80 FR 74731 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 229 (November 30, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 229 (November 30, 2015)
| Page Range | 74731-74734 | |
| FR Document | 2015-30217 |
[Federal Register Volume 80, Number 229 (Monday, November 30, 2015)] [Proposed Rules] [Pages 74731-74734] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-30217] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-6538; Directorate Identifier 2015-NM-031-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 737-100, -200, -200C, -300, -400, and -500 series airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that the bulkhead is subject to widespread fatigue damage (WFD). This proposed AD would require repetitive inspections of the aft pressure bulkhead web for any cracking, incorrectly drilled fastener holes, and elongated fastener holes, and related investigative and corrective actions if necessary. We are proposing this AD to detect and correct fatigue cracking of the aft pressure bulkhead web at the ``Y''-chord, which could result in reduced structural integrity of the airplane and rapid decompression of the fuselage. DATES: We must receive comments on this proposed AD by January 14, 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 proposed 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-6538. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 6538; or in person at the Docket Management Facility between 9 a.m. [[Page 74732]] 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: Alan Pohl, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-917- 6450; 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-2015-6538; Directorate Identifier 2015-NM-031-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-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 widespread fatigue damage (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 have received an evaluation by the design approval holder (DAH) indicating that the aft pressure bulkhead is subject to WFD. Cracks have been reported in the aft pressure bulkhead web at the web-to- ``Y''-chord interface and have occurred in the aft row of fasteners connecting the aft pressure bulkhead web to the ``Y''-chord. This condition, if not corrected, could result in fatigue cracking of the aft pressure bulkhead web at the ``Y''-chord, which could result in reduced structural integrity of the airplane and rapid decompression of the fuselage. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015. This service information describes, among other actions, procedures for repetitive inspections of the aft pressure bulkhead web for any cracking, incorrectly drilled fastener holes, and elongated fastener holes; and related investigative and corrective actions. 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 of this AD. 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 discussed under ``Differences Between this Proposed AD and the Service Information.'' Refer to this service information for details on the procedures and compliance times. The phrase ``related investigative actions'' is used in this proposed AD. ``Related investigative actions'' are follow-on actions that (1) are related to the primary action, and (2) further investigate the nature of any condition found. Related investigative actions in an AD could include, for example, inspections. The phrase ``corrective actions'' is used in this proposed AD. ``Corrective actions'' correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Differences Between This Proposed AD and the Service Information AD 2012-18-13 R1, Amendment 39-17429 (78 FR 27020, May 9, 2013), refers to Boeing Alert Service Bulletin 737-53A1214, Revision 4, dated December 16, 2011, as an appropriate source of service information for doing certain actions required by that AD. Since AD 2012-18-13 R1 was issued, Boeing issued Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015, to address WFD by adding new inspections specified in tables 9, 10, and 11 of paragraph 1.E., [[Page 74733]] ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015. Boeing determined that the WFD-based inspections specified in tables 9, 10, and 11 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015, affect only Group 2 airplanes because Group 1 airplanes will reach their limit of validity before the compliance times specified in tables 9, 10, and 11 (Group 1 is for airplanes having line numbers 1 through 2565; Group 2 is for airplanes having line numbers 2566 through 3132). Therefore, although Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015, is effective for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes, this proposed AD applies to only certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes (i.e., Group 2 airplanes). This difference is due to the fact that this proposed AD only addresses the new WFD inspections specified in Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015. Accomplishing the actions required by paragraphs (g) and (h) of this proposed AD would terminate the inspections required by paragraphs (k) and (l) of AD 2012-18-13 R1, Amendment 39-17429 (78 FR 27020, May 9, 2013). The service bulletin 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 122 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Parts Cost on U.S. Action Labor cost cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspections of the web at the Up to 60 work-hours x $0 Up to $5,100 per Up to $622,200 ``Y''[dash]chord. $85 per hour = Up to inspection cycle. per inspection $5,100 per cycle. 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. 