81 FR 17415 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 60 (March 29, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 60 (March 29, 2016)
| Page Range | 17415-17417 | |
| FR Document | 2016-07023 |
[Federal Register Volume 81, Number 60 (Tuesday, March 29, 2016)] [Proposed Rules] [Pages 17415-17417] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-07023] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-5034; Directorate Identifier 2015-NM-172-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 all The Boeing Company Model 737-600, -700, -700C, -800, -900, and 900ER series airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that the S-14L and S-14R lap splices are subject to widespread fatigue damage (WFD). This proposed AD would require repetitive low frequency eddy current inspections for cracking in the lower fastener row of the S-14L and S-14R lap splices and repair if necessary. We are proposing this AD to detect and correct widespread cracking in the S-14L and S-14R lap splices that could rapidly link up and result in possible rapid decompression and reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by May 13, 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-2016-5034. 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- 5034; 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: Jason Deutschman, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6595; 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-2016-5034; Directorate Identifier 2015-NM-172-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 Structural fatigue damage is progressive. It begins as minute cracks, and those cracks grow under the action of repeated stresses. This can happen because of normal operational conditions and design attributes, or because of isolated situations or incidents such as material defects, poor fabrication quality, or corrosion pits, dings, or scratches. Fatigue damage can occur locally, in small areas or structural design details, or globally. Global fatigue damage is general degradation of large areas of structure with similar structural details and stress levels. Multiple-site damage is global damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Global damage can also occur in multiple elements such as adjacent frames or stringers. Multiple- site- [[Page 17416]] damage and multiple-element-damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane, in a condition known as WFD. As an airplane ages, WFD will likely occur, and will certainly occur if the airplane is operated long enough without any intervention. The FAA's WFD final rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent structural failure due to WFD throughout the operational life of certain existing transport category airplanes and all of these airplanes that will be certificated in the future. For existing and future airplanes subject to the WFD rule, the rule requires that DAHs establish a limit of validity (LOV) of the engineering data that support the structural maintenance program. Operators affected by the WFD rule may not fly an airplane beyond its LOV, unless an extended LOV is approved. The WFD rule (75 FR 69746, November 15, 2010) does not require identifying and developing maintenance actions if the DAHs can show that such actions are not necessary to prevent WFD before the airplane reaches the LOV. Many LOVs, however, do depend on accomplishment of future maintenance actions. As stated in the WFD rule, any maintenance actions necessary to reach the LOV will be mandated by airworthiness directives through separate rulemaking actions. In the context of WFD, this action is necessary to enable DAHs to propose LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. This approach allows for an implementation strategy that provides flexibility to DAHs in determining the timing of service information development (with FAA approval), while providing operators with certainty regarding the LOV applicable to their airplanes. We received reports that the existing inspection program is not sufficient to preclude the occurrence of WFD in the S-14L and S-14R lap splices. This condition, if not corrected, could result in widespread cracking that could rapidly link up and result in possible rapid decompression and reduced structural integrity of the airplane. Relevant Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 737-53A1352, dated October 2, 2015. The service information describes procedures for low frequency eddy current inspections for cracking in the lower fastener row of the S-14L and S-14R lap splices and repair. 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 these same type designs. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ``Differences Between this Proposed AD and the Service Information.'' 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-2016-5034. Differences Between This Proposed AD and the Service Information Boeing Alert Service Bulletin 737-53A1352, dated October 2, 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 1,513 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 ---------------------------------------------------------------------------------------------------------------- Inspection for Group 1 airplanes 84 work-hours x $85 $0 $7,140 per $10,502,940 per (1,471 airplanes). per hour = $7,140 inspection cycle. inspection cycle. per inspection cycle. Inspection for Group 2 airplanes 65 work-hours x $85 $0 $5,525 per $232,050 per (42 airplanes). per hour = $5,525 inspection cycle. inspection cycle. per inspection cycle. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this 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 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. [[Page 17417]] 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-2016-5034; Directorate Identifier 2015-NM-172-AD. (a) Comments Due Date We must receive comments by May 13, 2016. (b) Affected ADs None. (c) Applicability This AD applies to all The Boeing Company Model 737-600, -700, - 700C, -800, -900, and -900ER series airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the S-14L and S-14R lap splices are subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct widespread cracking in the S-14L and S-14R lap splices that could rapidly link up and result in possible rapid decompression and reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections At the applicable compliance time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1352, dated October 2, 2015, do a low frequency eddy current inspection for cracking of the lower fastener row of S-14L and S-14R lap splices, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1352, dated October 2, 2015. Repeat the inspection thereafter at the applicable times specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1352, dated October 2, 2015. If any cracking is found, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (h) of this AD. (h) 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 (i)(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) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (h)(4)(i) and (h)(4)(ii) of this AD 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. (i) Related Information (1) For more information about this AD, contact Jason Deutschman, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6595; fax: 425-917-6590; email: [email protected]. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544- 5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. 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 March 20, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-07023 Filed 3-28-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 60 / Tuesday, March 29, 2016 / Proposed Rules 17415
(1) The ‘‘fuel control drive’’ is a series of Notice of proposed rulemaking
ACTION: Management Facility between 9 a.m.
mating splines located between the fuel (NPRM). and 5 p.m., Monday through Friday,
pump and fuel control governor. except Federal holidays. The AD docket
(2) The fuel control drive consists of four SUMMARY: We propose to adopt a new contains this proposed AD, the
drive splines: The fuel pump internal spline, airworthiness directive (AD) for all The
the fuel control external ‘‘quill shaft’’ spline,
regulatory evaluation, any comments
Boeing Company Model 737–600, –700, received, and other information. The
and the stub shaft internal and external
–700C, –800, –900, and 900ER series street address for the Docket Office
splines.
airplanes. This proposed AD was (phone: 800–647–5527) is in the
(h) Alternative Methods of Compliance prompted by an evaluation by the ADDRESSES section. Comments will be
(AMOCs) design approval holder (DAH) available in the AD docket shortly after
The Manager, Los Angeles Aircraft indicating that the S–14L and S–14R lap receipt.
Certification Office, FAA, may approve splices are subject to widespread fatigue
AMOCs for this AD. Use the procedures FOR FURTHER INFORMATION CONTACT:
damage (WFD). This proposed AD
found in 14 CFR 39.19 to make your request. Jason Deutschman, Aerospace Engineer,
would require repetitive low frequency
Airframe Branch, ANM–120S, FAA,
(i) Related Information eddy current inspections for cracking in
Seattle Aircraft Certification Office
(1) For more information about this AD, the lower fastener row of the S–14L and
(ACO), 1601 Lind Avenue SW., Renton,
contact Joseph Costa, Aerospace Engineer, S–14R lap splices and repair if
WA 98057–3356; phone: 425–917–6595;
Los Angeles Aircraft Certification Office, necessary. We are proposing this AD to
fax: 425–917–6590; email:
FAA, Transport Airplane Directorate, 3960 detect and correct widespread cracking
Paramount Blvd., Lakewood, CA 90712–
Jason.deutschman@faa.gov.
in the S–14L and S–14R lap splices that
4137; phone: 562–627–5246; fax: 562–627– could rapidly link up and result in SUPPLEMENTARY INFORMATION:
5210; email: joseph.costa@faa.gov. possible rapid decompression and
(2) Information pertaining to operating Comments Invited
reduced structural integrity of the
recommendations for affected engines after a We invite you to send any written
fuel control drive failure is contained in airplane.
relevant data, views, or arguments about
Honeywell Operating Information Letter DATES: We must receive comments on this proposal. Send your comments to
(OIL) OI331–12R6, dated May 26, 2009, for this proposed AD by May 13, 2016. an address listed under the ADDRESSES
multi-engine airplanes; and OIL OI331–18R4,
ADDRESSES: You may send comments, section. Include ‘‘Docket No. FAA–
dated May 26, 2009, for single-engine
airplanes. Information on fuel control drive using the procedures found in 14 CFR 2016–5034; Directorate Identifier 2015–
inspection can be found in Section 72–00–00 11.43 and 11.45, by any of the following NM–172–AD’’ at the beginning of your
of the applicable TPE331 maintenance methods: comments. We specifically invite
manuals. These Honeywell OILs and the • Federal eRulemaking Portal: Go to comments on the overall regulatory,
TPE331 maintenance manuals can be http://www.regulations.gov. Follow the economic, environmental, and energy
obtained from Honeywell using the contact instructions for submitting comments. aspects of this proposed AD. We will
information in paragraph (i)(3) of this • Fax: 202–493–2251. consider all comments received by the
proposed AD. • Mail: U.S. Department of closing date and may amend this
(3) For service information identified in
this AD, contact Honeywell International
Transportation, Docket Operations, M– proposed AD because of those
Inc., 111 S. 34th Street, Phoenix, AZ 85034– 30, West Building Ground Floor, Room comments.
2802; phone: 800–601–3099; Internet: W12–140, 1200 New Jersey Avenue SE., We will post all comments we
https://myaerospace.honeywell.com/wps/ Washington, DC 20590. receive, without change, to http://
portal. • Hand Delivery: Deliver to Mail www.regulations.gov, including any
(4) You may view this service information address above between 9 a.m. and 5 personal information you provide. We
at the FAA, Engine & Propeller Directorate, p.m., Monday through Friday, except will also post a report summarizing each
1200 District Avenue, Burlington, MA. For Federal holidays. substantive verbal contact we receive
information on the availability of this For service information identified in about this proposed AD.
material at the FAA, call 781–238–7125.
this NPRM, contact Boeing Commercial
Issued in Burlington, Massachusetts, on Discussion
Airplanes, Attention: Data & Services
March 15, 2016. Management, P.O. Box 3707, MC 2H–65, Structural fatigue damage is
Ann C. Mollica, Seattle, WA 98124–2207; telephone progressive. It begins as minute cracks,
Acting Manager, Engine and Propeller 206–544–5000, extension 1; fax 206– and those cracks grow under the action
Directorate, Aircraft Certification Service. 766–5680; Internet https:// of repeated stresses. This can happen
[FR Doc. 2016–06936 Filed 3–28–16; 8:45 am] www.myboeingfleet.com. You may view because of normal operational
BILLING CODE 4910–13–P this referenced service information at conditions and design attributes, or
the FAA, Transport Airplane because of isolated situations or
Directorate, 1601 Lind Avenue SW., incidents such as material defects, poor
DEPARTMENT OF TRANSPORTATION Renton, WA. For information on the fabrication quality, or corrosion pits,
availability of this material at the FAA, dings, or scratches. Fatigue damage can
Federal Aviation Administration call 425–227–1221. It is also available occur locally, in small areas or
on the Internet at http:// structural design details, or globally.
14 CFR Part 39 www.regulations.gov by searching for Global fatigue damage is general
degradation of large areas of structure
mstockstill on DSK4VPTVN1PROD with PROPOSALS
[Docket No. FAA–2016–5034; Directorate and locating Docket No. FAA–2016–
Identifier 2015–NM–172–AD] 5034. with similar structural details and stress
levels. Multiple-site damage is global
RIN 2120–AA64 Examining the AD Docket damage that occurs in a large structural
Airworthiness Directives; The Boeing You may examine the AD docket on element such as a single rivet line of a
Company Airplanes the Internet at http:// lap splice joining two large skin panels.
www.regulations.gov by searching for Global damage can also occur in
AGENCY:Federal Aviation and locating Docket No. FAA–2016– multiple elements such as adjacent
Administration (FAA), DOT. 5034; or in person at the Docket frames or stringers. Multiple-site-
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![Federal Register / Vol. 81, No. 60 / Tuesday, March 29, 2016 / Proposed Rules 17417
For the reasons discussed above, I (g) Repetitive Inspections Renton, WA 98057–3356; phone: 425–917–
certify this proposed regulation: At the applicable compliance time 6595; fax: 425–917–6590; email:
(1) Is not a ‘‘significant regulatory specified in paragraph 1.E., ‘‘Compliance,’’ of Jason.deutschman@faa.gov.
action’’ under Executive Order 12866, Boeing Alert Service Bulletin 737–53A1352, (2) For service information identified in
(2) Is not a ‘‘significant rule’’ under dated October 2, 2015, do a low frequency this AD, contact Boeing Commercial
eddy current inspection for cracking of the Airplanes, Attention: Data & Services
the DOT Regulatory Policies and
lower fastener row of S–14L and S–14R lap Management, P.O. Box 3707, MC 2H–65,
Procedures (44 FR 11034, February 26, Seattle, WA 98124–2207; telephone 206–
1979), splices, in accordance with the
Accomplishment Instructions of Boeing Alert 544–5000, extension 1; fax 206–766–5680;
(3) Will not affect intrastate aviation Internet https://www.myboeingfleet.com. You
Service Bulletin 737–53A1352, dated October
in Alaska, and 2, 2015. Repeat the inspection thereafter at may view this referenced service information
(4) Will not have a significant the applicable times specified in paragraph at the FAA, Transport Airplane Directorate,
economic impact, positive or negative, 1.E., ‘‘Compliance,’’ of Boeing Alert Service 1601 Lind Avenue SW., Renton, WA. For
on a substantial number of small entities Bulletin 737–53A1352, dated October 2, information on the availability of this
under the criteria of the Regulatory 2015. If any cracking is found, before further material at the FAA, call 425–227–1221.
Flexibility Act. flight, repair using a method approved in Issued in Renton Washington, on March
accordance with the procedures specified in 20, 2016.
List of Subjects in 14 CFR Part 39 paragraph (h) of this AD.
Michael Kaszycki,
Air transportation, Aircraft, Aviation (h) Alternative Methods of Compliance Acting Manager, Transport Airplane
safety, Incorporation by reference, (AMOCs) Directorate, Aircraft Certification Service.
Safety. (1) The Manager, Seattle Aircraft [FR Doc. 2016–07023 Filed 3–28–16; 8:45 am]
The Proposed Amendment Certification Office (ACO), FAA, has the BILLING CODE 4910–13–P
authority to approve AMOCs for this AD, if
Accordingly, under the authority requested using the procedures found in 14
delegated to me by the Administrator, CFR 39.19. In accordance with 14 CFR 39.19,
the FAA proposes to amend 14 CFR part send your request to your principal inspector
DEPARTMENT OF TRANSPORTATION
39 as follows: or local Flight Standards District Office, as
appropriate. If sending information directly Federal Aviation Administration
PART 39—AIRWORTHINESS to the manager of the ACO, send it to the
DIRECTIVES attention of the person identified in 14 CFR Part 39
paragraph (i)(1) of this AD. Information may
[Docket No. FAA–2016–5035; Directorate
■ 1. The authority citation for part 39 be emailed to: 9-ANM-Seattle-ACO-AMOC-
Identifier 2015–NM–042–AD]
continues to read as follows: Requests@faa.gov.
(2) Before using any approved AMOC, RIN 2120–AA64
Authority: 49 U.S.C. 106(g), 40113, 44701. notify your appropriate principal inspector,
§ 39.13 [Amended] or lacking a principal inspector, the manager Airworthiness Directives; Fokker
of the local flight standards district office/ Services B.V. Airplanes
■ 2. The FAA amends § 39.13 by adding certificate holding district office.
the following new airworthiness (3) An AMOC that provides an acceptable AGENCY: Federal Aviation
directive (AD): level of safety may be used for any repair, Administration (FAA), DOT.
The Boeing Company: Docket No. FAA– modification, or alteration required by this ACTION: Notice of proposed rulemaking
2016–5034; Directorate Identifier 2015– AD if it is approved by the Boeing
Commercial Airplanes Organization
(NPRM).
NM–172–AD.
Designation Authorization (ODA) that has
(a) Comments Due Date SUMMARY: We propose to adopt a new
been authorized by the Manager, Seattle
We must receive comments by May 13, ACO, to make those findings. To be airworthiness directive (AD) for all
2016. approved, the repair method, modification Fokker Services B.V. Model F.28 Mark
deviation, or alteration deviation must meet 0070 and Mark 0100 airplanes. This
(b) Affected ADs proposed AD was prompted by reports
the certification basis of the airplane, and the
None. approval must specifically refer to this AD. of cracking in a certain area of the
(c) Applicability (4) For service information that contains pressure bulkhead webplate and skin
steps that are labeled as Required for connection angle. This proposed AD
This AD applies to all The Boeing Compliance (RC), the provisions of
Company Model 737–600, –700, –700C, would require a one-time inspection of
paragraphs (h)(4)(i) and (h)(4)(ii) of this AD
–800, –900, and –900ER series airplanes, the affected pressure bulkhead webplate
apply.
certificated in any category. (i) The steps labeled as RC, including and skin connection angle, and
(d) Subject substeps under an RC step and any figures corrective actions if necessary. We are
identified in an RC step, must be done to proposing this AD to detect and correct
Air Transport Association (ATA) of cracking of the pressure bulkhead
America Code 53, Fuselage. comply with the AD. An AMOC is required
for any deviations to RC steps, including webplate and skin connection angle that
(e) Unsafe Condition substeps and identified figures. could lead to sudden inflight
This AD was prompted by an evaluation by (ii) Steps not labeled as RC may be decompression of the airplane resulting
the design approval holder (DAH) indicating deviated from using accepted methods in in injury to occupants.
that the S–14L and S–14R lap splices are accordance with the operator’s maintenance
or inspection program without obtaining DATES: We must receive comments on
subject to widespread fatigue damage (WFD).
approval of an AMOC, provided the RC steps, this proposed AD by May 13, 2016.
mstockstill on DSK4VPTVN1PROD with PROPOSALS
We are issuing this AD to detect and correct
widespread cracking in the S–14L and S–14R including substeps and identified figures, can ADDRESSES: You may send comments,
lap splices that could rapidly link up and still be done as specified, and the airplane using the procedures found in 14 CFR
result in possible rapid decompression and can be put back in an airworthy condition. 11.43 and 11.45, by any of the following
reduced structural integrity of the airplane. methods:
(i) Related Information
(f) Compliance (1) For more information about this AD, • Federal eRulemaking Portal: Go to
Comply with this AD within the contact Jason Deutschman, Aerospace http://www.regulations.gov. Follow the
compliance times specified, unless already Engineer, Airframe Branch, ANM–120S, instructions for submitting comments.
done. FAA, Seattle ACO, 1601 Lind Avenue SW., • Fax: 202–493–2251.
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Document Created: 2016-03-30 08:29:43
Document Modified: 2016-03-30 08:29:43
| 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 May 13, 2016. | |
| Contact | Jason Deutschman, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6595; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 81 FR 17415 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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