81 FR 8157 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 32 (February 18, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 32 (February 18, 2016)
| Page Range | 8157-8160 | |
| FR Document | 2016-03297 |
[Federal Register Volume 81, Number 32 (Thursday, February 18, 2016)] [Proposed Rules] [Pages 8157-8160] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-03297] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-3697; Directorate Identifier 2015-NM-143-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 supersede Airworthiness Directive (AD) 2011-01- 15, which applies to certain The Boeing Company Model 757-200, -200CB, and -300 series airplanes. AD 2011-01-15 currently requires repetitive inspections for cracking of the fuselage skin of the crown skin panel along the chem-milled step at stringers S-4L (left) and S-4R (right), from stations (STA) 297 through STA 439, and repair, if necessary. AD 2011-01-15 also includes terminating action for the repetitive inspections of the repaired areas only. Since we issued AD 2011-01-15, we received reports of the initiation of new fatigue cracking in the fuselage skin of the crown skin panel along locally thinned channels adjacent to the chem-milled steps. This proposed AD would add repetitive inspections for cracking in additional areas and repair if necessary. This proposed AD would also remove airplanes from the applicability in AD 2011-01-15. This proposed AD would also add an optional skin panel replacement which would terminate all inspections and an optional preventative modification that would terminate certain inspections. We are proposing this AD to detect and correct fatigue cracking of the fuselage skin of the crown skin panel, which could result in pressure venting and consequent rapid decompression of the airplane. DATES: We must receive comments on this proposed AD by April 4, 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, 3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001; telephone: 206-544-5000, extension 2; fax: 206-766-5683; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 3697. 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- 3697; 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: Eric Schrieber, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5348; fax: 562-627-5210; email: [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2016-3697; Directorate Identifier 2015-NM-143-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 On December 28, 2010, we issued AD 2011-01-15, Amendment 39-16572 (76 FR 1351, January 10, 2011), for certain The Boeing Company Model 757-200, -200CB, and -300 series airplanes. AD 2011-01-15 requires repetitive inspections for cracking of the fuselage skin of the crown skin panel along the [[Page 8158]] chem-milled step at stringers S-4L and S-4R, from stations (STA) 297 through STA 439, and repair if necessary. AD 2011-01-15 also includes terminating action for the repetitive inspections of the repaired areas only. AD 2011-01-15 resulted from reports of cracking in the fuselage skin of the crown skin panel. We issued AD 2011-01-15 to detect and correct fatigue cracking of the fuselage skin of the crown skin panel, which could result in pressure venting and consequent rapid decompression of the airplane. Actions Since AD 2011-01-15, Amendment 39-16572 (76 FR 1351, January 10, 2011), Was Issued The preamble to AD 2011-01-15, Amendment 39-16572 (76 FR 1351, January 10, 2011), specifies that we consider the requirements ``interim action.'' AD 2011-01-15 explains that we might consider further rulemaking if final action is later identified. We now have determined that it is necessary to initiate further rulemaking to add repetitive inspections for cracking in additional areas for certain airplanes, and repair if necessary. We have removed Model 757-200 CB series airplanes from the applicability because the crown skins on those airplanes are manufactured differently and therefore are not affected by the identified unsafe condition. We have also determined that the external detailed inspection that is allowed as an option in AD 2011-01-15, Amendment 39-16572 (76 FR 1351, January 12, 2011), does not adequately address the identified unsafe condition. Only eddy current inspections are adequate to address the identified unsafe condition. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Special Attention Service Bulletin 757-53-0097, Revision 2, dated July 28, 2015. The service information describes procedures for repetitive external sliding probe eddy current (EC) and external spot-probe-medium-frequency EC inspections for cracking of the crown skin panel, repair, a preventive modification, and replacement of the crown skin panel. 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. For information on the procedures and compliance times, see this service information at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 3697. Explanation of ``RC'' Steps in Service Information The FAA worked in conjunction with industry, under the Airworthiness Directive Implementation Aviation Rulemaking Committee (ARC), to enhance the AD system. One enhancement was a new process for annotating which steps in the service information are required for compliance with an AD. Differentiating these steps from other tasks in the service information is expected to improve an owner's/operator's understanding of crucial AD requirements and help provide consistent judgment in AD compliance. The steps identified as RC (required for compliance) in any service information identified previously have a direct effect on detecting, preventing, resolving, or eliminating an identified unsafe condition. Costs of Compliance We estimate that this proposed AD affects 652 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspections (Zone 1) [Retained 2 work-hour x $85 per $0............... $170 per $110,840 per actions from AD 2011-01-15, hour = $170 per inspection cycle. inspection Amendment 39[dash]16572 (76 FR inspection cycle. cycle. 1351, January 10, 2011)]. Inspections (Zones 2 and 3) Up to 4 work-hours x $0............... Up to $340 per $221,680 per [new proposed action]. $85 per hour = Up to inspection cycle. inspection $340 per inspection cycle. cycle. Optional modification.......... Up to 615 work-hours x Up to $26,496.... Up to $78,771.... Up to $85 per hour = Up to $51,358,692. $52,275. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide a cost estimate for the on-condition actions specified in this proposed AD. We have received no definitive data that would enable us to provide a cost estimate for the optional replacement 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 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 have 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 that the proposed regulation: [[Page 8159]] (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 removing Airworthiness Directive (AD) 2011-01-15, Amendment 39-16572 (76 FR 1351, January 10, 2011), and adding the following new AD: The Boeing Company: Docket No. FAA-2016-3697; Directorate Identifier 2015-NM-143-AD. (a) Comments Due Date The FAA must receive comments on this AD action by April 4, 2016. (b) Affected ADs This AD replaces AD 2011-01-15, Amendment 39-16572 (76 FR 1351, January 10, 2011). (c) Applicability (c) This AD applies to The Boeing Company Model 757-200 and -300 series airplanes, certificated in any category, as identified in Boeing Special Attention Service Bulletin 757-53-0097, Revision 2, dated July 28, 2015. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by reports of the initiation of fatigue cracking in the fuselage skin of the crown skin panel along locally thinned channels adjacent to the chem-milled steps. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin of the crown skin panel, which could result in pressure venting and consequent rapid decompression of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections Do the applicable inspections required by paragraphs (g)(1), (g)(2), and (g)(3) of this AD. (1) For all airplanes: At the applicable time specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 757-53-0097, Revision 2, dated July 28, 2015: Do the inspection specified in paragraph (g)(1)(i) or (g)(1)(ii) of this AD in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757-53-0097, Revision 2, dated July 28, 2015. Repeat the inspection thereafter at the applicable times specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 757-53-0097, Revision 2, dated July 28, 2015. Accomplishing the preventative modification specified in paragraph (j)(1) of this AD or the replacement specified in paragraph (j)(2) of this AD terminates the inspections required by this paragraph. (i) Do an external sliding probe eddy current (EC) inspection for cracking of the crown skin panel at stringers S-4L (left) and S- 4R (right). (ii) Do an external spot-probe-medium-frequency EC inspection for cracking of the crown skin panel at stringers S-4L and S-4R. (2) For airplanes on which any crack is found during any inspection required by paragraph (g)(1) of this AD; or any repair is installed that covers the Zone 1 inspection area specified in Boeing Special Attention Service Bulletin 757-53-0097, Revision 2, dated July 28, 2015; or any preventive modification is installed as specified in Part 3 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757-53-0097, Revision 2, dated July 28, 2015: At the applicable time specified in table 2 of paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 757-53-0097, Revision 2, dated July 28, 2015, except as required by paragraph (k)(1) of this AD: Do the inspection specified in paragraph (g)(2)(i) or (g)(2)(ii) of this AD, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757-53-0097, Revision 2, dated July 28, 2015. Repeat the inspection thereafter at the applicable times specified in table 2 of paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 757-53-0097, Revision 2, dated July 28, 2015. Accomplishing the replacement specified in paragraph (j)(2) of this AD terminates the inspections required by this paragraph. (i) Do an external sliding probe EC inspection for cracking of the crown skin panel at stringers S-2L, S-3L, and S-3R, as applicable. (ii) Do an external spot-probe-medium-frequency EC inspection for cracking of the crown skin panel at stringers S-2L, S-3L, and S- 3R, as applicable. (3) For airplanes on which any crack is found during any inspection required by paragraph (g)(1) of this AD; or any repair is installed that covers the Zone 1 inspection area specified in Boeing Special Attention Service Bulletin 757-53-0097, Revision 2, dated July 28, 2015; or any preventive modification is installed as specified in Part 3 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757-53-0097, Revision 2, dated July 28, 2015: At the applicable time specified in table 3 of paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 757-53-0097, Revision 2, dated July 28, 2015, except as required by paragraph (k)(1) of this AD: Do the inspection specified in paragraph (g)(3)(i) or (g)(3)(ii) of this AD, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757-53-0097, Revision 2, dated July 28, 2015. Repeat the inspection thereafter at the applicable times specified in table 3 of paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 757-53-0097, Revision 2, dated July 28, 2015. Accomplishing the replacement specified in paragraph (j)(2) of this AD terminates the inspections required by this paragraph. (i) Do an external sliding probe EC inspection for cracking of the crown skin panel at stringers S-3L and S-3R. (ii) Do an external spot-probe-medium-frequency EC inspection for cracking of the crown skin panel at stringers S-3L and S-3R. (h) Post-Preventive Modification Supplemental Inspections For airplanes on which a preventive modification has been installed as specified in Part 3 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757-53-0097, Revision 2, dated July 28, 2015: At the applicable time specified in table 4 of paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 757-53-0097, Revision 2, dated July 28, 2015; do eddy current and detailed inspections for cracking of the applicable areas of the fuselage skin of the doublers, triplers, and fillers of the preventive modification, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757-53- 0097, Revision 2, dated July 28, 2015. Repeat the inspection thereafter at the applicable times specified in table 4 of paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 757-53-0097, Revision 2, dated July 28, 2015. (i) Repair If any cracking is found during any inspection required by paragraph (g)(1), (g)(2), (g)(3), or (h) of this AD, repair before further flight using a method approved in accordance with the procedures specified in paragraph (m) of this AD. Doing the repair ends the repetitive inspections for the repaired area only. (j) Optional Terminating Actions (1) Accomplishing the preventative modification, including doing high frequency EC inspections for cracking around existing fastener holes, in accordance with Part 3 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 757-53-0097, Revision 2, dated July 28, 2015, except [[Page 8160]] as required by paragraphs (k)(2) and (k)(3) of this AD, terminates the inspections required by paragraph (g)(1) of this AD, provided the preventative modification is done before further flight after accomplishing an inspection required by paragraph (g) of this AD. (2) Replacing the crown skin panel between STA 297 and STA 439, S-4L to S-4R, using a method approved in accordance with the procedures specified in paragraph (m) of this AD, terminates the inspections required by paragraphs (g)(1), (g)(2), and (g)(3) of this AD. (k) Exceptions to Service Information Specifications and Preventative Modification (1) Where Boeing Special Attention Service Bulletin 757-53-0097, Revision 2, dated July 28, 2015, specifies a compliance time ``after the Revision 2 date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Where Boeing Special Attention Service Bulletin 757-53-0097, Revision 2, dated July 28, 2015, specifies to contact Boeing for repair instructions: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (m) of this AD. (3) If any cracking is found during any inspection specified in paragraph (j)(1) of this AD, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (m) of this AD. (l) Credit for Previous Actions (1) This paragraph provides credit for Zone 1 inspections required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Boeing Special Attention Service Bulletin 757-53-0097, dated November 22, 2010, which was incorporated by reference in AD 2011-01-15, Amendment 39- 16572 (76 FR 1351, January 10, 2011). (2) This paragraph provides credit for the Zone 1 inspection required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD, using Boeing Special Attention Service Bulletin 757-53-0097, Revision 1, dated January 6, 2011, which is not incorporated by reference in this AD. (m) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (m)(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, Los Angeles ACO, to make those findings. For a repair method 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) AMOCs approved for AD 2011-01-15, Amendment 39-16572 (76 FR 1351, January 10, 2011), are not approved as AMOCs for the corresponding provisions of paragraph (g) of this AD. (5) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (m)(5)(i) and (m)(5)(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. (n) Related Information (1) For more information about this AD, contact Eric Schrieber, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5348; fax: 562-627-5210; email: [email protected] (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800-0019, Long Beach, CA 90846-0001; telephone: 206-544-5000, extension 2; fax: 206-766-5683; Internet https://www.myboeingfleet.com. 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. Issued in Renton, Washington, on February 8, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-03297 Filed 2-17-16; 8:45 am] BILLING CODE 4910-13-P
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(2) Contacting the Manufacturer: For any Notice of proposed rulemaking
ACTION: Directorate, 1601 Lind Avenue SW.,
requirement in this AD to obtain corrective (NPRM). Renton, WA. For information on the
actions from a manufacturer, the action must availability of this material at the FAA,
be accomplished using a method approved SUMMARY: We propose to supersede call 425–227–1221. It is also available
by the Manager, International Branch, ANM– Airworthiness Directive (AD) 2011–01–
116, Transport Airplane Directorate, FAA; or
on the Internet at http://
15, which applies to certain The Boeing www.regulations.gov by searching for
the European Aviation Safety Agency Company Model 757–200, –200CB, and
(EASA); or Airbus’s EASA Design and locating Docket No. FAA–2016–
–300 series airplanes. AD 2011–01–15 3697.
Organization Approval (DOA). If approved by
the DOA, the approval must include the
currently requires repetitive inspections
for cracking of the fuselage skin of the Examining the AD Docket
DOA-authorized signature.
(3) Required for Compliance (RC): Except crown skin panel along the chem-milled You may examine the AD docket on
as required by paragraph (h) of this AD: If step at stringers S–4L (left) and S–4R the Internet at http://
any service information contains procedures (right), from stations (STA) 297 through www.regulations.gov by searching for
or tests that are identified as RC, those STA 439, and repair, if necessary. AD and locating Docket No. FAA–2016–
procedures and tests must be done to comply 2011–01–15 also includes terminating 3697; or in person at the Docket
with this AD; any procedures or tests that are action for the repetitive inspections of Management Facility between 9 a.m.
not identified as RC are recommended. Those the repaired areas only. Since we issued
procedures and tests that are not identified
and 5 p.m., Monday through Friday,
AD 2011–01–15, we received reports of except Federal holidays. The AD docket
as RC may be deviated from using accepted
methods in accordance with the operator’s
the initiation of new fatigue cracking in contains this proposed AD, the
maintenance or inspection program without the fuselage skin of the crown skin regulatory evaluation, any comments
obtaining approval of an AMOC, provided panel along locally thinned channels received, and other information. The
the procedures and tests identified as RC can adjacent to the chem-milled steps. This street address for the Docket Office
be done and the airplane can be put back in proposed AD would add repetitive (phone: 800–647–5527) is in the
an airworthy condition. Any substitutions or inspections for cracking in additional ADDRESSES section. Comments will be
changes to procedures or tests identified as areas and repair if necessary. This available in the AD docket shortly after
RC require approval of an AMOC. proposed AD would also remove receipt.
(j) Related Information airplanes from the applicability in AD FOR FURTHER INFORMATION CONTACT: Eric
(1) Refer to Mandatory Continuing
2011–01–15. This proposed AD would Schrieber, Aerospace Engineer,
Airworthiness Information (MCAI) EASA AD also add an optional skin panel Airframe Branch, ANM–120L, FAA, Los
2014–0202R1, dated September 19, 2014, for replacement which would terminate all Angeles Aircraft Certification Office
related information. This MCAI may be inspections and an optional (ACO), 3960 Paramount Boulevard,
found in the AD docket on the Internet at preventative modification that would Lakewood, CA 90712–4137; phone:
http://www.regulations.gov by searching for terminate certain inspections. We are 562–627–5348; fax: 562–627–5210;
and locating Docket No. FAA–2016–0466. proposing this AD to detect and correct email: eric.schrieber@faa.gov.
(2) For service information identified in fatigue cracking of the fuselage skin of
this AD, contact Airbus SAS, Airworthiness SUPPLEMENTARY INFORMATION:
the crown skin panel, which could
Office—EAW, 1 Rond Point Maurice Comments Invited
Bellonte, 31707 Blagnac Cedex, France;
result in pressure venting and
telephone +33 5 61 93 36 96; fax +33 5 61 consequent rapid decompression of the We invite you to send any written
93 44 51; email account.airworth-eas@ airplane. relevant data, views, or arguments about
airbus.com; Internet http://www.airbus.com. DATES: We must receive comments on this proposed AD. Send your comments
You may view this service information at the this proposed AD by April 4, 2016. to an address listed under the
FAA, Transport Airplane Directorate, 1601 ADDRESSES: You may send comments, ADDRESSES section. Include ‘‘Docket No.
Lind Avenue SW., Renton, WA. For using the procedures found in 14 CFR FAA–2016–3697; Directorate Identifier
information on the availability of this 2015–NM–143–AD’’ at the beginning of
material at the FAA, call 425–227–1221.
11.43 and 11.45, by any of the following
methods: your comments. We specifically invite
Issued in Renton, Washington, on February • Federal eRulemaking Portal: Go to comments on the overall regulatory,
6, 2016. http://www.regulations.gov. Follow the economic, environmental, and energy
Michael Kaszycki, instructions for submitting comments. aspects of this proposed AD. We will
Acting Manager, Transport Airplane • Fax: 202–493–2251. consider all comments received by the
Directorate, Aircraft Certification Service. • Mail: U.S. Department of closing date and may amend this
[FR Doc. 2016–03135 Filed 2–17–16; 8:45 am] Transportation, Docket Operations, M– proposed AD because of those
BILLING CODE 4910–13–P 30, West Building Ground Floor, Room comments.
W12–140, 1200 New Jersey Avenue SE., We will post all comments we
Washington, DC 20590. receive, without change, to http://
DEPARTMENT OF TRANSPORTATION • Hand Delivery: Deliver to Mail www.regulations.gov, including any
address above between 9 a.m. and 5 personal information you provide. We
Federal Aviation Administration p.m., Monday through Friday, except will also post a report summarizing each
Federal holidays. substantive verbal contact we receive
14 CFR Part 39 For service information identified in about this proposed AD.
this NPRM, contact Boeing Commercial
[Docket No. FAA–2016–3697; Directorate Airplanes, Attention: Data & Services Discussion
wgreen on DSK2VPTVN1PROD with PROPOSALS
Identifier 2015–NM–143–AD] Management, 3855 Lakewood On December 28, 2010, we issued AD
Boulevard, MC D800–0019, Long Beach, 2011–01–15, Amendment 39–16572 (76
RIN 2120–AA64 CA 90846–0001; telephone: 206–544– FR 1351, January 10, 2011), for certain
Airworthiness Directives; The Boeing 5000, extension 2; fax: 206–766–5683; The Boeing Company Model 757–200,
Company Airplanes Internet https:// –200CB, and –300 series airplanes. AD
www.myboeingfleet.com. You may view 2011–01–15 requires repetitive
AGENCY:Federal Aviation this referenced service information at inspections for cracking of the fuselage
Administration (FAA), DOT. the FAA, Transport Airplane skin of the crown skin panel along the
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chem-milled step at stringers S–4L and allowed as an option in AD 2011–01–15, the service information described
S–4R, from stations (STA) 297 through Amendment 39–16572 (76 FR 1351, previously. For information on the
STA 439, and repair if necessary. AD January 12, 2011), does not adequately procedures and compliance times, see
2011–01–15 also includes terminating address the identified unsafe condition. this service information at http://
action for the repetitive inspections of Only eddy current inspections are www.regulations.gov by searching for
the repaired areas only. AD 2011–01–15 adequate to address the identified and locating Docket No. FAA–2016–
resulted from reports of cracking in the unsafe condition. 3697.
fuselage skin of the crown skin panel.
Related Service Information Under 1 Explanation of ‘‘RC’’ Steps in Service
We issued AD 2011–01–15 to detect and
CFR Part 51 Information
correct fatigue cracking of the fuselage
skin of the crown skin panel, which We reviewed Boeing Special
Attention Service Bulletin 757–53– The FAA worked in conjunction with
could result in pressure venting and
consequent rapid decompression of the 0097, Revision 2, dated July 28, 2015. industry, under the Airworthiness
airplane. The service information describes Directive Implementation Aviation
procedures for repetitive external Rulemaking Committee (ARC), to
Actions Since AD 2011–01–15, sliding probe eddy current (EC) and enhance the AD system. One
Amendment 39–16572 (76 FR 1351, external spot-probe-medium-frequency enhancement was a new process for
January 10, 2011), Was Issued EC inspections for cracking of the crown annotating which steps in the service
The preamble to AD 2011–01–15, skin panel, repair, a preventive information are required for compliance
Amendment 39–16572 (76 FR 1351, modification, and replacement of the with an AD. Differentiating these steps
January 10, 2011), specifies that we crown skin panel. This service from other tasks in the service
consider the requirements ‘‘interim information is reasonably available information is expected to improve an
action.’’ AD 2011–01–15 explains that because the interested parties have owner’s/operator’s understanding of
we might consider further rulemaking if access to it through their normal course crucial AD requirements and help
final action is later identified. We now of business or by the means identified provide consistent judgment in AD
have determined that it is necessary to in the ADDRESSES section. compliance. The steps identified as RC
initiate further rulemaking to add (required for compliance) in any service
repetitive inspections for cracking in FAA’s Determination information identified previously have a
additional areas for certain airplanes, We are proposing this AD because we direct effect on detecting, preventing,
and repair if necessary. evaluated all the relevant information resolving, or eliminating an identified
We have removed Model 757–200 CB and determined the unsafe condition unsafe condition.
series airplanes from the applicability described previously is likely to exist or
because the crown skins on those develop in other products of the same Costs of Compliance
airplanes are manufactured differently type design.
and therefore are not affected by the We estimate that this proposed AD
identified unsafe condition. Proposed AD Requirements affects 652 airplanes of U.S. registry.
We have also determined that the This proposed AD would require We estimate the following costs to
external detailed inspection that is accomplishing the actions specified in comply with this proposed AD:
ESTIMATED COSTS
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
Inspections (Zone 1) [Retained actions 2 work-hour × $85 per hour = $170 $0 .......................... $170 per inspec- $110,840 per in-
from AD 2011–01–15, Amendment per inspection cycle. tion cycle. spection cycle.
39-16572 (76 FR 1351, January 10,
2011)].
Inspections (Zones 2 and 3) [new pro- Up to 4 work-hours × $85 per hour = $0 .......................... Up to $340 per in- $221,680 per in-
posed action]. Up to $340 per inspection cycle. spection cycle. spection cycle.
Optional modification ............................ Up to 615 work-hours × $85 per hour Up to $26,496 ....... Up to $78,771 ....... Up to $51,358,692.
= Up to $52,275.
We have received no definitive data detail the scope of the Agency’s products identified in this rulemaking
that would enable us to provide a cost authority. action.
estimate for the on-condition actions We are issuing this rulemaking under Regulatory Findings
specified in this proposed AD. the authority described in Subtitle VII,
We have received no definitive data We have determined that this
Part A, Subpart III, Section 44701,
that would enable us to provide a cost proposed AD would not have federalism
‘‘General requirements.’’ Under that
estimate for the optional replacement implications under Executive Order
section, Congress charges the FAA with 13132. This proposed AD would not
specified in this proposed AD.
promoting safe flight of civil aircraft in
wgreen on DSK2VPTVN1PROD with PROPOSALS
have a substantial direct effect on the
Authority for This Rulemaking air commerce by prescribing regulations States, on the relationship between the
Title 49 of the United States Code for practices, methods, and procedures national Government and the States, or
specifies the FAA’s authority to issue the Administrator finds necessary for on the distribution of power and
rules on aviation safety. Subtitle I, safety in air commerce. This regulation responsibilities among the various
Section 106, describes the authority of is within the scope of that authority levels of government.
the FAA Administrator. Subtitle VII, because it addresses an unsafe condition For the reasons discussed above, I
Aviation Programs, describes in more that is likely to exist or develop on certify that the proposed regulation:
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![Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Proposed Rules 8159
(1) Is not a ‘‘significant regulatory (f) Compliance installed that covers the Zone 1 inspection
action’’ under Executive Order 12866, Comply with this AD within the area specified in Boeing Special Attention
(2) Is not a ‘‘significant rule’’ under compliance times specified, unless already Service Bulletin 757–53–0097, Revision 2,
the DOT Regulatory Policies and done. dated July 28, 2015; or any preventive
modification is installed as specified in Part
Procedures (44 FR 11034, February 26, (g) Repetitive Inspections 3 of the Accomplishment Instructions of
1979), Boeing Special Attention Service Bulletin
(3) Will not affect intrastate aviation Do the applicable inspections required by
paragraphs (g)(1), (g)(2), and (g)(3) of this AD. 757–53–0097, Revision 2, dated July 28,
in Alaska, and (1) For all airplanes: At the applicable time 2015: At the applicable time specified in
(4) Will not have a significant specified in table 1 of paragraph 1.E., table 3 of paragraph 1.E., ‘‘Compliance,’’ of
economic impact, positive or negative, ‘‘Compliance,’’ of Boeing Special Attention Boeing Special Attention Service Bulletin
on a substantial number of small entities Service Bulletin 757–53–0097, Revision 2, 757–53–0097, Revision 2, dated July 28,
under the criteria of the Regulatory dated July 28, 2015: Do the inspection 2015, except as required by paragraph (k)(1)
Flexibility Act. specified in paragraph (g)(1)(i) or (g)(1)(ii) of of this AD: Do the inspection specified in
this AD in accordance with the paragraph (g)(3)(i) or (g)(3)(ii) of this AD, in
List of Subjects in 14 CFR Part 39 Accomplishment Instructions of Boeing accordance with the Accomplishment
Special Attention Service Bulletin 757–53– Instructions of Boeing Special Attention
Air transportation, Aircraft, Aviation Service Bulletin 757–53–0097, Revision 2,
safety, Incorporation by reference, 0097, Revision 2, dated July 28, 2015. Repeat
the inspection thereafter at the applicable dated July 28, 2015. Repeat the inspection
Safety. times specified in table 1 of paragraph 1.E., thereafter at the applicable times specified in
‘‘Compliance,’’ of Boeing Special Attention table 3 of paragraph 1.E., ‘‘Compliance,’’ of
The Proposed Amendment Boeing Special Attention Service Bulletin
Service Bulletin 757–53–0097, Revision 2,
Accordingly, under the authority dated July 28, 2015. Accomplishing the 757–53–0097, Revision 2, dated July 28,
delegated to me by the Administrator, preventative modification specified in 2015. Accomplishing the replacement
the FAA proposes to amend 14 CFR part paragraph (j)(1) of this AD or the replacement specified in paragraph (j)(2) of this AD
39 as follows: specified in paragraph (j)(2) of this AD terminates the inspections required by this
terminates the inspections required by this paragraph.
PART 39—AIRWORTHINESS paragraph. (i) Do an external sliding probe EC
(i) Do an external sliding probe eddy inspection for cracking of the crown skin
DIRECTIVES panel at stringers S–3L and S–3R.
current (EC) inspection for cracking of the
■ 1. The authority citation for part 39 crown skin panel at stringers S–4L (left) and (ii) Do an external spot-probe-medium-
S–4R (right). frequency EC inspection for cracking of the
continues to read as follows: crown skin panel at stringers S–3L and S–3R.
(ii) Do an external spot-probe-medium-
Authority: 49 U.S.C. 106(g), 40113, 44701. frequency EC inspection for cracking of the (h) Post-Preventive Modification
crown skin panel at stringers S–4L and S–4R. Supplemental Inspections
§ 39.13 [Amended]
(2) For airplanes on which any crack is
■ 2. The FAA amends § 39.13 by found during any inspection required by For airplanes on which a preventive
removing Airworthiness Directive (AD) paragraph (g)(1) of this AD; or any repair is modification has been installed as specified
2011–01–15, Amendment 39–16572 (76 installed that covers the Zone 1 inspection in Part 3 of the Accomplishment Instructions
area specified in Boeing Special Attention of Boeing Special Attention Service Bulletin
FR 1351, January 10, 2011), and adding 757–53–0097, Revision 2, dated July 28,
the following new AD: Service Bulletin 757–53–0097, Revision 2,
dated July 28, 2015; or any preventive 2015: At the applicable time specified in
The Boeing Company: Docket No. FAA– modification is installed as specified in Part table 4 of paragraph 1.E., ‘‘Compliance,’’ of
2016–3697; Directorate Identifier 2015– Boeing Special Attention Service Bulletin
3 of the Accomplishment Instructions of
NM–143–AD. 757–53–0097, Revision 2, dated July 28,
Boeing Special Attention Service Bulletin
2015; do eddy current and detailed
(a) Comments Due Date 757–53–0097, Revision 2, dated July 28,
inspections for cracking of the applicable
2015: At the applicable time specified in
The FAA must receive comments on this areas of the fuselage skin of the doublers,
table 2 of paragraph 1.E., ‘‘Compliance,’’ of
AD action by April 4, 2016. triplers, and fillers of the preventive
Boeing Special Attention Service Bulletin
modification, in accordance with the
(b) Affected ADs 757–53–0097, Revision 2, dated July 28,
Accomplishment Instructions of Boeing
This AD replaces AD 2011–01–15, 2015, except as required by paragraph (k)(1)
Special Attention Service Bulletin 757–53–
Amendment 39–16572 (76 FR 1351, January of this AD: Do the inspection specified in
0097, Revision 2, dated July 28, 2015. Repeat
10, 2011). paragraph (g)(2)(i) or (g)(2)(ii) of this AD, in the inspection thereafter at the applicable
accordance with the Accomplishment times specified in table 4 of paragraph 1.E.,
(c) Applicability Instructions of Boeing Special Attention ‘‘Compliance,’’ of Boeing Special Attention
(c) This AD applies to The Boeing Service Bulletin 757–53–0097, Revision 2, Service Bulletin 757–53–0097, Revision 2,
Company Model 757–200 and –300 series dated July 28, 2015. Repeat the inspection dated July 28, 2015.
airplanes, certificated in any category, as thereafter at the applicable times specified in
identified in Boeing Special Attention table 2 of paragraph 1.E., ‘‘Compliance,’’ of (i) Repair
Service Bulletin 757–53–0097, Revision 2, Boeing Special Attention Service Bulletin If any cracking is found during any
dated July 28, 2015. 757–53–0097, Revision 2, dated July 28, inspection required by paragraph (g)(1),
2015. Accomplishing the replacement (g)(2), (g)(3), or (h) of this AD, repair before
(d) Subject specified in paragraph (j)(2) of this AD further flight using a method approved in
Air Transport Association (ATA) of terminates the inspections required by this accordance with the procedures specified in
America Code 53, Fuselage. paragraph. paragraph (m) of this AD. Doing the repair
(i) Do an external sliding probe EC ends the repetitive inspections for the
(e) Unsafe Condition inspection for cracking of the crown skin repaired area only.
wgreen on DSK2VPTVN1PROD with PROPOSALS
This AD was prompted by reports of the panel at stringers S–2L, S–3L, and S–3R, as
initiation of fatigue cracking in the fuselage applicable. (j) Optional Terminating Actions
skin of the crown skin panel along locally (ii) Do an external spot-probe-medium- (1) Accomplishing the preventative
thinned channels adjacent to the chem- frequency EC inspection for cracking of the modification, including doing high frequency
milled steps. We are issuing this AD to detect crown skin panel at stringers S–2L, S–3L, EC inspections for cracking around existing
and correct fatigue cracking of the fuselage and S–3R, as applicable. fastener holes, in accordance with Part 3 of
skin of the crown skin panel, which could (3) For airplanes on which any crack is the Accomplishment Instructions of Boeing
result in pressure venting and consequent found during any inspection required by Special Attention Service Bulletin 757–53–
rapid decompression of the airplane. paragraph (g)(1) of this AD; or any repair is 0097, Revision 2, dated July 28, 2015, except
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![8160 Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Proposed Rules
as required by paragraphs (k)(2) and (k)(3) of (3) An AMOC that provides an acceptable DEPARTMENT OF TRANSPORTATION
this AD, terminates the inspections required level of safety may be used for any repair.
by paragraph (g)(1) of this AD, provided the modification, or alteration required by this Federal Aviation Administration
preventative modification is done before AD if it is approved by the Boeing
further flight after accomplishing an Commercial Airplanes Organization
inspection required by paragraph (g) of this
14 CFR Part 39
Designation Authorization (ODA) that has
AD. [Docket No. FAA–2016–0465; Directorate
(2) Replacing the crown skin panel been authorized by the Manager, Los Angeles
Identifier 2015–NM–096–AD]
between STA 297 and STA 439, S–4L to S– ACO, to make those findings. For a repair
4R, using a method approved in accordance method to be approved the repair method, RIN 2120–AA64
with the procedures specified in paragraph modification deviation, or alteration
(m) of this AD, terminates the inspections deviation must meet the certification basis of Airworthiness Directives; Airbus
required by paragraphs (g)(1), (g)(2), and the airplane and the approval must Airplanes
(g)(3) of this AD. specifically refer to this AD.
AGENCY: Federal Aviation
(k) Exceptions to Service Information (4) AMOCs approved for AD 2011–01–15,
Administration (FAA), DOT.
Specifications and Preventative Modification Amendment 39–16572 (76 FR 1351, January
10, 2011), are not approved as AMOCs for the ACTION: Notice of proposed rulemaking
(1) Where Boeing Special Attention Service (NPRM).
Bulletin 757–53–0097, Revision 2, dated July corresponding provisions of paragraph (g) of
28, 2015, specifies a compliance time ‘‘after this AD.
SUMMARY: We propose to adopt a new
the Revision 2 date of this service bulletin,’’ (5) For service information that contains
airworthiness directive (AD) for certain
this AD requires compliance within the steps that are labeled as Required for
specified compliance time after the effective Airbus Model A330–200 and –300 series
Compliance (RC), the provisions of
date of this AD. airplanes; and Model A340–200 and
paragraphs (m)(5)(i) and (m)(5)(ii) apply.
(2) Where Boeing Special Attention Service –300 series airplanes. This proposed AD
(i) The steps labeled as RC, including
Bulletin 757–53–0097, Revision 2, dated July was prompted by a determination that
substeps under an RC step and any figures
28, 2015, specifies to contact Boeing for the compliance times for certain post-
repair instructions: Before further flight, identified in an RC step, must be done to
comply with the AD. An AMOC is required
repair inspections and certain allowable
repair using a method approved in damage limits (ADLs) must be reduced
accordance with the procedures specified in for any deviations to RC steps, including
substeps and identified figures. in order to address fatigue. This
paragraph (m) of this AD.
(3) If any cracking is found during any (ii) Steps not labeled as RC may be proposed AD would require identifying
inspection specified in paragraph (j)(1) of this deviated from using accepted methods in any repairs and ADLs used to assess or
AD, before further flight, repair using a accordance with the operator’s maintenance control any structural damage on certain
method approved in accordance with the or inspection program without obtaining structural areas, and corrective action if
procedures specified in paragraph (m) of this approval of an AMOC, provided the RC steps, necessary. We are proposing this AD to
AD. prevent fatigue damage on primary
including substeps and identified figures, can
(l) Credit for Previous Actions still be done as specified, and the airplane structure and structural repairs, which
(1) This paragraph provides credit for Zone can be put back in an airworthy condition. could result in reduced structural
1 inspections required by paragraph (g) of integrity of the airplane.
(n) Related Information
this AD, if those actions were performed DATES: We must receive comments on
before the effective date of this AD using (1) For more information about this AD, this proposed AD by April 4, 2016.
Boeing Special Attention Service Bulletin contact Eric Schrieber, Aerospace Engineer, ADDRESSES: You may send comments,
757–53–0097, dated November 22, 2010, Airframe Branch, ANM–120L, FAA, Los
which was incorporated by reference in AD using the procedures found in 14 CFR
Angeles Aircraft Certification Office (ACO),
2011–01–15, Amendment 39–16572 (76 FR 11.43 and 11.45, by any of the following
3960 Paramount Boulevard, Lakewood, CA
1351, January 10, 2011). methods:
90712–4137; phone: 562–627–5348; fax: 562–
(2) This paragraph provides credit for the • Federal eRulemaking Portal: Go to
627–5210; email: Eric.Schrieber@faa.gov.
Zone 1 inspection required by paragraph (g) http://www.regulations.gov. Follow the
of this AD, if those actions were performed (2) For service information identified in
instructions for submitting comments.
this AD, contact Boeing Commercial
before the effective date of this AD, using • Fax: 202–493–2251.
Boeing Special Attention Service Bulletin Airplanes, Attention: Data & Services
• Mail: U.S. Department of
757–53–0097, Revision 1, dated January 6, Management, 3855 Lakewood Boulevard, MC
2011, which is not incorporated by reference
Transportation, Docket Operations, M–
D800–0019, Long Beach, CA 90846–0001;
in this AD. 30, West Building Ground Floor, Room
telephone: 206–544–5000, extension 2; fax:
206–766–5683; Internet https://
W12–140, 1200 New Jersey Avenue SE.,
(m) Alternative Methods of Compliance Washington, DC 20590.
(AMOCs) www.myboeingfleet.com. You may view this
referenced service information at the FAA,
• Hand Delivery: U.S. Department of
(1) The Manager, Los Angeles Aircraft Transportation, Docket Operations, M–
Certification Office (ACO), FAA, has the Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information 30, West Building Ground Floor, Room
authority to approve AMOCs for this AD, if W12–140, 1200 New Jersey Avenue SE.,
requested using the procedures found in 14 on the availability of this material at the
CFR 39.19. In accordance with 14 CFR 39.19, FAA, call 425–227–1221. Washington, DC, between 9 a.m. and 5
send your request to your principal inspector p.m., Monday through Friday, except
Issued in Renton, Washington, on February Federal holidays.
or local Flight Standards District Office, as
appropriate. If sending information directly 8, 2016. For service information identified in
to the manager of the ACO, send it to the Michael Kaszycki, this NPRM, contact Airbus SAS,
wgreen on DSK2VPTVN1PROD with PROPOSALS
attention of the person identified in Acting Manager, Transport Airplane Airworthiness Office—EAL, 1 Rond
paragraph (m)(1) of this AD. Information may Directorate, Aircraft Certification Service. Point Maurice Bellonte, 31707 Blagnac
be emailed to: 9-ANM-LAACO-AMOC- Cedex, France; telephone: +33 5 61 93
[FR Doc. 2016–03297 Filed 2–17–16; 8:45 am]
Requests@faa.gov.
(2) Before using any approved AMOC, BILLING CODE 4910–13–P
36 96; fax: +33 5 61 93 45 80; email:
notify your appropriate principal inspector, airworthiness.A330-A340@airbus.com;
or lacking a principal inspector, the manager Internet: http://www.airbus.com. You
of the local flight standards district office/ may view this referenced service
certificate holding district office. information at the FAA, Transport
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Document Created: 2016-02-18 07:46:20
Document Modified: 2016-02-18 07:46:20
| 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 April 4, 2016. | |
| Contact | Eric Schrieber, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5348; fax: 562-627-5210; email: [email protected] | |
| FR Citation | 81 FR 8157 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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