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-2015-6538; Directorate Identifier 2015-NM-031-AD. (a) Comments Due Date We must receive comments by January 14, 2016. (b) Affected ADs This AD affects AD 2012-18-13 R1, Amendment 39-17429 (78 FR 27020, May 9, 2013). (c) Applicability This AD applies to The Boeing Company Model 737-100, -200, - 200C, -300, -400, and -500 series airplanes, certificated in any category, identified as Group 2 in Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder indicating that the aft pressure bulkhead is subject to widespread fatigue damage. We are issuing this AD to detect and correct fatigue cracking of the aft pressure bulkhead web at the ``Y''-chord, which could result in reduced structural integrity of the airplane and rapid decompression of the fuselage. (f) Compliance Comply with this AD within the compliance times specified, unless already done. [[Page 74734]] (g) Repetitive Inspections of the Aft Pressure Bulkhead Web at the ``Y''-Chord Upper Bulkhead At the applicable time specified in tables 9 and 10 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015: Do detailed and low frequency eddy current (LFEC) inspections from the aft side of the aft pressure bulkhead web, or do detailed and high frequency eddy current (HFEC) inspections from the forward side of the aft pressure bulkhead web, for any cracking, incorrectly drilled fastener hole, and elongated fastener hole, and do all applicable related investigative and corrective actions, in accordance with Part I of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015, except as required by paragraph (i) of this AD. Do all related investigative and corrective actions before further flight. If any cracking, incorrectly drilled fastener hole, or elongated fastener hole is found, before further flight, repair the web using a method approved in accordance with the procedures specified in paragraph (l) of this AD. Thereafter, repeat the inspections at the applicable times specified in tables 9 and 10 of paragraph 1.E., ``Compliance'' of Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015. (h) Repetitive Inspections of the Aft Pressure Bulkhead Web at the ``Y''-Chord Below S-15 At the applicable time specified in table 11 of 1.E., ``Compliance'' of Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015: Do detailed and eddy current inspections of the web from the forward or aft side of the bulkhead for any cracking, incorrectly drilled fastener hole, and elongated fastener hole, and do all applicable corrective actions, in accordance with Part III of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015, except as required by paragraph (i) of this AD. Do all corrective actions before further flight. If any cracking, incorrectly drilled fastener hole, or elongated fastener hole is found, before further flight, repair the web using a method approved in accordance with the procedures specified in paragraph (l) of this AD. Thereafter, repeat the inspections at the applicable times specified in table 11 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015. (i) Exception to the Service Information Where Boeing Alert Service Bulletin 737-53A1214, Revision 5, dated January 30, 2015, specifies to contact Boeing for repair instructions: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (l) of this AD. (j) Terminating Action for Other Rulemaking Accomplishing the actions required by paragraphs (g) and (h) of this AD terminates the inspections required by paragraphs (k) and (l) of AD 2012-18-13 R1, Amendment 39-17429 (78 FR 27020, May 9, 2013). (k) Credit for Previous Actions This paragraph provides credit for the actions required by paragraphs (g) and (h) of this AD, if the actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 737-53A1214, Revision 4, dated December 16, 2011, which is not incorporated by reference in this AD. (l) 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 (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 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. For a repair method to be approved, the repair must meet the certification basis of airplane, and the approval must specifically refer to this AD. (m) Related Information (1) For more information about this AD, contact Alan Pohl, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone: 425-917-6450; 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 November 20, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-30217 Filed 11-27-15; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 80, No. 229 / Monday, November 30, 2015 / Proposed Rules 74731
a pylon and consequent reduced structural (2) Contacting the Manufacturer: For any Notice of proposed rulemaking
ACTION:
integrity of the airplane. requirement in this AD to obtain corrective (NPRM).
actions from a manufacturer, the action must
(f) Compliance be accomplished using a method approved SUMMARY: We propose to adopt a new
Comply with this AD within the by the Manager, International Branch, ANM– airworthiness directive (AD) for certain
compliance times specified, unless already 116, Transport Airplane Directorate, FAA; or The Boeing Company Model 737–100,
done. the European Aviation Safety Agency –200, –200C, –300, –400, and –500
(EASA); or Airbus’s EASA Design series airplanes. This proposed AD was
(g) Repetitive Inspections
Organization Approval (DOA). If approved by
At the later of times specified in the DOA, the approval must include the
prompted by an evaluation by the
paragraphs (g)(1) and (g)(2), or (g)(1) and DOA-authorized signature. design approval holder (DAH)
(g)(3), of this AD, as applicable: Do a detailed (3) Required for Compliance (RC): If any indicating that the bulkhead is subject
inspection for damage and cracking of the service information contains procedures or to widespread fatigue damage (WFD).
AFF of the pylons, in accordance with the tests that are identified as RC, those This proposed AD would require
Accomplishment Instructions of Airbus procedures and tests must be done to comply repetitive inspections of the aft pressure
Service Bulletin A320–54–1027, dated April with this AD; any procedures or tests that are bulkhead web for any cracking,
10, 2014. Repeat the inspection thereafter at not identified as RC are recommended. Those incorrectly drilled fastener holes, and
intervals not to exceed 2,500 flight cycles or procedures and tests that are not identified elongated fastener holes, and related
3,750 flight hours, whichever occurs first. as RC may be deviated from using accepted
(1) For all airplanes: Before exceeding methods in accordance with the operator’s
investigative and corrective actions if
5,000 flight cycles or 7,500 flight hours, maintenance or inspection program without necessary. We are proposing this AD to
whichever occurs first since the airplane’s obtaining approval of an AMOC provided the detect and correct fatigue cracking of the
first flight. procedures and tests identified as RC can be aft pressure bulkhead web at the ‘‘Y’’-
(2) For airplanes on which the inspection done and the airplane can be put back in an chord, which could result in reduced
specified in Airbus All Operators airworthy condition. Any substitutions or structural integrity of the airplane and
Transmission (AOT) A54N002–12 has been changes to procedures or tests identified as rapid decompression of the fuselage.
done as of the effective date of this AD: RC require approval of an AMOC. DATES: We must receive comments on
Within 2,500 flight cycles or 3,750 flight
hours, since the most recent accomplishment (j) Related Information this proposed AD by January 14, 2016.
of maintenance planning document (MPD) (1) Refer to Mandatory Continuing ADDRESSES: You may send comments,
Task ZL 371–01, or since doing the most Airworthiness Information (MCAI) EASA using the procedures found in 14 CFR
recent inspection specified in Airbus AOT Airworthiness Directive 2014–0154, dated 11.43 and 11.45, by any of the following
A54N002–12, whichever occurs first. July 2, 2014, for related information. This methods:
(3) For airplanes on which the inspection MCAI may be found in the AD docket on the • Federal eRulemaking Portal: Go to
specified in Airbus AOT A54N002–12 has Internet at http://www.regulations.gov by http://www.regulations.gov. Follow the
not been done as of the effective date of this searching for and locating Docket No. FAA–
instructions for submitting comments.
AD: Within 750 flight cycles or 1,500 flight 2015–6537.
• Fax: 202–493–2251.
hours after the effective date of this AD, (2) For service information identified in
this AD, contact Airbus, Airworthiness
• Mail: U.S. Department of
whichever occurs first.
Office—EAS, 1 Rond Point Maurice Bellonte, Transportation, Docket Operations, M–
(h) Repair 31707 Blagnac Cedex, France; telephone +33 30, West Building Ground Floor, Room
If any crack is found during any inspection 5 61 93 36 96; fax +33 5 61 93 44 51; email W12–140, 1200 New Jersey Avenue SE.,
required by paragraph (g) of this AD; before account.airworth-eas@airbus.com; Internet Washington, DC 20590.
further flight, repair in accordance with the http://www.airbus.com. You may view this • Hand Delivery: Deliver to Mail
Accomplishment Instructions of Airbus service information at the FAA, Transport address above between 9 a.m. and 5
Service Bulletin A320–54–1027, dated April Airplane Directorate, 1601 Lind Avenue SW., p.m., Monday through Friday, except
10, 2014. Accomplishment of this repair does Renton, WA. For information on the Federal holidays.
not terminate the repetitive inspections availability of this material at the FAA, call For service information identified in
required by paragraph (g) of this AD. 425–227–1221.
this proposed AD, contact Boeing
(i) Other FAA AD Provisions Issued in Renton, Washington, on Commercial Airplanes, Attention: Data
The following provisions also apply to this November 20, 2015. & Services Management, P. O. Box 3707,
AD: Jeffrey E. Duven, MC 2H–65, Seattle, WA 98124–2207;
(1) Alternative Methods of Compliance Manager, Transport Airplane Directorate, telephone 206–544–5000, extension 1;
(AMOCs): The Manager, International Aircraft Certification Service. fax 206–766–5680; Internet https://
Branch, ANM–116, FAA, has the authority to [FR Doc. 2015–30218 Filed 11–27–15; 8:45 am] www.myboeingfleet.com. You may view
approve AMOCs for this AD, if requested this referenced service information at
BILLING CODE 4910–13–P
using the procedures found in 14 CFR 39.19.
the FAA, Transport Airplane
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local Directorate, 1601 Lind Avenue SW.,
Flight Standards District Office, as DEPARTMENT OF TRANSPORTATION Renton, WA. For information on the
appropriate. If sending information directly availability of this material at the FAA,
to the International Branch, send it to ATTN: Federal Aviation Administration call 425–227–1221. It is also available
Sanjay Ralhan, Aerospace Engineer, on the Internet at http://
International Branch, ANM 116, Transport 14 CFR Part 39 www.regulations.gov by searching for
Airplane Directorate, FAA, 1601 Lind and locating Docket No. FAA–2015–
Avenue SW., Renton, WA 98057–3356; [Docket No. FAA–2015–6538; Directorate
jstallworth on DSK7TPTVN1PROD with PROPOSALS
6538.
telephone 425–227–1405; fax 425–227–1149. Identifier 2015–NM–031–AD]
Information may be emailed to: 9-ANM-116- Examining the AD Docket
AMOC-REQUESTS@faa.gov. Before using RIN 2120–AA64 You may examine the AD docket on
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal Airworthiness Directives; The Boeing the Internet at http://
inspector, the manager of the local flight Company Airplanes www.regulations.gov by searching for
standards district office/certificate holding and locating Docket No. FAA–2015–
district office. The AMOC approval letter AGENCY:Federal Aviation 6538; or in person at the Docket
must specifically reference this AD. Administration (FAA), DOT. Management Facility between 9 a.m.
VerDate Sep<11>2014 15:18 Nov 27, 2015 Jkt 238001 PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 E:\FR\FM\30NOP1.SGM 30NOP1](https://thefederalregister.org/doc/80_FR_74960/page/1.svg)
![Federal Register / Vol. 80, No. 229 / Monday, November 30, 2015 / Proposed Rules 74733
‘‘Compliance,’’ of Boeing Alert Service 100, –200, –200C, –300, –400, and –500 instructions on how to repair certain
Bulletin 737–53A1214, Revision 5, series airplanes, this proposed AD conditions, but this proposed AD would
dated January 30, 2015. Boeing applies to only certain The Boeing require repairing those conditions in
determined that the WFD-based Company Model 737–100, –200, –200C, one of the following ways:
inspections specified in tables 9, 10, and –300, –400, and –500 series airplanes • In accordance with a method that
11 of paragraph 1.E., ‘‘Compliance,’’ of (i.e., Group 2 airplanes). This difference we approve; or
Boeing Alert Service Bulletin 737– is due to the fact that this proposed AD
• Using data that meet the
53A1214, Revision 5, dated January 30, only addresses the new WFD
certification basis of the airplane, and
2015, affect only Group 2 airplanes inspections specified in Boeing Alert
that have been approved by the Boeing
because Group 1 airplanes will reach Service Bulletin 737–53A1214, Revision
their limit of validity before the Commercial Airplanes Organization
5, dated January 30, 2015.
compliance times specified in tables 9, Accomplishing the actions required Designation Authorization (ODA) whom
10, and 11 (Group 1 is for airplanes by paragraphs (g) and (h) of this we have authorized to make those
having line numbers 1 through 2565; proposed AD would terminate the findings.
Group 2 is for airplanes having line inspections required by paragraphs (k) Costs of Compliance
numbers 2566 through 3132). and (l) of AD 2012–18–13 R1,
Therefore, although Boeing Alert Amendment 39–17429 (78 FR 27020, We estimate that this proposed AD
Service Bulletin 737–53A1214, Revision May 9, 2013). affects 122 airplanes of U.S. registry.
5, dated January 30, 2015, is effective for The service bulletin specifies to We estimate the following costs to
all The Boeing Company Model 737– contact the manufacturer for comply with this proposed AD:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspections of the web Up to 60 work-hours × $85 per $0 Up to $5,100 per inspection cycle Up to $622,200
at the ‘‘Y’’-chord. hour = Up to $5,100 per in- per inspection cycle.
spection cycle.
We have received no definitive data responsibilities among the various The Boeing Company: Docket No. FAA–
that would enable us to provide cost levels of government. 2015–6538; Directorate Identifier 2015–
estimates for the on-condition actions For the reasons discussed above, I NM–031–AD.
specified in this proposed AD. certify this proposed regulation: (a) Comments Due Date
(1) Is not a ‘‘significant regulatory
Authority for This Rulemaking action’’ under Executive Order 12866, We must receive comments by January 14,
Title 49 of the United States Code (2) Is not a ‘‘significant rule’’ under 2016.
specifies the FAA’s authority to issue the DOT Regulatory Policies and (b) Affected ADs
rules on aviation safety. Subtitle I, Procedures (44 FR 11034, February 26,
This AD affects AD 2012–18–13 R1,
section 106, describes the authority of 1979),
(3) Will not affect intrastate aviation Amendment 39–17429 (78 FR 27020, May 9,
the FAA Administrator. Subtitle VII: 2013).
Aviation Programs, describes in more in Alaska, and
detail the scope of the Agency’s (4) Will not have a significant (c) Applicability
authority. economic impact, positive or negative, This AD applies to The Boeing Company
We are issuing this rulemaking under on a substantial number of small entities Model 737–100, –200, –200C, –300, –400,
the authority described in Subtitle VII, under the criteria of the Regulatory and –500 series airplanes, certificated in any
Part A, Subpart III, Section 44701: Flexibility Act. category, identified as Group 2 in Boeing
‘‘General requirements.’’ Under that List of Subjects in 14 CFR Part 39 Alert Service Bulletin 737–53A1214,
section, Congress charges the FAA with Revision 5, dated January 30, 2015.
Air transportation, Aircraft, Aviation
promoting safe flight of civil aircraft in
safety, Incorporation by reference, (d) Subject
air commerce by prescribing regulations
Safety. Air Transport Association (ATA) of
for practices, methods, and procedures
the Administrator finds necessary for The Proposed Amendment America Code 53, Fuselage.
safety in air commerce. This regulation Accordingly, under the authority (e) Unsafe Condition
is within the scope of that authority delegated to me by the Administrator, This AD was prompted by an evaluation by
because it addresses an unsafe condition the FAA proposes to amend 14 CFR part the design approval holder indicating that
that is likely to exist or develop on 39 as follows: the aft pressure bulkhead is subject to
products identified in this rulemaking
widespread fatigue damage. We are issuing
action. PART 39—AIRWORTHINESS this AD to detect and correct fatigue cracking
Regulatory Findings DIRECTIVES of the aft pressure bulkhead web at the ‘‘Y’’-
jstallworth on DSK7TPTVN1PROD with PROPOSALS
chord, which could result in reduced
We determined that this proposed AD ■ 1. The authority citation for part 39
structural integrity of the airplane and rapid
would not have federalism implications continues to read as follows:
decompression of the fuselage.
under Executive Order 13132. This Authority: 49 U.S.C. 106(g), 40113, 44701.
proposed AD would not have a (f) Compliance
substantial direct effect on the States, on § 39.13 [Amended] Comply with this AD within the
the relationship between the national ■ 2. The FAA amends § 39.13 by adding compliance times specified, unless already
Government and the States, or on the the following new airworthiness done.
distribution of power and directive (AD):
VerDate Sep<11>2014 15:18 Nov 27, 2015 Jkt 238001 PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 E:\FR\FM\30NOP1.SGM 30NOP1](https://thefederalregister.org/doc/80_FR_74960/page/3.svg)
![74734 Federal Register / Vol. 80, No. 229 / Monday, November 30, 2015 / Proposed Rules
(g) Repetitive Inspections of the Aft Pressure (k) Credit for Previous Actions DEPARTMENT OF TRANSPORTATION
Bulkhead Web at the ‘‘Y’’-Chord Upper This paragraph provides credit for the
Bulkhead Federal Aviation Administration
actions required by paragraphs (g) and (h) of
At the applicable time specified in tables this AD, if the actions were performed before
9 and 10 of paragraph 1.E., ‘‘Compliance,’’ of the effective date of this AD using Boeing 14 CFR Part 71
Boeing Alert Service Bulletin 737–53A1214,
Alert Service Bulletin 737–53A1214, [Docket No. FAA–2015–4006; Airspace
Revision 5, dated January 30, 2015: Do
detailed and low frequency eddy current Revision 4, dated December 16, 2011, which Docket No. 15–ANE–3]
(LFEC) inspections from the aft side of the aft is not incorporated by reference in this AD.
pressure bulkhead web, or do detailed and Proposed Amendment of Class E
(l) Alternative Methods of Compliance
high frequency eddy current (HFEC) Airspace; West Dover, VT
(AMOCs)
inspections from the forward side of the aft
pressure bulkhead web, for any cracking, (1) The Manager, Seattle Aircraft AGENCY: Federal Aviation
incorrectly drilled fastener hole, and Certification Office (ACO), FAA, has the Administration (FAA), DOT.
elongated fastener hole, and do all applicable authority to approve AMOCs for this AD, if ACTION: Notice of proposed rulemaking
related investigative and corrective actions, requested using the procedures found in 14 (NPRM).
in accordance with Part I of the CFR 39.19. In accordance with 14 CFR 39.19,
Accomplishment Instructions of Boeing Alert SUMMARY: This action proposes to
send your request to your principal inspector
Service Bulletin 737–53A1214, Revision 5, or local Flight Standards District Office, as
amend Class E Airspace at West Dover,
dated January 30, 2015, except as required by
appropriate. If sending information directly
VT as the Mt. Snow Non-Directional
paragraph (i) of this AD. Do all related Beacon (NDB) has been
investigative and corrective actions before to the manager of the ACO, send it to the
attention of the person identified in
decommissioned, requiring airspace
further flight. If any cracking, incorrectly redesign at Deerfield Valley Regional
drilled fastener hole, or elongated fastener paragraph (m)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOC- Airport. This action would enhance the
hole is found, before further flight, repair the
web using a method approved in accordance Requests@faa.gov. safety and management of Instrument
with the procedures specified in paragraph (2) Before using any approved AMOC, Flight Rules (IFR) operations at the
(l) of this AD. Thereafter, repeat the notify your appropriate principal inspector, airport. This action also would
inspections at the applicable times specified or lacking a principal inspector, the manager recognize the airport’s name change.
in tables 9 and 10 of paragraph 1.E., of the local flight standards district office/ DATES: Comments must be received on
‘‘Compliance’’ of Boeing Alert Service or before January 14, 2016.
certificate holding district office.
Bulletin 737–53A1214, Revision 5, dated
(3) An AMOC that provides an acceptable ADDRESSES: Send comments on this rule
January 30, 2015.
level of safety may be used for any repair to: U. S. Department of Transportation,
(h) Repetitive Inspections of the Aft Pressure required by this AD if it is approved by the Docket Operations, 1200 New Jersey
Bulkhead Web at the ‘‘Y’’-Chord Below S–15 Boeing Commercial Airplanes Organization Avenue SE, West Bldg Ground Floor Rm
At the applicable time specified in table 11 Designation Authorization (ODA) that has W12–140, Washington, DC 20590–0001;
of 1.E., ‘‘Compliance’’ of Boeing Alert Service been authorized by the Manager, Seattle Telephone: 1–800–647–5527; Fax: 202–
Bulletin 737–53A1214, Revision 5, dated ACO, to make those findings. For a repair 493–2251. You must identify the Docket
January 30, 2015: Do detailed and eddy method to be approved, the repair must meet Number FAA–2015–4006; Airspace
current inspections of the web from the the certification basis of airplane, and the Docket No. 15–ANE–3, at the beginning
forward or aft side of the bulkhead for any
cracking, incorrectly drilled fastener hole,
approval must specifically refer to this AD. of your comments. You may also submit
and elongated fastener hole, and do all (m) Related Information
and review received comments through
applicable corrective actions, in accordance the Internet at http://
(1) For more information about this AD, www.regulations.gov. You may review
with Part III of the Accomplishment
Instructions of Boeing Alert Service Bulletin contact Alan Pohl, Aerospace Engineer, the public docket containing the
737–53A1214, Revision 5, dated January 30, Airframe Branch, ANM–120S, FAA, Seattle proposal, any comments received, and
2015, except as required by paragraph (i) of Aircraft Certification Office (ACO), 1601 Lind any final disposition in person in the
this AD. Do all corrective actions before Avenue SW., Renton, WA 98057–3356; Dockets Office between 9:00 a.m. and
further flight. If any cracking, incorrectly telephone: 425–917–6450; fax: 425–917–
5:00 p.m., Monday through Friday,
drilled fastener hole, or elongated fastener 6590; email: Alan.Pohl@faa.gov.
hole is found, before further flight, repair the
except Federal holidays. The Docket
(2) For service information identified in
web using a method approved in accordance Office (telephone 1–800–647–5527), is
this AD, contact Boeing Commercial
with the procedures specified in paragraph on the ground floor of the building at
Airplanes, Attention: Data & Services
(l) of this AD. Thereafter, repeat the the above address.
Management, P. O. Box 3707, MC 2H–65,
inspections at the applicable times specified FAA Order 7400.9Z, Airspace
Seattle, WA 98124–2207; telephone 206–
in table 11 of paragraph 1.E., ‘‘Compliance,’’ Designations and Reporting Points, and
of Boeing Alert Service Bulletin 737– 544–5000, extension 1; fax 206–766–5680;
subsequent amendments can be viewed
53A1214, Revision 5, dated January 30, 2015. Internet https://www.myboeingfleet.com. You
online at http://www.faa.gov/air_traffic/
may view this referenced service information
(i) Exception to the Service Information publications/. For further information,
at the FAA, Transport Airplane Directorate,
Where Boeing Alert Service Bulletin 737– you can contact the Airspace Policy and
1601 Lind Avenue SW., Renton, WA. For
53A1214, Revision 5, dated January 30, 2015, information on the availability of this
Regulations Group, Federal Aviation
specifies to contact Boeing for repair material at the FAA, call 425–227–1221.
Administration, 800 Independence
instructions: Before further flight, repair Avenue SW, Washington, DC, 20591;
using a method approved in accordance with Issued in Renton, Washington, on telephone: 202–267–8783. The Order is
jstallworth on DSK7TPTVN1PROD with PROPOSALS
the procedures specified in paragraph (l) of November 20, 2015. also available for inspection at the
this AD. Jeffrey E. Duven, National Archives and Records
(j) Terminating Action for Other Rulemaking Manager, Transport Airplane Directorate, Administration (NARA). For
Accomplishing the actions required by Aircraft Certification Service. information on the availability of FAA
paragraphs (g) and (h) of this AD terminates [FR Doc. 2015–30217 Filed 11–27–15; 8:45 am] Order 7400.9Z at NARA, call 202–741–
the inspections required by paragraphs (k) BILLING CODE 4910–13–P
6030, or go to http://www.archives.gov/
and (l) of AD 2012–18–13 R1, Amendment federal_register/code_of_federal-
39–17429 (78 FR 27020, May 9, 2013). regulations/ibr_locations.html.
VerDate Sep<11>2014 15:18 Nov 27, 2015 Jkt 238001 PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 E:\FR\FM\30NOP1.SGM 30NOP1](https://thefederalregister.org/doc/80_FR_74960/page/4.svg)
Document Created: 2018-03-01 11:11:42
Document Modified: 2018-03-01 11:11:42
| 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 January 14, 2016. | |
| Contact | Alan Pohl, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-917- 6450; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 80 FR 74731 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
2025 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR