81 FR 72554 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 203 (October 20, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 203 (October 20, 2016)
| Page Range | 72554-72557 | |
| FR Document | 2016-24262 |
[Federal Register Volume 81, Number 203 (Thursday, October 20, 2016)] [Proposed Rules] [Pages 72554-72557] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-24262] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-9188; Directorate Identifier 2016-NM-102-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) 2007-26- 04, which applies to certain Boeing Model 737-100, -200, -200C, -300, - 400, and -500 series airplanes. AD 2007-26-04 currently requires repetitive inspections for cracking around the heads of the fasteners on the forward fastener row of certain areas of a certain circumferential butt splice, and repair if necessary; and also requires a preventive modification, which eliminates the need for the repetitive inspections. Since we issued AD 2007-26-04, an evaluation by the design approval holder (DAH) indicating that the forward skin panel at a circumferential butt splice between certain stringers is subject to widespread fatigue damage (WFD). This proposed AD would remove the mandatory modification. It would add repetitive inspections of the skin for cracking at the aft fastener column and a one-time inspection for defects of the production countersunk rivets, and require corrective actions if necessary. It would also add an optional skin trim-out repair, which would terminate certain inspections. We are proposing this AD to prevent cracking of the station (STA) 259.5 circumferential butt splice, which could result in loss of structural integrity of the fuselage skin and possible loss of cabin pressure. DATES: We must receive comments on this proposed AD by December 5, 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-2016-9188. 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- 9188; 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: Wade Sullivan, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6430; fax: 425-917-6590; email: [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about [[Page 72555]] this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2016-9188; Directorate Identifier 2016-NM-102-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 Fatigue damage can occur locally, in small areas or structural design details, or globally, in widespread areas. Multiple-site damage is widespread damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Widespread 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. This condition is known as widespread fatigue damage. It is associated with general degradation of large areas of structure with similar structural details and stress levels. 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. On December 10, 2007, we issued AD 2007-26-04, Amendment 39-15806 (72 FR 71216, December 17, 2007) (``AD 2007-26-04''), for certain Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD 2007-26-04 currently requires repetitive inspections for cracking around the heads of the fasteners on the forward fastener row of certain areas of the STA 259.5 circumferential butt splice, and repair if necessary; and also requires a preventive modification, which eliminates the need for the repetitive inspections. AD 2007-26-04 resulted from a report of multiple cracks in the fuselage skin of a Model 737-200 airplane, at the forward fastener row of the STA 259.5 circumferential butt splice between stringers 19 and 24. We issued AD 2007-26-04 to prevent cracking of the STA 259.5 circumferential butt splice, which could result in loss of structural integrity of the fuselage skin and possible loss of cabin pressure. Actions Since AD 2007-26-04 Was Issued Since we issued AD 2007-26-04, an evaluation by the DAH indicated that the forward skin panel at STA 259.5 circumferential butt splice between stringers 19L and 24L is subject to WFD. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 737-53A1267, Revision 1, dated March 8, 2016 (``ASB 737-53A1267 R1''). The service information describes procedures for detailed inspections and high frequency eddy current (HFEC) surface inspections of the skin around the fastener heads for any crack on the forward and aft fastener columns, left and right sides, at STA 259.5 circumferential butt splice; a detailed inspection for any defect of the production countersunk rivet heads on both forward and aft fastener columns, left and right sides, at STA 259.5 circumferential butt splice; and corrective actions, including a skin trim-out repair and other repairs. 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 Although this proposed AD does not explicitly restate the requirements of AD 2007-26-04, this proposed AD would retain certain requirements of AD 2007-26-04. Those requirements are referenced in the service information identified previously, which, in turn, is referenced in this proposed AD. This proposed AD would also 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-2016-9188. 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. Explanation of Applicability Model 737 airplanes having line numbers 1 through 291 have a limit of validity (LOV) of 34,000 total flight cycles, and the actions proposed in this NPRM, as specified in ASB 737-53A1267 R1, would be required at a compliance time occurring after that LOV. Although operation of an airplane beyond its LOV is prohibited by 14 CFR 121.1115 and 129.115, this proposed AD would include those airplanes in the applicability in the event the LOV is extended in the future. Differences Between This Proposed AD and the Service Information ASB 737-53A1267 R1, specifies to contact the manufacturer for certain instructions, but this proposed AD [[Page 72556]] would require accomplishment of repair methods, modification deviations, and alteration deviations 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 115 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...................... 28 work-hours x $85 $0 $2,380 per $273,700 per per hour = $2,380 inspection cycle. inspection cycle. per inspection cycle. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for the optional skin-trim-out repair specified in this proposed AD. 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 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: (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) 2007-26-04, Amendment 39-15806 (72 FR 71216, December 17, 2007), and adding the following new AD: The Boeing Company: Docket No. FAA-2016-9188; Directorate Identifier 2016-NM-102-AD. (a) Comments Due Date The FAA must receive comments on this AD action by December 5, 2016. (b) Affected Ads This AD replaces AD 2007-26-04, Amendment 39-15806 (72 FR 71216, December 17, 2007) (``AD 2007-26-04''). (c) Applicability This AD applies to The Boeing Company Model 737-100, -200, - 200C, -300, -400, and -500 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 737- 53A1267, Revision 1, dated March 8, 2016 (``ASB 737-53A1267 R1''). (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 forward skin panel at station (STA) 259.5 circumferential butt splice between stringers 19L and 24L is subject to widespread fatigue damage (WFD). We are issuing this AD to prevent cracking of the STA 259.5 circumferential butt splice, which could result in loss of structural integrity of the fuselage skin and possible loss of cabin pressure. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Actions for Group 2 Airplanes For airplanes identified as Group 2 in ASB 737-53A1267 R1: Within 120 days after the effective date of this AD, inspect the airplane and do all applicable corrective actions using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (h) Inspections for Group 1 Airplanes For airplanes identified as Group 1 in ASB 737-53A1267 R1: Except as specified in paragraph (j)(1) of this AD, at the applicable time specified in paragraph 1.E. ``Compliance'' of ASB 737-53A1267 R1, do the applicable actions specified in paragraphs (h)(1) and (h)(2) of this AD; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of ASB 737-53A1267 R1, except as specified in paragraph (j)(2) of this AD. Do all applicable corrective actions before further flight. Repeat the applicable inspections specified in paragraph (h)(1) of this AD thereafter at the applicable intervals specified paragraph 1.E., ``Compliance,'' of ASB 737-53A1267 R1, except as provided by paragraph (i) of this AD. (1) Do detailed inspections and high frequency eddy current (HFEC) surface inspections of the skin around the fastener heads for any crack on the forward and aft fastener columns, left and right sides, at STA 259.5 circumferential butt splice, in accordance with Parts 1, 2, 6, 7, 8, and 9 of [[Page 72557]] the Accomplishment Instructions of ASB 737-53A1267 R1, as applicable. (2) Do a one-time detailed inspection for any defect of the production countersunk rivet heads on both forward and aft fastener columns, left and right sides, at STA 259.5 circumferential butt splice, in accordance with Part 3 of the Accomplishment Instructions of ASB 737-53A1267 R1. (i) Optional Terminating Repairs (1) For airplanes identified as Group 1, Configuration 1 in ASB 737-53A1267 R1: Doing the skin trim-out repair specified in Part 5 of the Accomplishment Instructions of ASB 737-53A1267 R1 terminates the repetitive inspections required by paragraph (h) of this AD that are specified in Part 1 of the Accomplishment Instructions of ASB 737-53A1267 R1 only; all other repetitive inspections required by paragraph (h) of this AD must be done, except as provided by paragraph (i)(2) of this AD. (2) For airplanes identified as Group 1, Configuration 1 in ASB 737-53A1267 R1: Doing the skin repair specified in Part 4 of the Accomplishment Instructions of ASB 737-53A1267 R1, terminates the repetitive inspections required by paragraph (h) of this AD that are specified in Part 1 and Part 2 of the Accomplishment Instructions of ASB 737-53A1267 R1 for the repaired area only; all other repetitive inspections required by paragraph (h) of this AD must be done, except as provided by paragraph (i)(1) of this AD. (j) Exceptions to Service Information (1) Where paragraph 1.E., ``Compliance,'' of ASB 737-53A1267 R1, specifies a compliance time ``after the Revision 1 date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Although ASB 737-53A1267 R1, specifies to contact Boeing for appropriate action, and specifies that action as ``RC'' (Required for Compliance), this AD requires repair before further flight using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (k) 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 (l)(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. 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 previously for AD 2007-26-04 are approved as AMOCs for the corresponding provisions of this AD. (5) Except as required by paragraph (j)(2) of this AD: For service information that contains steps that are labeled as RC, the provisions of paragraphs (k)(5)(i) and (k)(5)(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. If a step or sub-step is labeled ``RC Exempt,'' then the RC requirement is removed from that step or sub-step. 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. (l) Related Information (1) For more information about this AD, contact Wade Sullivan, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057- 3356; phone: 425-917-6430; 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 206-66-5680; 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 September 30, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-24262 Filed 10-19-16; 8:45 am] BILLING CODE 4910-13-P
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the FAA proposes to amend 14 CFR part certificate holding district office before DATES: We must receive comments on
39 as follows: operating any aircraft complying with this this proposed AD by December 5, 2016.
AD through an AMOC.
ADDRESSES: You may send comments,
PART 39—AIRWORTHINESS (g) Subject using the procedures found in 14 CFR
DIRECTIVES 11.43 and 11.45, by any of the following
Joint Aircraft Service Component (JASC)
■ 1. The authority citation for part 39 Code: 3452, ATC Transponder System. methods:
continues to read as follows: Issued in Fort Worth, Texas, on October 11, • Federal eRulemaking Portal: Go to
2016. http://www.regulations.gov. Follow the
Authority: 49 U.S.C. 106(g), 40113, 44701. instructions for submitting comments.
Lance T. Gant,
§ 39.13 [Amended] • Fax: 202–493–2251.
Manager, Rotorcraft Directorate, Aircraft
■ 2. The FAA amends § 39.13 by adding Certification Service. • Mail: U.S. Department of
the following new airworthiness Transportation, Docket Operations, M–
[FR Doc. 2016–25255 Filed 10–19–16; 8:45 am]
directive (AD): 30, West Building Ground Floor, Room
BILLING CODE 4910–13–P
W12–140, 1200 New Jersey Avenue SE.,
NavWorx, Inc.: Docket No. FAA–2016–9226; Washington, DC 20590.
Directorate Identifier 2016–SW–065–AD. • Hand Delivery: Deliver to Mail
DEPARTMENT OF TRANSPORTATION
(a) Applicability address above between 9 a.m. and 5
This AD applies to the following NavWorx, Federal Aviation Administration p.m., Monday through Friday, except
Inc., Automatic Dependent Surveillance- Federal holidays.
Broadcast (ADS–B) Universal Access 14 CFR Part 39 For service information identified in
Transceiver units (unit) installed on aircraft this NPRM, contact Boeing Commercial
certificated in any category: [Docket No. FAA–2016–9188; Directorate Airplanes, Attention: Data & Services
(1) Model ADS600–B part number (P/N) Identifier 2016–NM–102–AD] Management, P.O. Box 3707, MC 2H–65,
200–0012; Seattle, WA 98124–2207; telephone
(2) Model ADS600–B P/N 200–0013; and RIN 2120–AA64
(3) Model ADS600–EXP P/N 200–8013.
206–544–5000, extension 1; fax 206–
766–5680; Internet https://
(b) Unsafe Condition Airworthiness Directives; The Boeing www.myboeingfleet.com. You may view
This AD defines the unsafe condition as an
Company Airplanes this referenced service information at
ADS–B unit incorrectly broadcasting a AGENCY: Federal Aviation the FAA, Transport Airplane
Source Integrity Level of 3 instead of 0. This Administration (FAA), DOT. Directorate, 1601 Lind Avenue SW.,
condition could result in the unit Renton, WA. For information on the
communicating unreliable position ACTION: Notice of proposed rulemaking
(NPRM). availability of this material at the FAA,
information to Air Traffic Control and nearby
aircraft and a subsequent aircraft collision.
call 425–227–1221. It is also available
SUMMARY: We propose to supersede on the internet at http://
(c) Comments Due Date Airworthiness Directive (AD) 2007–26– www.regulations.gov by searching for
We must receive comments by December 04, which applies to certain Boeing and locating Docket No. FAA–2016–
19, 2016. Model 737–100, –200, –200C, –300, 9188.
(d) Compliance –400, and –500 series airplanes. AD Examining the AD Docket
You are responsible for performing each
2007–26–04 currently requires
repetitive inspections for cracking You may examine the AD docket on
action required by this AD within the
specified compliance time unless it has around the heads of the fasteners on the the Internet at http://
already been accomplished prior to that time. forward fastener row of certain areas of www.regulations.gov by searching for
a certain circumferential butt splice, and and locating Docket No. FAA–2016–
(e) Required Actions 9188; or in person at the Docket
repair if necessary; and also requires a
(1) Before further flight, remove the ADS– preventive modification, which Management Facility between 9 a.m.
B unit. eliminates the need for the repetitive and 5 p.m., Monday through Friday,
(2) After the effective date of this AD, do except Federal holidays. The AD docket
not install any ADS–B unit that is listed in
inspections. Since we issued AD 2007–
26–04, an evaluation by the design contains this proposed AD, the
the applicability of this AD on any aircraft.
approval holder (DAH) indicating that regulatory evaluation, any comments
(f) Alternative Methods of Compliance the forward skin panel at a received, and other information. The
(AMOC) circumferential butt splice between street address for the Docket Office
(1) The Manager, Fort Worth Aircraft certain stringers is subject to (phone: 800–647–5527) is in the
Certification Office, FAA, may approve widespread fatigue damage (WFD). This ADDRESSES section. Comments will be
AMOCs for this AD. Send your proposal to: proposed AD would remove the available in the AD docket shortly after
Kyle Cobble, Aviation Safety Engineer, Fort receipt.
Worth Aircraft Certification Office, Rotorcraft
mandatory modification. It would add
Directorate, FAA, 10101 Hillwood Pkwy., repetitive inspections of the skin for FOR FURTHER INFORMATION CONTACT:
Fort Worth, TX 76177, telephone (817) 222– cracking at the aft fastener column and Wade Sullivan, Aerospace Engineer,
5172, email kyle.cobble@faa.gov; or Michael a one-time inspection for defects of the Airframe Branch, ANM–120S, FAA,
Heusser, Program Manager, Continued production countersunk rivets, and Seattle Aircraft Certification Office
Operational Safety Branch, Rotorcraft require corrective actions if necessary. It (ACO), 1601 Lind Avenue SW., Renton,
mstockstill on DSK3G9T082PROD with PROPOSALS
Directorate, FAA, 10101 Hillwood Pkwy., would also add an optional skin trim- WA 98057–3356; phone: 425–917–6430;
Fort Worth, TX 76177, telephone (817) 222– out repair, which would terminate fax: 425–917–6590; email:
5038, email michael.a.heusser@faa.gov. certain inspections. We are proposing wade.sullivan@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
this AD to prevent cracking of the SUPPLEMENTARY INFORMATION:
14 CFR part 91, subpart K, we suggest that station (STA) 259.5 circumferential butt
splice, which could result in loss of Comments Invited
you notify your principal inspector, or
lacking a principal inspector, the manager of structural integrity of the fuselage skin We invite you to send any written
the local flight standards district office or and possible loss of cabin pressure. relevant data, views, or arguments about
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would require accomplishment of repair • Using data that meet the Costs of Compliance
methods, modification deviations, and certification basis of the airplane, and
alteration deviations in one of the that have been approved by the Boeing We estimate that this proposed AD
following ways: Commercial Airplanes Organization affects 115 airplanes of U.S. registry. We
Designation Authorization (ODA) whom estimate the following costs to comply
• In accordance with a method that with this proposed AD:
we have authorized to make those
we approve; or
findings.
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspections .............................. 28 work-hours × $85 per hour $0 $2,380 per inspection cycle .... $273,700 per inspection cycle.
= $2,380 per inspection
cycle.
We have received no definitive data Procedures (44 FR 11034, February 26, (d) Subject
that would enable us to provide cost 1979), Air Transport Association (ATA) of
estimates for the optional skin-trim-out (3) Will not affect intrastate aviation America Code 53, Fuselage.
repair specified in this proposed AD. in Alaska, and
(e) Unsafe Condition
We have received no definitive data (4) Will not have a significant
economic impact, positive or negative, This AD was prompted by an evaluation by
that would enable us to provide cost the design approval holder (DAH) indicating
estimates for the on-condition actions on a substantial number of small entities
under the criteria of the Regulatory that the forward skin panel at station (STA)
specified in this proposed AD. 259.5 circumferential butt splice between
Flexibility Act. stringers 19L and 24L is subject to
Authority for This Rulemaking
List of Subjects in 14 CFR Part 39 widespread fatigue damage (WFD). We are
Title 49 of the United States Code issuing this AD to prevent cracking of the
Air transportation, Aircraft, Aviation STA 259.5 circumferential butt splice, which
specifies the FAA’s authority to issue
safety, Incorporation by reference, could result in loss of structural integrity of
rules on aviation safety. Subtitle I,
Safety. the fuselage skin and possible loss of cabin
Section 106, describes the authority of
The Proposed Amendment pressure.
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more Accordingly, under the authority (f) Compliance
detail the scope of the Agency’s delegated to me by the Administrator, Comply with this AD within the
authority. the FAA proposes to amend 14 CFR part compliance times specified, unless already
We are issuing this rulemaking under 39 as follows: done.
the authority described in Subtitle VII, (g) Actions for Group 2 Airplanes
Part A, Subpart III, Section 44701, PART 39—AIRWORTHINESS
For airplanes identified as Group 2 in ASB
‘‘General requirements.’’ Under that DIRECTIVES
737–53A1267 R1: Within 120 days after the
section, Congress charges the FAA with effective date of this AD, inspect the airplane
promoting safe flight of civil aircraft in ■ 1. The authority citation for part 39
and do all applicable corrective actions using
air commerce by prescribing regulations continues to read as follows:
a method approved in accordance with the
for practices, methods, and procedures Authority: 49 U.S.C. 106(g), 40113, 44701. procedures specified in paragraph (k) of this
the Administrator finds necessary for AD.
§ 39.13 [Amended]
safety in air commerce. This regulation (h) Inspections for Group 1 Airplanes
is within the scope of that authority ■ 2. The FAA amends § 39.13 by
because it addresses an unsafe condition removing Airworthiness Directive (AD) For airplanes identified as Group 1 in ASB
2007–26–04, Amendment 39–15806 (72 737–53A1267 R1: Except as specified in
that is likely to exist or develop on paragraph (j)(1) of this AD, at the applicable
products identified in this rulemaking FR 71216, December 17, 2007), and
adding the following new AD: time specified in paragraph 1.E.
action. ‘‘Compliance’’ of ASB 737–53A1267 R1, do
The Boeing Company: Docket No. FAA– the applicable actions specified in
Regulatory Findings 2016–9188; Directorate Identifier 2016– paragraphs (h)(1) and (h)(2) of this AD; and
We have determined that this NM–102–AD. do all applicable corrective actions; in
proposed AD would not have federalism (a) Comments Due Date accordance with the Accomplishment
implications under Executive Order Instructions of ASB 737–53A1267 R1, except
The FAA must receive comments on this
13132. This proposed AD would not as specified in paragraph (j)(2) of this AD. Do
AD action by December 5, 2016.
all applicable corrective actions before
have a substantial direct effect on the further flight. Repeat the applicable
(b) Affected Ads
States, on the relationship between the inspections specified in paragraph (h)(1) of
national Government and the States, or This AD replaces AD 2007–26–04,
Amendment 39–15806 (72 FR 71216, this AD thereafter at the applicable intervals
on the distribution of power and specified paragraph 1.E., ‘‘Compliance,’’ of
December 17, 2007) (‘‘AD 2007–26–04’’).
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responsibilities among the various ASB 737–53A1267 R1, except as provided by
levels of government. (c) Applicability paragraph (i) of this AD.
For the reasons discussed above, I This AD applies to The Boeing Company (1) Do detailed inspections and high
certify that the proposed regulation: Model 737–100, –200, –200C, –300, –400, frequency eddy current (HFEC) surface
and –500 series airplanes, certificated in any inspections of the skin around the fastener
(1) Is not a ‘‘significant regulatory heads for any crack on the forward and aft
category, as identified in Boeing Alert
action’’ under Executive Order 12866, Service Bulletin 737–53A1267, Revision 1, fastener columns, left and right sides, at STA
(2) Is not a ‘‘significant rule’’ under dated March 8, 2016 (‘‘ASB 737–53A1267 259.5 circumferential butt splice, in
the DOT Regulatory Policies and R1’’). accordance with Parts 1, 2, 6, 7, 8, and 9 of
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![Federal Register / Vol. 81, No. 203 / Thursday, October 20, 2016 / Proposed Rules 72557
the Accomplishment Instructions of ASB Designation Authorization (ODA) that has DEPARTMENT OF TRANSPORTATION
737–53A1267 R1, as applicable. been authorized by the Manager, Los Angeles
(2) Do a one-time detailed inspection for ACO, to make those findings. To be Federal Aviation Administration
any defect of the production countersunk approved, the repair method, modification
rivet heads on both forward and aft fastener deviation, or alteration deviation must meet
columns, left and right sides, at STA 259.5
14 CFR Part 39
the certification basis of the airplane and the
circumferential butt splice, in accordance [Docket No. FAA–2016–9186; Directorate
with Part 3 of the Accomplishment approval must specifically refer to this AD.
Identifier 2015–NM–160–AD]
Instructions of ASB 737–53A1267 R1. (4) AMOCs approved previously for AD
2007–26–04 are approved as AMOCs for the RIN 2120–AA64
(i) Optional Terminating Repairs corresponding provisions of this AD.
(1) For airplanes identified as Group 1, (5) Except as required by paragraph (j)(2) Airworthiness Directives; BAE
Configuration 1 in ASB 737–53A1267 R1: of this AD: For service information that Systems (Operations) Limited
Doing the skin trim-out repair specified in contains steps that are labeled as RC, the
Part 5 of the Accomplishment Instructions of AGENCY: Federal Aviation
provisions of paragraphs (k)(5)(i) and Administration (FAA), DOT.
ASB 737–53A1267 R1 terminates the
(k)(5)(ii) of this AD apply.
repetitive inspections required by paragraph ACTION: Notice of proposed rulemaking
(h) of this AD that are specified in Part 1 of (i) The steps labeled as RC, including
(NPRM).
the Accomplishment Instructions of ASB substeps under an RC step and any figures
737–53A1267 R1 only; all other repetitive identified in an RC step, must be done to SUMMARY: We propose to supersede
inspections required by paragraph (h) of this comply with the AD. If a step or sub-step is Airworthiness Directive (AD) 2012–16–
AD must be done, except as provided by labeled ‘‘RC Exempt,’’ then the RC 08, for certain BAE Systems
paragraph (i)(2) of this AD. requirement is removed from that step or (Operations) Limited Model BAe 146
(2) For airplanes identified as Group 1, sub-step. An AMOC is required for any and Avro 146–RJ series airplanes. AD
Configuration 1 in ASB 737–53A1267 R1: deviations to RC steps, including substeps
Doing the skin repair specified in Part 4 of 2012–16–08 currently requires
and identified figures. repetitive detailed inspections for
the Accomplishment Instructions of ASB
737–53A1267 R1, terminates the repetitive (ii) Steps not labeled as RC may be bulging, surface anomalies, and cracking
inspections required by paragraph (h) of this deviated from using accepted methods in of the fuselage skin adjacent to the
AD that are specified in Part 1 and Part 2 of accordance with the operator’s maintenance discharge valves, and repair and
the Accomplishment Instructions of ASB or inspection program without obtaining application of additional sealant in the
737–53A1267 R1 for the repaired area only; approval of an AMOC, provided the RC steps, affected area if necessary. Since we
all other repetitive inspections required by including substeps and identified figures, can issued AD 2012–16–08, it was found
paragraph (h) of this AD must be done, still be done as specified, and the airplane that airplanes on which a certain
except as provided by paragraph (i)(1) of this can be put back in an airworthy condition.
AD. modification was incorporated during
(l) Related Information production were excluded from the
(j) Exceptions to Service Information applicability, but are also affected by the
(1) For more information about this AD,
(1) Where paragraph 1.E., ‘‘Compliance,’’ of condition that precipitated AD 2012–
ASB 737–53A1267 R1, specifies a contact Wade Sullivan, Aerospace Engineer,
16–08. This proposed AD would retain
compliance time ‘‘after the Revision 1 date of Airframe Branch, ANM–120S, FAA, Seattle
the requirements of AD 2012–16–08,
this service bulletin,’’ this AD requires Aircraft Certification Office (ACO), 1601 Lind
expand the applicability, and require an
compliance within the specified compliance Avenue SW., Renton, WA 98057–3356;
additional one-time inspection for the
time after the effective date of this AD. phone: 425–917–6430; fax: 425–917–6590;
(2) Although ASB 737–53A1267 R1, presence of water traps/air driers to
email: wade.sullivan@faa.gov.
specifies to contact Boeing for appropriate determine which airplanes must be
(2) For service information identified in
action, and specifies that action as ‘‘RC’’ inspected. We are proposing this AD to
this AD, contact Boeing Commercial
(Required for Compliance), this AD requires Airplanes, Attention: Data & Services
detect and correct bulging, surface
repair before further flight using a method
Management, P.O. Box 3707, MC 2H–65,
anomalies, and cracking that could
approved in accordance with the procedures propagate towards the forward
specified in paragraph (k) of this AD. Seattle, WA 98124–2207; telephone 206–
544–5000, extension 1; fax 206–66–5680;
discharge valve outlet and result in the
(k) Alternative Methods of Compliance Internet https://www.myboeingfleet.com. You
failure of the fuselage skin, leading to a
(AMOCs) may view this referenced service information possible sudden loss of cabin pressure
(1) The Manager, Los Angeles Aircraft at the FAA, Transport Airplane Directorate, and injury to occupants.
Certification Office (ACO), FAA, has the 1601 Lind Avenue SW., Renton, WA. For DATES: We must receive comments on
authority to approve AMOCs for this AD, if information on the availability of this this proposed AD by December 5, 2016.
requested using the procedures found in 14 material at the FAA, call 425–227–1221. ADDRESSES: You may send comments by
CFR 39.19. In accordance with 14 CFR 39.19, any of the following methods:
send your request to your principal inspector Issued in Renton, Washington, on
• Federal eRulemaking Portal: Go to
or local Flight Standards District Office, as September 30, 2016.
appropriate. If sending information directly http://www.regulations.gov. Follow the
Michael Kaszycki, instructions for submitting comments.
to the manager of the ACO, send it to the
attention of the person identified in Acting Manager, Transport Airplane • Fax: 202–493–2251.
paragraph (l)(1) of this AD. Information may Directorate, Aircraft Certification Service. • Mail: U.S. Department of
be emailed to: 9-ANM-LAACO-ACO-AMOC- [FR Doc. 2016–24262 Filed 10–19–16; 8:45 am] Transportation, Docket Operations, M–
Requests@faa.gov. BILLING CODE 4910–13–P
30, West Building Ground Floor, Room
(2) Before using any approved AMOC, W12–140, 1200 New Jersey Avenue SE.,
mstockstill on DSK3G9T082PROD with PROPOSALS
notify your appropriate principal inspector, Washington, DC 20590.
or lacking a principal inspector, the manager • Hand Delivery: U.S. Department of
of the local flight standards district office/ Transportation, Docket Operations, M–
certificate holding district office.
(3) An AMOC that provides an acceptable
30, West Building Ground Floor, Room
level of safety may be used for any repair, W12–140, 1200 New Jersey Avenue SE.,
modification, or alteration required by this Washington, DC, between 9 a.m. and 5
AD if it is approved by the Boeing p.m., Monday through Friday, except
Commercial Airplanes Organization Federal holidays.
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Document Created: 2016-10-21 09:59:02
Document Modified: 2016-10-21 09:59:02
| 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 December 5, 2016. | |
| Contact | Wade Sullivan, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6430; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 81 FR 72554 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft and Aviation Safety |
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