certain stringers in certain fuselage sections are subject to widespread fatigue damage on aging Model 777 airplanes that have accumulated at least 45,000 total flight cycles. We are issuing this AD to detect and correct fatigue cracking of the skin lap splices, and consequent risk of sudden decompression and the inability to sustain limit flight and pressure loads. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections and Corrective Actions Except as provided by paragraph (h)(1) of this AD, at the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 777-53A0052, dated October 10, 2014: Do Part 1, inspection ``A,'' of the modification area for cracks; Part 2, inspection ``B,'' of the modification area for cracks; and Part 3, inspection ``C,'' of the modification area for scribe lines and cracks; as applicable; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777-53A0052, dated October 10, 2014, except as provided by paragraph (h)(2) of this AD. Do all applicable corrective actions before further flight. (1) Inspection ``A'' includes an external phased array ultrasonic inspection for cracks in the lower/overlapped skin of the stringer S-14 left and right (L/R) lap splices between fuselage station 655 and station 1434, and an open hole high frequency eddy current (HFEC) inspection for skin cracks at the upper and lower fastener rows of the stringer S-14 L/R lap splices. (2) Inspection ``B'' includes the inspections specified in paragraphs (g)(2)(i) through (g)(2)(iv) of this AD. (i) A detailed inspection for cracks of any skin panel common to a stringer S-14 L/R lap splice between fuselage station 655 and station 1434 that has a scribe line 0.001 inch or deeper. [[Page 9751]] (ii) Either an ultrasonic inspection or a surface HFEC inspection for cracks (depending on the location of the scribe line(s)) of any skin panel common to a stringer S-14 L/R lap splice between fuselage station 655 and station 1434 that has a scribe line 0.001 inch or deeper. (iii) An external phased array ultrasonic inspection for cracks in the lower/overlapped skin of the stringer S-14 L/R lap splices between fuselage station 655 and station 1434. (iv) An open hole HFEC inspection for skin cracks at the upper and lower fastener rows of the stringer S-14 L/R lap splices. (3) Inspection ``C'' includes the inspections for scribe lines and cracks specified in paragraphs (g)(3)(i), (g)(3)(ii), and (g)(3)(iii) of this AD on stringer S-14 L/R lap splice between fuselage station 655 and station 1434 on both sides of the airplane. (i) A detailed inspection for scribe lines. If any scribe line is found during the inspection required by this paragraph, the actions include the inspections specified in paragraphs (g)(3)(i)(A) and (g)(3)(i)(B) of this AD. (A) A detailed inspection for cracks of the scribe line area(s). (B) Either an ultrasonic inspection or a surface HFEC inspection for cracks (depending on the location of the scribe line(s)). (ii) An external phased array ultrasonic inspection for cracks in the lower/overlapped skin of the stringer S-14 L/R lap splices between fuselage station 655 and station 1434. (iii) An open hole HFEC inspection for skin cracks at the upper and lower fastener rows of the stringer S-14 L/R lap splices. (h) Exceptions to Service Information Specifications (1) Where Paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 777-53A0052, dated October 10, 2014, 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, during accomplishment of any inspection required by this AD, any condition is found for which Boeing Alert Service Bulletin 777-53A0052, dated October 10, 2014, specifies to contact Boeing for special repair instructions or supplemental instructions for the modification, and specifies that action as ``RC'' (Required for Compliance): Before further flight, do the repair or modification using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (i) Lap Splice Modification At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 777-53A0052, dated October 10, 2014: Do the left-side and right-side lap splice modification, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777-53A0052, dated October 10, 2014, except as provided by paragraph (h)(2) of this AD. (j) Post-Modification Inspections and Corrective Action At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 777-53A0052, dated October 10, 2014: Do a post-modification internal surface HFEC inspection for skin cracks in the modified lap splices on both sides of the airplane; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 777-53A0052, dated October 10, 2014, except as provided by paragraph (h)(2) of this AD. Do all applicable corrective actions before further flight. Repeat the inspection of the modified lap splices thereafter at the applicable intervals specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 777-53A0052, dated October 10, 2014. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle 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, Seattle 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. (4) Except as required by paragraph (h)(2) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (k)(4)(i) and (k)(4)(ii) apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (l) Related Information For more information about this AD, contact Eric Lin, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6412; fax: 425- 917-6590; 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 777-53A0052, dated October 10, 2014. (ii) Reserved. (3) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. (4) You may view this service information at 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 February 16, 2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-03886 Filed 2-25-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 38 / Friday, February 26, 2016 / Rules and Regulations 9749
(i) Avions de Transport Régional Service actions if necessary. We are issuing this prompted by an evaluation by the DAH
Bulletin ATR42–92–0024, Revision 03, dated AD to detect and correct fatigue indicating that the skin lap splices at
January 21, 2015. cracking of the skin lap splices, and certain stringers in certain fuselage
(ii) Avions de Transport Régional Service
consequent risk of sudden sections are subject to WFD on aging
Bulletin ATR72–92–1032, Revision 03, dated
January 21, 2015. decompression and the inability to airplanes (airplanes that have
(3) For service information identified in sustain limit flight and pressure loads. accumulated at least 45,000 total flight
this AD, contact ATR–GIE Avions de DATES: This AD is effective April 1, cycles). The NPRM proposed to require
Transport Régional, 1, Allée Pierre Nadot, 2016. inspections to detect cracking of
31712 Blagnac Cedex, France; telephone +33 The Director of the Federal Register fuselage skin lap splices in certain
(0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18; approved the incorporation by reference fuselage sections, and corrective actions
email continued.airworthiness@atr.fr; of a certain publication listed in this AD if necessary; modification of left-side
Internet http://www.aerochain.com.
as of April 1, 2016. and right-side lap splices; and post-
(4) You may view this service information
at the FAA, Transport Airplane Directorate, ADDRESSES: For service information modification repetitive inspections for
1601 Lind Avenue SW., Renton, WA. For identified in this final rule, contact cracks in the modified lap splices, and
information on the availability of this Boeing Commercial Airplanes, corrective actions if necessary. We are
material at the FAA, call 425–227–1221. Attention: Data & Services Management, issuing this AD to detect and correct
(5) You may view this service information P. O. Box 3707, MC 2H–65, Seattle, WA fatigue cracking of the skin lap splices,
that is incorporated by reference at the 98124–2207; telephone 206–544–5000, and consequent risk of sudden
National Archives and Records decompression and the inability to
extension 1; fax 206–766–5680; Internet
Administration (NARA). For information on sustain limit flight and pressure loads.
the availability of this material at NARA, call https://www.myboeingfleet.com. You
202–741–6030, or go to: http:// may view this referenced service Comments
www.archives.gov/federal-register/cfr/ibr- information at the FAA, Transport
locations.html. Airplane Directorate, 1601 Lind Avenue We gave the public the opportunity to
SW., Renton, WA. For information on participate in developing this AD. The
Issued in Renton, Washington, on February following presents the comments
16, 2016. the availability of this material at the
FAA, call 425–227–1221. It is also received on the NPRM and the FAA’s
Dionne Palermo, response to each comment.
available on the Internet at http://
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service. www.regulations.gov by searching for Support for the NPRM
and locating Docket No. FAA–2015–
[FR Doc. 2016–03689 Filed 2–25–16; 8:45 am] An anonymous commenter expressed
3146.
BILLING CODE 4910–13–P support for the NPRM.
Examining the AD Docket
Request To Revise WFD Criteria
You may examine the AD docket on Definition
DEPARTMENT OF TRANSPORTATION the Internet at http://
www.regulations.gov by searching for Boeing requested that we revise the
Federal Aviation Administration
and locating Docket No. FAA–2015– NPRM to specify that DAH analysis
3146; or in person at the Docket indicates that potential multi-site
14 CFR Part 39
Management Facility between 9 a.m. damage that could lead to WFD does not
[Docket No. FAA–2015–3146; Directorate and 5 p.m., Monday through Friday, occur until at least 45,000 total flight
Identifier 2014–NM–249–AD; Amendment except Federal holidays. The AD docket cycles on aging Model 777 airplanes.
39–18411; AD 2016–04–17] contains this AD, the regulatory We agree with the commenter’s
RIN 2120–AA64 evaluation, any comments received, and request. We have revised the SUMMARY
other information. The address for the and Discussion sections of this final rule
Airworthiness Directives; The Boeing Docket Office (phone: 800–647–5527) is and paragraph (e) of this AD to specify
Company Airplanes Docket Management Facility, U.S. that this AD was prompted by an
AGENCY: Federal Aviation Department of Transportation, Docket evaluation by the DAH indicating that
Administration (FAA), DOT. Operations, M–30, West Building the skin lap splices at certain stringers
Ground Floor, Room W12–140, 1200 in certain fuselage sections are subject
ACTION: Final rule.
New Jersey Avenue SE., Washington, to WFD on aging Model 777 airplanes
SUMMARY: We are adopting a new DC 20590. that have accumulated at least 45,000
airworthiness directive (AD) for certain FOR FURTHER INFORMATION CONTACT: Eric total flight cycles.
The Boeing Company Model 777–200 Lin, Aerospace Engineer, Airframe Conclusion
series airplanes. This AD was prompted Branch, ANM–120S, FAA, Seattle
by an evaluation by the design approval Aircraft Certification Office (ACO), 1601 We reviewed the relevant data,
holder (DAH) indicating that the skin Lind Avenue SW., Renton, WA 98057– considered the comments received, and
lap splices at certain stringers in certain 3356; phone: 425–917–6412; fax: 425– determined that air safety and the
fuselage sections are subject to 917–6590; email: Eric.Lin@faa.gov. public interest require adopting this AD
widespread fatigue damage (WFD) on SUPPLEMENTARY INFORMATION: with the changes described previously
aging Model 777 airplanes that have and minor editorial changes. We have
accumulated at least 45,000 total flight Discussion determined that these minor changes:
cycles. This AD requires inspections to We issued a notice of proposed • Are consistent with the intent that
mstockstill on DSK4VPTVN1PROD with RULES
detect cracking of fuselage skin lap rulemaking (NPRM) to amend 14 CFR was proposed in the NPRM for
splices in certain fuselage sections, and part 39 by adding an AD that would correcting the unsafe condition; and
corrective actions if necessary; apply to certain The Boeing Company • Do not add any additional burden
modification of left-side and right-side Model 777–200 series airplanes. The upon the public than was already
lap splices; and post-modification NPRM published in the Federal proposed in the NPRM.
repetitive inspections for cracks in the Register on August 25, 2015 (80 FR We also determined that these
modified lap splices, and corrective 51488) (‘‘the NPRM’’). The NPRM was changes will not increase the economic
VerDate Sep<11>2014 17:33 Feb 25, 2016 Jkt 238001 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 E:\FR\FM\26FER1.SGM 26FER1](https://thefederalregister.org/doc/81_FR_9787/page/1.svg)
![9750 Federal Register / Vol. 81, No. 38 / Friday, February 26, 2016 / Rules and Regulations
burden on any operator or increase the procedures for inspections to detect course of business or by the means
scope of this AD. cracking of fuselage skin lap splices, identified in the ADDRESSES section.
modification to the skin lap splices,
Related Service Information Under 1 Costs of Compliance
repetitive inspections for cracks in the
CFR Part 51
modified lap splices, and repairs. This We estimate that this AD affects 21
We reviewed Boeing Alert Service service information is reasonably airplanes of U.S. registry.
Bulletin 777–53A0052, dated October available because the interested parties We estimate the following costs to
10, 2014. The service bulletin describes have access to it through their normal comply with this AD:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspection and modifica- 2,713 work-hours × $85 per hour = $230,605 ... $0 $230,605 ...................... $4,842,705.
tion.
Post-modification in- 1,391 work-hours × $85 per hour = $118,235 0 $118,235 per inspection $2,482,935 per inspec-
spection. per inspection cycle. cycle. tion cycle.
We have received no definitive data (1) Is not a ‘‘significant regulatory (d) Subject
that would enable us to provide cost action’’ under Executive Order 12866, Air Transport Association (ATA) of
estimates for the on-condition actions (2) Is not a ‘‘significant rule’’ under America Code 53, Fuselage.
specified in this AD. DOT Regulatory Policies and Procedures (e) Unsafe Condition
According to the manufacturer, some (44 FR 11034, February 26, 1979),
This AD was prompted by an evaluation by
of the costs of this AD may be covered (3) Will not affect intrastate aviation the design approval holder indicating that
under warranty, thereby reducing the in Alaska, and the skin lap splices at certain stringers in
cost impact on affected individuals. We (4) Will not have a significant certain fuselage sections are subject to
do not control warranty coverage for economic impact, positive or negative, widespread fatigue damage on aging Model
affected individuals. As a result, we on a substantial number of small entities 777 airplanes that have accumulated at least
have included all available costs in our under the criteria of the Regulatory 45,000 total flight cycles. We are issuing this
cost estimate. Flexibility Act. AD to detect and correct fatigue cracking of
the skin lap splices, and consequent risk of
Authority for This Rulemaking List of Subjects in 14 CFR Part 39 sudden decompression and the inability to
sustain limit flight and pressure loads.
Title 49 of the United States Code Air transportation, Aircraft, Aviation
specifies the FAA’s authority to issue safety, Incorporation by reference, (f) Compliance
rules on aviation safety. Subtitle I, Safety. Comply with this AD within the
section 106, describes the authority of Adoption of the Amendment
compliance times specified, unless already
the FAA Administrator. Subtitle VII: done.
Aviation Programs, describes in more Accordingly, under the authority (g) Inspections and Corrective Actions
detail the scope of the Agency’s delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as Except as provided by paragraph (h)(1) of
authority. this AD, at the applicable time specified in
We are issuing this rulemaking under follows: paragraph 1.E., ‘‘Compliance,’’ of Boeing
the authority described in Subtitle VII, Alert Service Bulletin 777–53A0052, dated
Part A, Subpart III, Section 44701: PART 39—AIRWORTHINESS October 10, 2014: Do Part 1, inspection ‘‘A,’’
‘‘General requirements.’’ Under that DIRECTIVES of the modification area for cracks; Part 2,
section, Congress charges the FAA with inspection ‘‘B,’’ of the modification area for
■ 1. The authority citation for part 39 cracks; and Part 3, inspection ‘‘C,’’ of the
promoting safe flight of civil aircraft in continues to read as follows: modification area for scribe lines and cracks;
air commerce by prescribing regulations as applicable; and do all applicable
for practices, methods, and procedures Authority: 49 U.S.C. 106(g), 40113, 44701.
corrective actions; in accordance with the
the Administrator finds necessary for § 39.13 [Amended] Accomplishment Instructions of Boeing Alert
safety in air commerce. This regulation Service Bulletin 777–53A0052, dated October
■ 2. The FAA amends § 39.13 by adding
is within the scope of that authority 10, 2014, except as provided by paragraph
the following new airworthiness (h)(2) of this AD. Do all applicable corrective
because it addresses an unsafe condition
directive (AD): actions before further flight.
that is likely to exist or develop on
products identified in this rulemaking 2016–04–17 The Boeing Company: (1) Inspection ‘‘A’’ includes an external
Amendment 39–18411; Docket No. phased array ultrasonic inspection for cracks
action. in the lower/overlapped skin of the stringer
FAA–2015–3146; Directorate Identifier
Regulatory Findings 2014–NM–249–AD. S–14 left and right (L/R) lap splices between
fuselage station 655 and station 1434, and an
This AD will not have federalism (a) Effective Date open hole high frequency eddy current
implications under Executive Order This AD is effective April 1, 2016. (HFEC) inspection for skin cracks at the
13132. This AD will not have a upper and lower fastener rows of the stringer
substantial direct effect on the States, on (b) Affected ADs S–14 L/R lap splices.
mstockstill on DSK4VPTVN1PROD with RULES
the relationship between the national None. (2) Inspection ‘‘B’’ includes the inspections
government and the States, or on the specified in paragraphs (g)(2)(i) through
(c) Applicability (g)(2)(iv) of this AD.
distribution of power and This AD applies to The Boeing Company (i) A detailed inspection for cracks of any
responsibilities among the various Model 777–200 series airplanes, certificated skin panel common to a stringer S–14 L/R lap
levels of government. in any category, as identified in Boeing Alert splice between fuselage station 655 and
For the reasons discussed above, I Service Bulletin 777–53A0052, dated October station 1434 that has a scribe line 0.001 inch
certify that this AD: 10, 2014. or deeper.
VerDate Sep<11>2014 17:33 Feb 25, 2016 Jkt 238001 PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 E:\FR\FM\26FER1.SGM 26FER1](https://thefederalregister.org/doc/81_FR_9787/page/2.svg)
![Federal Register / Vol. 81, No. 38 / Friday, February 26, 2016 / Rules and Regulations 9751
(ii) Either an ultrasonic inspection or a (j) Post-Modification Inspections and Airframe Branch, ANM–120S, FAA, Seattle
surface HFEC inspection for cracks Corrective Action ACO, 1601 Lind Avenue SW., Renton, WA
(depending on the location of the scribe At the applicable time specified in 98057–3356; phone: 425–917–6412; fax: 425–
line(s)) of any skin panel common to a paragraph 1.E., ‘‘Compliance,’’ of Boeing 917–6590; email: Eric.Lin@faa.gov.
stringer S–14 L/R lap splice between fuselage Alert Service Bulletin 777–53A0052, dated (m) Material Incorporated by Reference
station 655 and station 1434 that has a scribe October 10, 2014: Do a post-modification
line 0.001 inch or deeper. internal surface HFEC inspection for skin (1) The Director of the Federal Register
(iii) An external phased array ultrasonic cracks in the modified lap splices on both approved the incorporation by reference
inspection for cracks in the lower/overlapped sides of the airplane; and do all applicable (IBR) of the service information listed in this
skin of the stringer S–14 L/R lap splices corrective actions; in accordance with the paragraph under 5 U.S.C. 552(a) and 1 CFR
between fuselage station 655 and station Accomplishment Instructions of Boeing Alert part 51.
Service Bulletin 777–53A0052, dated October (2) You must use this service information
1434.
10, 2014, except as provided by paragraph as applicable to do the actions required by
(iv) An open hole HFEC inspection for skin
(h)(2) of this AD. Do all applicable corrective this AD, unless the AD specifies otherwise.
cracks at the upper and lower fastener rows
actions before further flight. Repeat the (i) Boeing Alert Service Bulletin 777–
of the stringer S–14 L/R lap splices. 53A0052, dated October 10, 2014.
(3) Inspection ‘‘C’’ includes the inspections inspection of the modified lap splices
thereafter at the applicable intervals specified (ii) Reserved.
for scribe lines and cracks specified in (3) For Boeing service information
paragraphs (g)(3)(i), (g)(3)(ii), and (g)(3)(iii) of in paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 777–53A0052, dated identified in this AD, contact Boeing
this AD on stringer S–14 L/R lap splice Commercial Airplanes, Attention: Data &
October 10, 2014.
between fuselage station 655 and station Services Management, P.O. Box 3707, MC
1434 on both sides of the airplane. (k) Alternative Methods of Compliance 2H–65, Seattle, WA 98124–2207; telephone
(i) A detailed inspection for scribe lines. If (AMOCs) 206–544–5000, extension 1; fax 206–766–
any scribe line is found during the inspection (1) The Manager, Seattle Aircraft 5680; Internet https://
required by this paragraph, the actions Certification Office (ACO), FAA, has the www.myboeingfleet.com.
include the inspections specified in authority to approve AMOCs for this AD, if (4) You may view this service information
paragraphs (g)(3)(i)(A) and (g)(3)(i)(B) of this requested using the procedures found in 14 at FAA, Transport Airplane Directorate, 1601
AD. CFR 39.19. In accordance with 14 CFR 39.19, Lind Avenue SW., Renton, WA. For
(A) A detailed inspection for cracks of the send your request to your principal inspector information on the availability of this
scribe line area(s). or local Flight Standards District Office, as material at the FAA, call 425–227–1221.
(B) Either an ultrasonic inspection or a appropriate. If sending information directly (5) You may view this service information
surface HFEC inspection for cracks to the manager of the ACO, send it to the that is incorporated by reference at the
(depending on the location of the scribe attention of the person identified in National Archives and Records
line(s)). paragraph (l) of this AD. Information may be Administration (NARA). For information on
(ii) An external phased array ultrasonic emailed to: 9-ANM-Seattle-ACO-AMOC- the availability of this material at NARA, call
inspection for cracks in the lower/overlapped Requests@faa.gov. 202–741–6030, or go to: http://
skin of the stringer S–14 L/R lap splices (2) Before using any approved AMOC, www.archives.gov/federal-register/cfr/ibr-
between fuselage station 655 and station notify your appropriate principal inspector, locations.html.
1434. or lacking a principal inspector, the manager
Issued in Renton, Washington, on February
(iii) An open hole HFEC inspection for skin of the local flight standards district office/
16, 2016.
cracks at the upper and lower fastener rows certificate holding district office.
(3) An AMOC that provides an acceptable Dionne Palermo,
of the stringer S–14 L/R lap splices. Acting Manager,
level of safety may be used for any repair,
(h) Exceptions to Service Information modification, or alteration required by this Transport Airplane Directorate, Aircraft
Specifications AD if it is approved by the Boeing Certification Service.
(1) Where Paragraph 1.E., ‘‘Compliance,’’ of Commercial Airplanes Organization [FR Doc. 2016–03886 Filed 2–25–16; 8:45 am]
Boeing Alert Service Bulletin 777–53A0052, Designation Authorization (ODA) that has BILLING CODE 4910–13–P
dated October 10, 2014, specifies a been authorized by the Manager, Seattle
ACO, to make those findings. To be
compliance time ‘‘after the original issue date
approved, the repair method, modification
of this service bulletin,’’ this AD requires DEPARTMENT OF TRANSPORTATION
deviation, or alteration deviation must meet
compliance within the specified compliance
the certification basis of the airplane, and the
time ‘‘after the effective date of this AD.’’ Federal Aviation Administration
approval must specifically refer to this AD.
(2) If, during accomplishment of any
(4) Except as required by paragraph (h)(2)
inspection required by this AD, any of this AD: For service information that 14 CFR Part 39
condition is found for which Boeing Alert contains steps that are labeled as Required
Service Bulletin 777–53A0052, dated October [Docket No. FAA–2015–2984; Directorate
for Compliance (RC), the provisions of Identifier 2015–NE–21–AD; Amendment 39–
10, 2014, specifies to contact Boeing for paragraphs (k)(4)(i) and (k)(4)(ii) apply.
special repair instructions or supplemental 18405; AD 2016–04–11]
(i) The steps labeled as RC, including
instructions for the modification, and substeps under an RC step and any figures RIN 2120–AA64
specifies that action as ‘‘RC’’ (Required for identified in an RC step, must be done to
Compliance): Before further flight, do the comply with the AD. An AMOC is required Airworthiness Directives; General
repair or modification using a method for any deviations to RC steps, including Electric Company Turbofan Engines
approved in accordance with the procedures substeps and identified figures.
specified in paragraph (k) of this AD. (ii) Steps not labeled as RC may be AGENCY: Federal Aviation
(i) Lap Splice Modification deviated from using accepted methods in Administration (FAA), DOT.
accordance with the operator’s maintenance ACTION: Final rule.
At the applicable time specified in or inspection program without obtaining
mstockstill on DSK4VPTVN1PROD with RULES
paragraph 1.E., ‘‘Compliance,’’ of Boeing approval of an AMOC, provided the RC steps, SUMMARY: We are adopting a new
Alert Service Bulletin 777–53A0052, dated including substeps and identified figures, can
October 10, 2014: Do the left-side and right-
airworthiness directive (AD) for all
still be done as specified, and the airplane General Electric Company (GE) GEnx–
side lap splice modification, in accordance can be put back in an airworthy condition.
with the Accomplishment Instructions of 1B54, –1B58, –1B64, –1B67, and –1B70
Boeing Alert Service Bulletin 777–53A0052, (l) Related Information turbofan engine models. This AD was
dated October 10, 2014, except as provided For more information about this AD, prompted by reports of two separate,
by paragraph (h)(2) of this AD. contact Eric Lin, Aerospace Engineer, single engine in-flight shutdowns
VerDate Sep<11>2014 17:33 Feb 25, 2016 Jkt 238001 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\26FER1.SGM 26FER1](https://thefederalregister.org/doc/81_FR_9787/page/3.svg)
Document Created: 2018-02-02 14:37:28
Document Modified: 2018-02-02 14:37:28
| 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 April 1, 2016. | |
| Contact | Eric Lin, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6412; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 81 FR 9749 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
2025 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR