81 FR 29206 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 91 (May 11, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 91 (May 11, 2016)
| Page Range | 29206-29209 | |
| FR Document | 2016-10915 |
[Federal Register Volume 81, Number 91 (Wednesday, May 11, 2016)] [Proposed Rules] [Pages 29206-29209] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-10915] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-6428; Directorate Identifier 2015-NM-119-AD] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This proposed AD was prompted by reports indicating that certain wing side-of-body stringer fittings have been installed with faying surface mismatch beyond the allowed machining tolerance. This proposed AD would 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 proposing 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 to a point where it cannot sustain limit load, which could adversely affect the structural integrity of the airplane. DATES: We must receive comments on this proposed AD by June 27, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, 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-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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Allen Rauschendorfer, Aerospace Engineer, Airframe Branch, ANM-120S, [[Page 29207]] 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: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2016-6428; Directorate Identifier 2015-NM-119-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We have received reports indicating that certain wing side-of-body stringer fittings have been installed with faying surface mismatch beyond the allowed machining tolerance. The fittings are assembled to the mating side-of-body rib chord. The faying surface mismatch produces a gouge in the mating surface which reduces the fatigue life, and could grow into a widespread fatigue condition on the upper side-of-body rib chord. We are proposing 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 to a point where it cannot sustain limit load, which could adversely affect the structural integrity of the airplane. 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. If faying surface mismatch is found, instructions are also given to replace 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. FAA's Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously, except as described in ``Differences Between this Proposed AD and the Service Information.'' Differences Between This Proposed AD and the Service Information Boeing Alert Service Bulletin B787-81205-SB570018-00, Issue 001, dated July 1, 2015, specifies to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions in one of the following ways: In accordance with a method that we approve; or Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Costs of Compliance We estimate that this proposed AD affects 5 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs -------------------------------------------------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ----------------------------------------------------------------------------------------------------------------------------------------- Modification and inspection................... 144 work-hours x $85 per hour = $100,079 $112,319 $561,595 $12,240. -------------------------------------------------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary corrective action for fretting damage or cutter mismatch that would be required based on the results of the proposed 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 cutter 9 work-hours x $85 per hour = $765.. $0 $765 mismatch. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for the crack repair specified in this proposed 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 [[Page 29208]] for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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): The Boeing Company: Docket No. FAA-2016-6428; Directorate Identifier 2015-NM-119-AD. (a) Comments Due Date We must receive comments by June 27, 2016. (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 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 to a point where it cannot sustain limit load, which could adversely affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection 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 fretting damage of the faying surface of the aluminum T-chord. (2) Do an eddy current inspection for cracking of the fastener holes. (3) Do a detailed inspection for a machine mismatch condition of the stringer 1 fitting faying surface. (h) Modifications 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 (1) 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]. (2) For service information identified in this AD, 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. [[Page 29209]] Issued in Renton, Washington, on May 3, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-10915 Filed 5-10-16; 8:45 am] BILLING CODE 4910-13-P
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1065, Revision 3, dated June 30, 2015: Do an been authorized by the Manager, Seattle fittings and upper side-of-body rib
external low frequency eddy current (LFEC) ACO, to make those findings. To be chord with tapered sleeve bolts. We are
inspection for cracking of the skin at the approved, the repair method, modification proposing this AD to prevent an
critical fastener row of the repair doubler; deviation, or alteration deviation must meet
and do all applicable corrective actions; in
unacceptable reduction of the fatigue
the certification basis of the airplane, and the
accordance the Accomplishment Instructions approval must specifically refer to this AD. life in the upper side-of-body rib chord.
of Boeing Special Attention Service Bulletin (4) AMOCs approved previously for AD Associated fatigue cracks can reduce the
737–53–1065, Revision 3, dated June 30, 2005–13–30, are approved as AMOCs for the structural capability to a point where it
2015, except as required by paragraph (i)(3) corresponding provisions of paragraph (h) of cannot sustain limit load, which could
of this AD. Do all applicable corrective this AD. adversely affect the structural integrity
actions before further flight. Repeat the LFEC of the airplane.
inspection thereafter at the applicable (p) Related Information
intervals specified in Boeing Special DATES: We must receive comments on
(1) For more information about this AD,
Attention Service Bulletin 737–53–1065, contact Wade Sullivan, Aerospace Engineer, this proposed AD by June 27, 2016.
Revision 3, dated June 30, 2015. Airframe Branch, ANM–120S, FAA, Seattle ADDRESSES: You may send comments,
(m) Skin Panel Replacement ACO, 1601 Lind Avenue SW., Renton, WA using the procedures found in 14 CFR
98057–3356; phone: 425–917–6430; fax: 425– 11.43 and 11.45, by any of the following
Except for Group 1 airplanes identified in 917–6590; email: wade.sullivan@faa.gov.
Boeing Special Attention Service Bulletin
methods:
737–53–1065, Revision 3, dated June 30,
(2) For service information identified in • Federal eRulemaking Portal: Go to
this AD, contact Boeing Commercial
2015: At the later of the times specified in http://www.regulations.gov. Follow the
Airplanes, Attention: Data & Services
paragraphs (m)(1) and (m)(2) of this AD: Management, P. O. Box 3707, MC 2H–65, instructions for submitting comments.
Replace the applicable skin panels, and do Seattle, WA 98124–2207; telephone 206– • Fax: 202–493–2251.
all applicable related investigative and 544–5000, extension 1; fax 206–766–5680; • Mail: U.S. Department of
corrective actions, in accordance with the Internet https://www.myboeingfleet.com. You Transportation, Docket Operations, M–
Accomplishment Instructions of Boeing may view this referenced service information 30, West Building Ground Floor, Room
Special Attention Service Bulletin 737–53– at the FAA, 1601 Lind Avenue SW., Renton, W12–140, 1200 New Jersey Avenue SE.,
1065, Revision 3, dated June 30, 2015. Do all Washington. For information on the
applicable related investigative and
Washington, DC 20590.
corrective actions before further flight. Doing
availability of this material at the FAA, call • Hand Delivery: Deliver to Mail
425–227–1221. address above between 9 a.m. and 5
the skin panel replacement required by this
paragraph terminates the inspection Issued in Renton, Washington, on May 4, p.m., Monday through Friday, except
requirements of paragraph (h) of this AD for 2016. Federal holidays.
that skin panel only, provided the skin panel Michael Kaszycki, For service information identified in
was replaced with a production skin panel Acting Manager, Transport Airplane this NPRM, contact Boeing Commercial
after 59,000 total flight cycles. Directorate, Aircraft Certification Service. Airplanes, Attention: Data & Services
(1) Before 60,000 total flight cycles, but not
[FR Doc. 2016–11095 Filed 5–10–16; 8:45 am] Management, P.O. Box 3707, MC 2H–65,
at or before 59,000 total flight cycles.
(2) Within 6,000 flight cycles after the BILLING CODE 4910–13–P Seattle, WA 98124–2207; telephone
effective date of this AD, but not at or before 206–544–5000, extension 1; fax 206–
59,000 total flight cycles. 766–5680; Internet https://
DEPARTMENT OF TRANSPORTATION www.myboeingfleet.com. You may view
(n) Credit for Previous Actions
this referenced service information at
This paragraph provides credit for the Federal Aviation Administration the FAA, Transport Airplane
actions required by paragraph (h) of this AD, Directorate, 1601 Lind Avenue SW.,
if those actions were performed before the 14 CFR Part 39
effective date of this AD using Boeing Special
Renton, WA. For information on the
Attention Service Bulletin 737–53–1065, [Docket No. FAA–2016–6428; Directorate availability of this material at the FAA,
Revision 2, dated April 19, 2001, which was Identifier 2015–NM–119–AD] call 425–227–1221. It is also available
incorporated by reference in AD 2005–13–30. on the Internet at http://
RIN 2120–AA64 www.regulations.gov by searching for
(o) Alternative Methods of Compliance
(AMOCs) and locating Docket No. FAA–2016–
Airworthiness Directives; The Boeing
6428.
(1) The Manager, Seattle Aircraft Company Airplanes
Certification Office (ACO), FAA, has the Examining the AD Docket
authority to approve AMOCs for this AD, if AGENCY: Federal Aviation
requested using the procedures found in 14 Administration (FAA), DOT. You may examine the AD docket on
CFR 39.19. In accordance with 14 CFR 39.19, ACTION: Notice of proposed rulemaking
the Internet at http://
send your request to your principal inspector (NPRM). www.regulations.gov by searching for
or local Flight Standards District Office, as and locating Docket No. FAA–2016–
appropriate. If sending information directly SUMMARY: We propose to adopt a new 6428; or in person at the Docket
to the manager of the ACO, send it to the airworthiness directive (AD) for certain Management Facility between 9 a.m.
attention of the person identified in and 5 p.m., Monday through Friday,
paragraph (p)(1) of this AD. Information may
The Boeing Company Model 787–8
airplanes. This proposed AD was except Federal holidays. The AD docket
be emailed to: 9–ANM-Seattle-ACO–AMOC-
Requests@faa.gov. prompted by reports indicating that contains this proposed AD, the
(2) Before using any approved AMOC, certain wing side-of-body stringer regulatory evaluation, any comments
notify your appropriate principal inspector, fittings have been installed with faying received, and other information. The
mstockstill on DSK3G9T082PROD with PROPOSALS
or lacking a principal inspector, the manager surface mismatch beyond the allowed street address for the Docket Office
of the local flight standards district office/ machining tolerance. This proposed AD (phone: 800–647–5527) is in the
certificate holding district office. would require inspection of certain ADDRESSES section. Comments will be
(3) An AMOC that provides an acceptable available in the AD docket shortly after
level of safety may be used for any repair,
stringer fittings for faying surface
mismatch common to the side-of-body receipt.
modification, or alteration required by this
AD if it is approved by the Boeing rib chord, replacement if necessary, and FOR FURTHER INFORMATION CONTACT:
Commercial Airplanes Organization replacement of the clearance fit Allen Rauschendorfer, Aerospace
Designation Authorization (ODA) that has fasteners common to the side-of-body Engineer, Airframe Branch, ANM–120S,
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for practices, methods, and procedures (c) Applicability (j) Alternative Methods of Compliance
the Administrator finds necessary for This AD applies to The Boeing Company (AMOCs)
safety in air commerce. This regulation Model 787–8 airplanes, certificated in any (1) The Manager, Seattle Aircraft
is within the scope of that authority category, as identified in Boeing Alert Certification Office (ACO), FAA, has the
because it addresses an unsafe condition Service Bulletin B787–81205–SB570018–00, authority to approve AMOCs for this AD, if
that is likely to exist or develop on Issue 001, dated July 1, 2015. requested using the procedures found in 14
products identified in this rulemaking CFR 39.19. In accordance with 14 CFR 39.19,
(d) Subject
action. send your request to your principal inspector
Air Transport Association (ATA) of or local Flight Standards District Office, as
Regulatory Findings America Code 57, Wings. appropriate. If sending information directly
(e) Unsafe Condition to the manager of the ACO, send it to the
We determined that this proposed AD attention of the person identified in
would not have federalism implications This AD was prompted by reports
paragraph (k)(1) of this AD. Information may
under Executive Order 13132. This indicating that certain wing side-of-body
be emailed to: 9–ANM-Seattle-ACO-AMOC-
proposed AD would not have a stringer fittings have been installed with
Requests@faa.gov.
substantial direct effect on the States, on faying surface mismatch beyond the allowed
(2) Before using any approved AMOC,
the relationship between the national machining tolerance. We are issuing this AD
notify your appropriate principal inspector,
to prevent an unacceptable reduction of the
Government and the States, or on the or lacking a principal inspector, the manager
fatigue life in the upper side-of-body rib
distribution of power and chord. Associated fatigue cracks can reduce of the local flight standards district office/
responsibilities among the various the structural capability to a point where it certificate holding district office.
levels of government. cannot sustain limit load, which could (3) An AMOC that provides an acceptable
For the reasons discussed above, I adversely affect the structural integrity of the level of safety may be used for any repair,
airplane. modification, or alteration required by this
certify this proposed regulation:
AD if it is approved by the Boeing
(1) Is not a ‘‘significant regulatory (f) Compliance Commercial Airplanes Organization
action’’ under Executive Order 12866, Comply with this AD within the Designation Authorization (ODA) that has
(2) Is not a ‘‘significant rule’’ under compliance times specified, unless already been authorized by the Manager, Seattle
the DOT Regulatory Policies and done. ACO, to make those findings. To be
Procedures (44 FR 11034, February 26, approved, the repair method, modification
(g) Inspection deviation, or alteration deviation must meet
1979),
Before the accumulation of 18,000 total the certification basis of the airplane, and the
(3) Will not affect intrastate aviation
flight cycles, or within 13 years after the approval must specifically refer to this AD.
in Alaska, and effective date of this AD, whichever occurs (4) Except as required by paragraph (i) of
(4) Will not have a significant first, do the inspections specified in this AD: For service information that
economic impact, positive or negative, paragraphs (g)(1), (g)(2), and (g)(3) of this AD, contains steps that are labeled as Required
on a substantial number of small entities and all applicable corrective actions, in for Compliance (RC), the provisions of
under the criteria of the Regulatory accordance with the Accomplishment paragraphs (j)(4)(i) and (j)(4)(ii) apply.
Flexibility Act. Instructions of Boeing Alert Service Bulletin (i) The steps labeled as RC, including
B787–81205–SB570018–00, Issue 001, dated substeps under an RC step and any figures
List of Subjects in 14 CFR Part 39 July 1, 2015, except as required by paragraph identified in an RC step, must be done to
(i) of this AD. Do all applicable corrective comply with the AD. An AMOC is required
Air transportation, Aircraft, Aviation actions before further flight. for any deviations to RC steps, including
safety, Incorporation by reference, (1) Do a detailed inspection for fretting substeps and identified figures.
Safety. damage of the faying surface of the aluminum (ii) Steps not labeled as RC may be
The Proposed Amendment T-chord. deviated from using accepted methods in
(2) Do an eddy current inspection for accordance with the operator’s maintenance
Accordingly, under the authority cracking of the fastener holes. or inspection program without obtaining
delegated to me by the Administrator, (3) Do a detailed inspection for a machine approval of an AMOC, provided the RC steps,
the FAA proposes to amend 14 CFR part mismatch condition of the stringer 1 fitting including substeps and identified figures, can
39 as follows: faying surface. still be done as specified, and the airplane
(h) Modifications can be put back in an airworthy condition.
PART 39—AIRWORTHINESS Concurrently with accomplishment of the (k) Related Information
DIRECTIVES requirements of paragraph (g) of this AD:
(1) For more information about this AD,
Modify the stringer fitting fasteners, and do
■ 1. The authority citation for part 39 contact Allen Rauschendorfer, Aerospace
an eddy current inspection for cracking of the
continues to read as follows: Engineer, Airframe Branch, ANM–120S,
fastener holes, in accordance with the
FAA, Seattle Aircraft Certification Office
Authority: 49 U.S.C. 106(g), 40113, 44701. Accomplishment Instructions of Boeing Alert
(ACO), 1601 Lind Avenue SW., Renton, WA
Service Bulletin B787–81205–SB570018–00,
Issue 001, dated July 1, 2015. If any crack is 98057–3356; phone: 425–917–6487; fax: 425–
§ 39.13 [Amended]
found, before further flight, repair using a 917–6590; email: allen.rauschendorfer@
■ 2. The FAA amends § 39.13 by adding method approved in accordance with the faa.gov.
the following new airworthiness procedures specified in paragraph (j) of this (2) For service information identified in
directive (AD): AD. this AD, Boeing Commercial Airplanes,
Attention: Data & Services Management, P. O.
The Boeing Company: Docket No. FAA–
mstockstill on DSK3G9T082PROD with PROPOSALS
(i) Exception to Service Information Box 3707, MC 2H–65, Seattle, WA 98124–
2016–6428; Directorate Identifier 2015– Specifications 2207; telephone 206–544–5000, extension 1;
NM–119–AD.
Where Boeing Alert Service Bulletin B787– fax 206–766–5680; Internet https://
(a) Comments Due Date 81205–SB570018–00, Issue 001, dated July 1, www.myboeingfleet.com. You may view this
We must receive comments by June 27, 2015, specifies to contact Boeing for repair of referenced service information at the FAA,
2016. cracking: Before further flight, repair the Transport Airplane Directorate, 1601 Lind
cracking using a method approved in Avenue SW., Renton, WA. For information
(b) Affected ADs accordance with the procedures specified in on the availability of this material at the
None. paragraph (j) of this AD. FAA, call 425–227–1221.
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![Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules 29209
Issued in Renton, Washington, on May 3, For service information identified in Directive 2015–0219, dated November 3,
2016. this NPRM, contact Airbus, 2015 (referred to after this as the
Michael Kaszycki, Airworthiness Office—EIAS, 1 Rond Mandatory Continuing Airworthiness
Acting Manager, Transport Airplane Point Maurice Bellonte, 31707 Blagnac Information, or ‘‘the MCAI’’), to correct
Directorate, Aircraft Certification Service. Cedex, France; telephone: +33 5 61 93 an unsafe condition for certain Airbus
[FR Doc. 2016–10915 Filed 5–10–16; 8:45 am] 36 96; fax: +33 5 61 93 44 51; email: Model A318–112 airplanes, A319–111,
BILLING CODE 4910–13–P account.airworth-eas@airbus.com; –112, –115, –132, and –133 airplanes,
Internet: http://www.airbus.com. You A320–214, –232, and –233 airplanes,
may view this referenced service and A321–211, –212, –213, –231, and
DEPARTMENT OF TRANSPORTATION information at the FAA, Transport –232 airplanes. The MCAI states:
Airplane Directorate, 1601 Lind Avenue Following an Airbus quality control review
Federal Aviation Administration SW., Renton, WA. For information on on the final assembly line, it was discovered
the availability of this material at the that aluminum alloy with inadequate heat
14 CFR Part 39 FAA, call 425–227–1221. treatment were delivered by a supplier for
[Docket No. FAA–2016–6431; Directorate several structural parts. The results of the
Examining the AD Docket investigations highlighted that 1% of the
Identifier 2015–NM–182–AD]
You may examine the AD docket on stock could be impacted by this wrong
RIN 2120–AA64 the Internet at http:// material.
www.regulations.gov by searching for Structural investigations demonstrated the
Airworthiness Directives; Airbus capability to sustain the static limits loads,
and locating Docket No. FAA–2016–
Airplanes and sufficient fatigue life up to a certain
6431; or in person at the Docket inspection threshold.
AGENCY: Federal Aviation Management Facility between 9 a.m. This condition, if not detected and
Administration (FAA), DOT. and 5 p.m., Monday through Friday, corrected, could reduce the aeroplane
ACTION: Notice of proposed rulemaking except Federal holidays. The AD docket structural integrity following fatigue load.
(NPRM). contains this proposed AD, the To address this potential unsafe condition,
regulatory evaluation, any comments Airbus issued Service Bulletin (SB) A320–
SUMMARY: We propose to adopt a new received, and other information. The 53–1292, SB A320–53–1293, and SB A320–
airworthiness directive (AD) for certain 53–1294 to provide inspection instructions.
street address for the Docket Operations
Airbus Model A318–112 airplanes, For the reasons described above, this
office (telephone: 800–647–5527) is in [EASA] AD requires a one-time Special
A319–111, –112, –115, –132, and –133 the ADDRESSES section. Comments will Detailed Inspection (SDI) [i.e., eddy current
airplanes, A320–214, –232, and –233 be available in the AD docket shortly conductivity measurement] of certain cabin,
airplanes, and A321–211, –212, –213, after receipt. cargo compartment and frame parts [for
–231, and –232 airplanes. This proposed FOR FURTHER INFORMATION CONTACT: material identification] and, depending on
AD was prompted by a quality control Sanjay Ralhan, Aerospace Engineer, findings, replacement with serviceable parts.
review on the final assembly line, which International Branch, ANM–116, You may examine the MCAI in the
determined that aluminum alloy with Transport Airplane Directorate, FAA, AD docket on the Internet at http://
inadequate heat treatment had been 1601 Lind Avenue SW., Renton, WA www.regulations.gov by searching for
delivered and used on several structural 98057–3356; telephone: 425–227–1405; and locating Docket No. FAA–2016–
parts. This proposed AD would require fax: 425–227–1149. 6431.
a one-time eddy current conductivity SUPPLEMENTARY INFORMATION:
measurement of certain cabin, cargo Related Service Information Under 1
compartment, and frame structural parts Comments Invited CFR Part 51
to determine if aluminum alloy with We invite you to send any written Airbus has issued the following
inadequate heat treatment was used, relevant data, views, or arguments about service information:
and replacement if necessary. We are this proposed AD. Send your comments • Airbus Service Bulletin A320–53–
proposing this AD to detect and replace to an address listed under the 1292, dated July 23, 2015; including
structural parts made of aluminum alloy ADDRESSES section. Include ‘‘Docket No. Appendices 01 and 02, dated July 23,
with inadequate heat treatment. This FAA–2016–6431; Directorate Identifier 2015.
condition could result in reduced 2015–NM–182–AD’’ at the beginning of • Airbus Service Bulletin A320–53–
structural integrity of the airplane. your comments. We specifically invite 1293, dated July 30, 2015; including
DATES: We must receive comments on comments on the overall regulatory, Appendices 01 and 02, dated July 30,
this proposed AD by June 27, 2016. economic, environmental, and energy 2015.
ADDRESSES: You may send comments, aspects of this proposed AD. We will • Airbus Service Bulletin A320–53–
using the procedures found in 14 CFR consider all comments received by the 1294, dated July 23, 2015; including
11.43 and 11.45, by any of the following closing date and may amend this Appendices 01 and 02, dated July 23,
methods: proposed AD based on those comments. 2015.
• Federal eRulemaking Portal: Go to We will post all comments we The service information describes
http://www.regulations.gov. Follow the receive, without change, to http:// procedures for a one-time eddy current
instructions for submitting comments. www.regulations.gov, including any conductivity measurement of certain
• Fax: 202–493–2251. personal information you provide. We cabin, cargo compartment, and frame
• Mail: U.S. Department of will also post a report summarizing each structural parts to determine if
mstockstill on DSK3G9T082PROD with PROPOSALS
Transportation, Docket Operations, M– substantive verbal contact we receive aluminum alloy with inadequate heat
30, West Building Ground Floor, Room about this proposed AD. treatment was used, and replacement of
W12–140, 1200 New Jersey Avenue SE., any affected part with a serviceable part.
Washington, DC 20590. Discussion This service information is reasonably
• Hand Delivery: Deliver to Mail The European Aviation Safety Agency available because the interested parties
address above between 9 a.m. and 5 (EASA), which is the Technical Agent have access to it through their normal
p.m., Monday through Friday, except for the Member States of the European course of business or by the means
Federal holidays. Union, has issued EASA Airworthiness identified in the ADDRESSES section.
VerDate Sep<11>2014 16:58 May 10, 2016 Jkt 238001 PO 00000 Frm 00041 Fmt 4702 Sfmt 4702 E:\FR\FM\11MYP1.SGM 11MYP1](https://thefederalregister.org/doc/81_FR_29297/page/4.svg)
Document Created: 2016-05-11 01:11:47
Document Modified: 2016-05-11 01:11:47
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by June 27, 2016. | |
| 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 | 81 FR 29206 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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