82 FR 3140 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 7 (January 11, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 7 (January 11, 2017)
| Page Range | 3140-3143 | |
| FR Document | 2016-31188 |
[Federal Register Volume 82, Number 7 (Wednesday, January 11, 2017)] [Rules and Regulations] [Pages 3140-3143] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-31188] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-6428; Directorate Identifier 2015-NM-119-AD; Amendment 39-18764; AD 2016-26-06] 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 787-8 airplanes. This AD was prompted by reports indicating that certain wing side-of-body upper stringer fittings have been installed with faying surface mismatch beyond the allowed machining tolerance. This AD requires inspections of certain stringer fittings, replacement if necessary, and replacement of certain fasteners. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective February 15, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 15, 2017. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740; telephone 562-797-1717; 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-2016-6428. 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- 6428; 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: Allen Rauschendorfer, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057- 3356; phone: 425-917-6487; 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 787-8 airplanes. The NPRM published in the Federal Register on May 11, 2016 (81 FR 29206) (``the NPRM''). The NPRM was prompted by reports indicating that certain wing side-of-body upper stringer fittings have been installed with faying surface mismatch beyond the allowed machining tolerance. The NPRM proposed to require inspection of certain stringer fittings for faying surface mismatch common to the side-of-body rib chord, replacement if necessary, and replacement of the clearance fit fasteners common to the side-of-body fittings and upper side-of-body rib chord with tapered sleeve bolts. We are issuing this AD to prevent an unacceptable reduction of the fatigue life in the upper side-of-body rib chord. Associated fatigue cracks can reduce the structural capability of the upper side-of-body t-chord to a point where it cannot sustain limit load, which could adversely affect the structural integrity of the airplane. 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. Request To Reference Revised Service Information United Airlines (UA) and All Nippon Airways (ANA) asked that we revise the NPRM to reference Boeing Alert Service Bulletin B787-81205- SB570018-00, Issue 002, because Boeing Alert Service Bulletin B787- 81205-SB570018-00, Issue 001, dated July 1, 2015, is currently being revised by Boeing. UA and ANA added that by including the revised service information for accomplishing the specified actions, requests for alternative methods of compliance (AMOCs) will be reduced. We do not agree because the revised service information is not yet released. In an AD, we cannot refer to service information that does not exist because doing so violates Office of the Federal Register (OFR) regulations for approval of materials incorporated by reference in rules. To allow operators to use service information issued after publication of an AD, either we must supersede the AD to reference specific service information, or operators must request approval to use the new service information as an AMOC for the AD under the provisions of paragraph (j) of this AD. We consider addressing the unsafe condition as soon as possible a necessity. We might consider issuing a global AMOC if revised service information is approved. We have not changed this AD in this regard. Request for Clarification of the Reason for the AD Boeing asked that we clarify that the proposed AD was prompted by reports indicating that the wing side-of-body stringer fittings that were installed with a faying surface mismatch beyond allowed tolerances were the upper stringer fittings. We agree that clarification of the language describing what prompted the AD is necessary. We have changed the SUMMARY section of this final rule, as well as paragraph (e) of this AD, to [[Page 3141]] include ``upper'' before ``stringer fittings.'' Request for Clarification of Certain Language in the Discussion Section Boeing asked that we clarify the Discussion section of the NPRM, which stated that the faying surface mismatch produces a gouge. Boeing requested that we revise this wording to indicate that a gouge produced from a faying surface mismatch is a possibility, not a certainty. We do not agree that the description in the Discussion section of the NPRM is inaccurate, because excessive cutter mismatch will produce a gouge in the mating surface eventually. In addition, the Discussion section of NPRMs is not fully repeated in final rules. Therefore, we have not changed this AD in this regard. Request for Clarification of Corrective Actions Boeing asked that we clarify the description of the corrective actions in the ``Related Service Information under 1 CFR part 51'' section of the NPRM by distinguishing certain conditions associated with the various corrective actions. We agree that clarification of the language is necessary. The ``Related Service Information under 1 CFR part 51'' section in an AD simply describes the various actions in the service information; it does not describe the detailed requirements with specific corrective actions for specific inspection findings. Therefore, we have changed that section in this final rule to simply list the different actions provided in Boeing Alert Service Bulletin B787-81205-SB570018-00, Issue 001, dated July 1, 2015. Request for Clarification of Certain Language in FAA's Determination Section Boeing asked that the word ``other'' be removed from the ``FAA's Determination'' section of the NPRM, which specifies that the unsafe condition ``is likely to exist or develop in other products of the same type design.'' Boeing stated that the unsafe condition resulted from a quality escapement applicable to specific line numbers, and therefore is not likely to develop in other products of the same type design (i.e., the entire 787-8 fleet). We do not agree to remove the word ``other'' from the specified sentence. In 14 CFR 39.5, which defines the reason for issuing ADs, it states that an AD addresses ``a product'' when the unsafe condition is likely to exist or develop in ``other products'' of the same type design. The product addressed by an AD refers to the airplane(s) associated with the incident or specific findings that prompted the AD. In this case, the ``other products'' extends to Model 787-8 airplanes that are identified in paragraph (c) of this AD--that is, airplanes identified in Boeing Alert Service Bulletin B787-81205-SB570018-00, Issue 001, dated July 1, 2015--not the entire fleet. We have not changed this AD in this regard. Request for Clarification of Compliance Time Boeing asked that we change the compliance time wording in paragraph (g) of the proposed AD for clarification by referring to Boeing Alert Service Bulletin B787-81205-SB570018-00, Issue 001, dated July 1, 2015, instead of specifying the actual compliance time. We do not agree with the request. Paragraph (g) of the proposed AD (which is retained in this final rule) provides the compliance time (before the accumulation of 18,000 total flight cycles, or within 13 years after the effective date of this AD, whichever occurs first) because the Accomplishment Instructions of the service information do not provide a compliance time for the inspection. We have not changed this AD regarding this issue. Request for Clarification of Type of Inspections and Applicable Corrective Actions Boeing asked that we clarify the description of the inspections specified in paragraphs (g)(1), (g)(2), and (g)(3) of the proposed AD as follows: (1) Do a detailed inspection for a machine mismatch condition of the stringer 1 fitting faying surface; (2) Do a detailed inspection of the faying surface of the aluminum T-chord common to stringer 1 fitting for fretting damage; and (3) Do an eddy current inspection for cracking of the fastener holes common to stringer fittings 1 and 5 through 11. Boeing stated that this will more closely match the information and sequence of the inspections specified in the referenced service information. We agree with the commenter's request to clarify the inspection language specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, for the reasons provided. We have clarified those paragraphs accordingly. Boeing asked that we revise paragraph (h) of the proposed AD to clarify the corrective actions. The commenter defined four corrective actions (which are also defined in the service information). We agree with the commenter's request in part. We do not agree to clarify the corrective actions because the actions described by the commenter are for the inspections required by paragraph (g) of this AD, and are clearly specified in Boeing Alert Service Bulletin B787-81205- SB570018-00, Issue 001, dated July 1, 2015. Those corrective actions are identified in paragraph (g) of this AD as, simply, ``corrective actions,'' and are further defined by reference to Boeing Alert Service Bulletin B787-81205-SB570018-00, Issue 001, dated July 1, 2015. However, we do agree to change the title of paragraph (h) of this AD to specify ``Modification, Inspection, and Repair'' to encompass the requirements specified in paragraph (h) of this AD. Request for Clarification of RC Steps To ensure that all provisions within the RC steps for contacting Boeing are captured, Boeing requested that we revise paragraph (i) of the proposed AD to refer to repair of the ``applicable condition'' instead of just ``cracking.'' We do not agree with the commenter's request. Boeing Alert Service Bulletin B787-81205-SB570018-00, Issue 001, dated July 1, 2015, specifies contacting Boeing if there is a crack; corrective actions for other discrepancies are provided within the service information. Boeing also asked that we add the following exception in paragraph (i) of the proposed AD: Additionally, where Boeing Alert Service Bulletin B787-81205- SB570018-00, Issue 001, dated July 1, 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. We do not agree to include the compliance time exception. As explained previously, the compliance times in this AD are defined using specific times instead of referring to the service information. Therefore, there are no exceptions to the service information regarding the compliance times in this AD. We have not changed this AD regarding this issue. 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 [[Page 3142]] 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 B787-81205-SB570018-00, Issue 001, dated July 1, 2015. The service information describes procedures for inspection of the left and right hand side stringer 1 fittings for faying surface mismatch common to the side-of-body rib chord, replacement of the stringer 1 fitting, and removal and replacement of the clearance fit fasteners common to the side-of-body fittings and upper side-of-body rib chord with tapered sleeve bolts from stringer 5 to stringer 11. 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 5 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 -------------------------------------------------------------------------------------------------------------------------------------------------------- Inspections and modification........... 144 work-hours x $85 per hour = $12,240........................ $100,079 $112,319 $561,595 -------------------------------------------------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary corrective action for fretting damage or cutter mismatch based on the results of the inspection. We have no way of determining the number of aircraft that might need these corrective actions: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Repair for fretting damage or 9 work-hours x $85 per hour = $765........... $0 $765 cutter mismatch. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that enables us to provide cost estimates for the crack repair 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): 2016-26-06 The Boeing Company: Amendment 39-18764; Docket No. FAA- 2016-6428; Directorate Identifier 2015-NM-119-AD. (a) Effective Date This AD is effective February 15, 2017. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 787-8 airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin B787-81205-SB570018-00, Issue 001, dated July 1, 2015. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Unsafe Condition This AD was prompted by reports indicating that certain wing side-of-body upper stringer fittings have been installed with faying surface mismatch beyond the allowed machining tolerance. We are issuing this AD to prevent an unacceptable reduction of the fatigue life in the upper side-of-body rib chord. Associated fatigue cracks can reduce the structural capability of the upper side-of-body t- chord to a point where it cannot sustain limit load, which could [[Page 3143]] adversely affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection and Corrective Actions Before the accumulation of 18,000 total flight cycles, or within 13 years after the effective date of this AD, whichever occurs first, do the inspections specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, and all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin B787-81205-SB570018-00, Issue 001, dated July 1, 2015, except as required by paragraph (i) of this AD. Do all applicable corrective actions before further flight. (1) Do a detailed inspection for a machine mismatch condition of the stringer 1 fitting faying surface. (2) Do a detailed inspection of the faying surface of the aluminum T-chord common to the stringer 1 fitting for fretting damage. (3) Do an eddy current inspection for cracking of the fastener holes common to stringer fitting 1 and stringer fittings 5 through 11. (h) Modification, Inspection, and Repair Concurrently with accomplishment of the requirements of paragraph (g) of this AD: Modify the stringer fitting fasteners, and do an eddy current inspection for cracking of the fastener holes, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin B787-81205-SB570018-00, Issue 001, dated July 1, 2015. If any crack is found, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (j) of this AD. (i) Exception to Service Information Specifications Where Boeing Alert Service Bulletin B787-81205-SB570018-00, Issue 001, dated July 1, 2015, specifies to contact Boeing for repair of cracking: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (j) of this AD. (j) 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 (k)(1) 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 (i) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (j)(4)(i) and (j)(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. (k) Related Information For more information about this AD, contact Allen Rauschendorfer, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6487; fax: 425-917-6590; email: [email protected]. (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 the AD specifies otherwise. (i) Boeing Alert Service Bulletin B787-81205-SB570018-00, Issue 001, dated July 1, 2015. (ii) Reserved. (3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740; telephone 562-797-1717; 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 December 15, 2016. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-31188 Filed 1-10-17; 8:45 am] BILLING CODE 4910-13-P
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(ii) Reserved. Boeing Commercial Airplanes, issuing this AD to prevent an
(3) For Boeing service information Attention: Contractual & Data Services unacceptable reduction of the fatigue
identified in this AD, contact Boeing (C&DS), 2600 Westminster Blvd., MC life in the upper side-of-body rib chord.
Commercial Airplanes, Attention: 110–SK57, Seal Beach, CA 90740; Associated fatigue cracks can reduce the
Contractual & Data Services (C&DS), 2600
Westminster Blvd., MC 110–SK57, Seal
telephone 562–797–1717; Internet structural capability of the upper side-
Beach, CA 90740–5600; telephone: 562–797– https://www.myboeingfleet.com. You of-body t-chord to a point where it
1717; Internet: https:// may view this referenced service cannot sustain limit load, which could
www.myboeingfleet.com. information at the FAA, Transport adversely affect the structural integrity
(4) You may view this service information Airplane Directorate, 1601 Lind Avenue of the airplane.
at the FAA, Transport Airplane Directorate, SW., Renton, WA. For information on
1601 Lind Avenue SW., Renton, WA. For Comments
the availability of this material at the
information on the availability of this FAA, call 425–227–1221. It is also We gave the public the opportunity to
material at the FAA, call 425–227–1221. available on the Internet at http:// participate in developing this AD. The
(5) You may view this service information
that is incorporated by reference at the
www.regulations.gov by searching for following presents the comments
National Archives and Records and locating Docket No. FAA–2016– received on the NPRM and the FAA’s
Administration (NARA). For information on 6428. response to each comment.
the availability of this material at NARA, call Examining the AD Docket Request To Reference Revised Service
202–741–6030, or go to: http://
www.archives.gov/federal-register/cfr/ibr- You may examine the AD docket on Information
locations.html. the Internet at http:// United Airlines (UA) and All Nippon
Issued in Renton, Washington, on www.regulations.gov by searching for Airways (ANA) asked that we revise the
December 15, 2016. and locating Docket No. FAA–2016– NPRM to reference Boeing Alert Service
Victor Wicklund, 6428; or in person at the Docket Bulletin B787–81205–SB570018–00,
Acting Manager, Transport Airplane Management Facility between 9 a.m. Issue 002, because Boeing Alert Service
Directorate, Aircraft Certification Service. and 5 p.m., Monday through Friday, Bulletin B787–81205–SB570018–00,
[FR Doc. 2016–31187 Filed 1–10–17; 8:45 am] except Federal holidays. The AD docket Issue 001, dated July 1, 2015, is
BILLING CODE 4910–13–P
contains this AD, the regulatory currently being revised by Boeing. UA
evaluation, any comments received, and and ANA added that by including the
other information. The address for the revised service information for
DEPARTMENT OF TRANSPORTATION Docket Office (phone: 800–647–5527) is accomplishing the specified actions,
Docket Management Facility, U.S. requests for alternative methods of
Federal Aviation Administration Department of Transportation, Docket compliance (AMOCs) will be reduced.
Operations, M–30, West Building We do not agree because the revised
14 CFR Part 39 Ground Floor, Room W12–140, 1200 service information is not yet released.
New Jersey Avenue SE., Washington, In an AD, we cannot refer to service
[Docket No. FAA–2016–6428; Directorate
Identifier 2015–NM–119–AD; Amendment DC 20590. information that does not exist because
39–18764; AD 2016–26–06] FOR FURTHER INFORMATION CONTACT: doing so violates Office of the Federal
Allen Rauschendorfer, Aerospace Register (OFR) regulations for approval
RIN 2120–AA64
Engineer, Airframe Branch, ANM–120S, of materials incorporated by reference in
Airworthiness Directives; The Boeing FAA, Seattle Aircraft Certification rules. To allow operators to use service
Company Airplanes Office (ACO), 1601 Lind Avenue SW., information issued after publication of
Renton, WA 98057–3356; phone: 425– an AD, either we must supersede the AD
AGENCY: Federal Aviation 917–6487; fax: 425–917–6590; email: to reference specific service
Administration (FAA), DOT. allen.rauschendorfer@faa.gov. information, or operators must request
ACTION: Final rule. SUPPLEMENTARY INFORMATION: approval to use the new service
information as an AMOC for the AD
SUMMARY: We are adopting a new Discussion under the provisions of paragraph (j) of
airworthiness directive (AD) for certain We issued a notice of proposed this AD. We consider addressing the
The Boeing Company Model 787–8 rulemaking (NPRM) to amend 14 CFR unsafe condition as soon as possible a
airplanes. This AD was prompted by part 39 by adding an AD that would necessity. We might consider issuing a
reports indicating that certain wing apply to certain The Boeing Company global AMOC if revised service
side-of-body upper stringer fittings have Model 787–8 airplanes. The NPRM information is approved. We have not
been installed with faying surface published in the Federal Register on changed this AD in this regard.
mismatch beyond the allowed May 11, 2016 (81 FR 29206) (‘‘the
machining tolerance. This AD requires Request for Clarification of the Reason
NPRM’’). The NPRM was prompted by for the AD
inspections of certain stringer fittings, reports indicating that certain wing
replacement if necessary, and side-of-body upper stringer fittings have Boeing asked that we clarify that the
replacement of certain fasteners. We are been installed with faying surface proposed AD was prompted by reports
issuing this AD to address the unsafe mismatch beyond the allowed indicating that the wing side-of-body
condition on these products. machining tolerance. The NPRM stringer fittings that were installed with
DATES: This AD is effective February 15, proposed to require inspection of a faying surface mismatch beyond
sradovich on DSK3GMQ082PROD with RULES
2017. certain stringer fittings for faying surface allowed tolerances were the upper
The Director of the Federal Register mismatch common to the side-of-body stringer fittings.
approved the incorporation by reference rib chord, replacement if necessary, and We agree that clarification of the
of a certain publication listed in this AD replacement of the clearance fit language describing what prompted the
as of February 15, 2017. fasteners common to the side-of-body AD is necessary. We have changed the
ADDRESSES: For service information fittings and upper side-of-body rib SUMMARY section of this final rule, as
identified in this final rule, contact chord with tapered sleeve bolts. We are well as paragraph (e) of this AD, to
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• Do not add any additional burden Issue 001, dated July 1, 2015. The information is reasonably available
upon the public than was already service information describes because the interested parties have
proposed in the NPRM. procedures for inspection of the left and access to it through their normal course
We also determined that these right hand side stringer 1 fittings for of business or by the means identified
changes will not increase the economic faying surface mismatch common to the in the ADDRESSES section.
burden on any operator or increase the side-of-body rib chord, replacement of
scope of this AD. the stringer 1 fitting, and removal and Costs of Compliance
replacement of the clearance fit
Related Service Information Under 1 We estimate that this AD affects 5
fasteners common to the side-of-body
CFR Part 51 airplanes of U.S. registry.
fittings and upper side-of-body rib
We reviewed Boeing Alert Service chord with tapered sleeve bolts from We estimate the following costs to
Bulletin B787–81205–SB570018–00, stringer 5 to stringer 11. This service comply with this AD:
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Inspections and modification ........................... 144 work-hours × $85 per hour = $12,240 ... $100,079 $112,319 $561,595
We estimate the following costs to do based on the results of the inspection. number of aircraft that might need these
any necessary corrective action for We have no way of determining the corrective actions:
fretting damage or cutter mismatch
ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Repair for fretting damage or cutter mismatch .............................................. 9 work-hours × $85 per hour = $0 $765
$765.
We have received no definitive data distribution of power and § 39.13 [Amended]
that enables us to provide cost estimates responsibilities among the various
for the crack repair specified in this AD. levels of government. ■ 2. The FAA amends § 39.13 by adding
the following new airworthiness
Authority for This Rulemaking For the reasons discussed above, I
directive (AD):
certify that this AD:
Title 49 of the United States Code (1) Is not a ‘‘significant regulatory 2016–26–06 The Boeing Company:
specifies the FAA’s authority to issue action’’ under Executive Order 12866, Amendment 39–18764; Docket No.
rules on aviation safety. Subtitle I, FAA–2016–6428; Directorate Identifier
(2) Is not a ‘‘significant rule’’ under 2015–NM–119–AD.
section 106, describes the authority of
DOT Regulatory Policies and Procedures
the FAA Administrator. Subtitle VII: (a) Effective Date
(44 FR 11034, February 26, 1979),
Aviation Programs, describes in more
detail the scope of the Agency’s (3) Will not affect intrastate aviation This AD is effective February 15, 2017.
authority. in Alaska, and (b) Affected ADs
We are issuing this rulemaking under (4) Will not have a significant
None.
the authority described in Subtitle VII, economic impact, positive or negative,
Part A, Subpart III, Section 44701: on a substantial number of small entities (c) Applicability
‘‘General requirements.’’ Under that under the criteria of the Regulatory This AD applies to The Boeing Company
section, Congress charges the FAA with Flexibility Act. Model 787–8 airplanes, certificated in any
promoting safe flight of civil aircraft in category, as identified in Boeing Alert
List of Subjects in 14 CFR Part 39 Service Bulletin B787–81205–SB570018–00,
air commerce by prescribing regulations
Air transportation, Aircraft, Aviation Issue 001, dated July 1, 2015.
for practices, methods, and procedures
the Administrator finds necessary for safety, Incorporation by reference, (d) Subject
safety in air commerce. This regulation Safety. Air Transport Association (ATA) of
is within the scope of that authority Adoption of the Amendment America Code 57, Wings.
because it addresses an unsafe condition
Accordingly, under the authority (e) Unsafe Condition
that is likely to exist or develop on
products identified in this rulemaking delegated to me by the Administrator, This AD was prompted by reports
action. the FAA amends 14 CFR part 39 as indicating that certain wing side-of-body
follows: upper stringer fittings have been installed
sradovich on DSK3GMQ082PROD with RULES
Regulatory Findings with faying surface mismatch beyond the
PART 39—AIRWORTHINESS allowed machining tolerance. We are issuing
This AD will not have federalism
DIRECTIVES this AD to prevent an unacceptable reduction
implications under Executive Order of the fatigue life in the upper side-of-body
13132. This AD will not have a rib chord. Associated fatigue cracks can
substantial direct effect on the States, on ■ 1. The authority citation for part 39
reduce the structural capability of the upper
the relationship between the national continues to read as follows: side-of-body t-chord to a point where it
government and the States, or on the Authority: 49 U.S.C. 106(g), 40113, 44701. cannot sustain limit load, which could
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![Federal Register / Vol. 82, No. 7 / Wednesday, January 11, 2017 / Rules and Regulations 3143
adversely affect the structural integrity of the (3) An AMOC that provides an acceptable Issued in Renton, Washington, on
airplane. level of safety may be used for any repair, December 15, 2016.
modification, or alteration required by this Victor Wicklund,
(f) Compliance
AD if it is approved by the Boeing Acting Manager, Transport Airplane
Comply with this AD within the Commercial Airplanes Organization Directorate, Aircraft Certification Service.
compliance times specified, unless already Designation Authorization (ODA) that has
done. [FR Doc. 2016–31188 Filed 1–10–17; 8:45 am]
been authorized by the Manager, Seattle
ACO, to make those findings. To be BILLING CODE 4910–13–P
(g) Inspection and Corrective Actions
approved, the repair method, modification
Before the accumulation of 18,000 total deviation, or alteration deviation must meet
flight cycles, or within 13 years after the the certification basis of the airplane, and the DEPARTMENT OF TRANSPORTATION
effective date of this AD, whichever occurs approval must specifically refer to this AD.
first, do the inspections specified in (4) Except as required by paragraph (i) of Federal Aviation Administration
paragraphs (g)(1), (g)(2), and (g)(3) of this AD, this AD: For service information that
and all applicable corrective actions, in contains steps that are labeled as Required 14 CFR Part 39
accordance with the Accomplishment for Compliance (RC), the provisions of
Instructions of Boeing Alert Service Bulletin paragraphs (j)(4)(i) and (j)(4)(ii) apply.
B787–81205–SB570018–00, Issue 001, dated [Docket No. FAA–2016–9113; Directorate
(i) The steps labeled as RC, including Identifier 2016–NM–042–AD; Amendment
July 1, 2015, except as required by paragraph substeps under an RC step and any figures
(i) of this AD. Do all applicable corrective 39–18772; AD 2017–01–05]
identified in an RC step, must be done to
actions before further flight. comply with the AD. An AMOC is required
(1) Do a detailed inspection for a machine for any deviations to RC steps, including RIN 2120–AA64
mismatch condition of the stringer 1 fitting substeps and identified figures.
faying surface. (ii) Steps not labeled as RC may be Airworthiness Directives; Airbus
(2) Do a detailed inspection of the faying deviated from using accepted methods in Defense and Space S.A. (Formerly
surface of the aluminum T-chord common to accordance with the operator’s maintenance Known as Construcciones
the stringer 1 fitting for fretting damage. or inspection program without obtaining
(3) Do an eddy current inspection for
Aeronauticas, S.A.) Airplanes
approval of an AMOC, provided the RC steps,
cracking of the fastener holes common to including substeps and identified figures, can AGENCY: Federal Aviation
stringer fitting 1 and stringer fittings 5 still be done as specified, and the airplane Administration (FAA), Department of
through 11. can be put back in an airworthy condition. Transportation (DOT).
(h) Modification, Inspection, and Repair (k) Related Information ACTION: Final rule.
Concurrently with accomplishment of the For more information about this AD,
requirements of paragraph (g) of this AD: SUMMARY: We are adopting a new
contact Allen Rauschendorfer, Aerospace
Modify the stringer fitting fasteners, and do airworthiness directive (AD) for all
Engineer, Airframe Branch, ANM–120S,
an eddy current inspection for cracking of the Airbus Defense and Space S.A. Model
FAA, Seattle Aircraft Certification Office
fastener holes, in accordance with the CN–235, CN–235–100, CN 235–200, and
(ACO), 1601 Lind Avenue SW., Renton, WA
Accomplishment Instructions of Boeing Alert
Service Bulletin B787–81205–SB570018–00,
98057–3356; phone: 425–917–6487; fax: 425– CN–235–300 airplanes. This AD was
917–6590; email: allen.rauschendorfer@ prompted by reports of cracks in certain
Issue 001, dated July 1, 2015. If any crack is
faa.gov. areas of the rear fuselage. This AD
found, before further flight, repair using a
method approved in accordance with the (l) Material Incorporated by Reference requires repetitive borescope and
procedures specified in paragraph (j) of this (1) The Director of the Federal Register detailed visual inspections of the rear
AD. approved the incorporation by reference fuselage lateral beam and its external
(i) Exception to Service Information (IBR) of the service information listed in this area, and repair if necessary. We are
Specifications paragraph under 5 U.S.C. 552(a) and 1 CFR issuing this AD to address the unsafe
Where Boeing Alert Service Bulletin B787– part 51. condition on these products.
81205–SB570018–00, Issue 001, dated July 1, (2) You must use this service information DATES: This AD is effective February 15,
as applicable to do the actions required by
2015, specifies to contact Boeing for repair of 2017.
cracking: Before further flight, repair the this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin B787– The Director of the Federal Register
cracking using a method approved in approved the incorporation by reference
accordance with the procedures specified in 81205–SB570018–00, Issue 001, dated July 1,
2015. of a certain publications listed in this
paragraph (j) of this AD.
(ii) Reserved. AD as of February 15, 2017.
(j) Alternative Methods of Compliance (3) For service information identified in ADDRESSES: For service information
(AMOCs) this AD, contact Boeing Commercial
identified in this final rule, contact
(1) The Manager, Seattle Aircraft Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
Airbus Defence and Space, Services/
Certification Office (ACO), FAA, has the
MC 110–SK57, Seal Beach, CA 90740; Engineering Support, Avenida de
authority to approve AMOCs for this AD, if
requested using the procedures found in 14 telephone 562–797–1717; Internet https:// Aragón 404, 28022 Madrid, Spain;
CFR 39.19. In accordance with 14 CFR 39.19, www.myboeingfleet.com. telephone +34 91 585 55 84; fax +34 91
send your request to your principal inspector (4) You may view this service information 585 31 27; email
or local Flight Standards District Office, as at the FAA, Transport Airplane Directorate, MTA.TechnicalService@Airbus.com.
appropriate. If sending information directly 1601 Lind Avenue SW., Renton, WA. For You may view this referenced service
to the manager of the ACO, send it to the information on the availability of this information at the FAA, Transport
attention of the person identified in material at the FAA, call 425–227–1221. Airplane Directorate, 1601 Lind Avenue
sradovich on DSK3GMQ082PROD with RULES
paragraph (k)(1) of this AD. Information may (5) You may view this service information SW., Renton, WA. For information on
be emailed to: 9-ANM-Seattle-ACO-AMOC- that is incorporated by reference at the
National Archives and Records
the availability of this material at the
Requests@faa.gov.
(2) Before using any approved AMOC, Administration (NARA). For information on FAA, call 425–227–1221. It is also
notify your appropriate principal inspector, the availability of this material at NARA, call available on the Internet at http://
or lacking a principal inspector, the manager 202–741–6030, or go to: http:// www.regulations.gov by searching for
of the local flight standards district office/ www.archives.gov/federal-register/cfr/ibr- and locating Docket No. FAA–2016–
certificate holding district office. locations.html. 9113.
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Document Created: 2018-02-01 14:59:10
Document Modified: 2018-02-01 14:59:10
| 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 February 15, 2017. | |
| Contact | Allen Rauschendorfer, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057- 3356; phone: 425-917-6487; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 82 FR 3140 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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