82 FR 11140 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 33 (February 21, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 33 (February 21, 2017)
| Page Range | 11140-11144 | |
| FR Document | 2017-02661 |
[Federal Register Volume 82, Number 33 (Tuesday, February 21, 2017)] [Rules and Regulations] [Pages 11140-11144] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-02661] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-6664; Directorate Identifier 2015-NM-177-AD; Amendment 39-18795; AD 2017-03-04] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2012-16-07 for certain The Boeing Company Model 737-500 series airplanes. AD 2012-16- 07 required inspections of the fuselage skin at the chem-milled steps, and repair if necessary. This new AD adds new inspections, permanent repairs of time-limited repairs, related investigative and corrective actions if necessary, and skin panel replacement. This AD was prompted by evaluation by the design approval holder (DAH) that indicates that the fuselage skin is subject to widespread fatigue damage (WFD), and reports of cracking in certain areas of the fuselage skin. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective March 28, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 28, 2017. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600; telephone 562-797-1717; 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- 6664. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.govby searching for and locating Docket No. FAA-2016- 6664; 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800-647- 5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Jennifer Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5264; fax: 562-627-5210; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2012-16-07, Amendment 39-17154 (77 FR 48423, August 14, 2012) (``AD 2012-16-07''). AD 2012-16-07 applied to certain The Boeing Company Model 737-500 series airplanes. The NPRM published in the Federal Register on May 13, 2016 (81 FR 29813) (``the NPRM''). The NPRM was prompted by evaluation by the DAH that indicates that the fuselage skin is subject to WFD, and reports of cracks at the chem- milled steps in the fuselage skin. The NPRM proposed to continue to require inspections of the fuselage skin at the chem-milled steps, and repair if necessary. The NPRM also proposed to add new fuselage skin inspections for cracking, inspections to detect missing or loose fasteners and any disbonding or cracking of bonded doublers, permanent repairs of time-limited repairs, related investigative and corrective actions if necessary, and skin panel replacement. We are issuing this AD to detect and correct cracking on the aft lower lobe fuselage skins, which could result in rapid decompression of the airplane. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Request To Remove Time-Limited Repair Exception From Paragraph (g) of the Proposed AD Boeing requested that we remove the paragraph (h)(5) exception specified in paragraph (g) of the proposed AD. Boeing stated that paragraph (h)(5) of the proposed AD refers to structure with time- limited repairs and is not applicable to paragraph (g) of the proposed AD, which deals with actions on unrepaired structure. We agree with Boeing's request to remove the paragraph (h)(5) reference in paragraph (g) of this AD for the reason provided by Boeing. We have revised paragraph (g) of this AD accordingly. Request To Revise Proposed Compliance Time and Method of Compliance Boeing requested that we revise paragraphs (h)(4), (k)(1), and (k)(2) of the proposed AD to specify that the skin [[Page 11141]] panel replacement condition is ``before'' 53,000 total flight cycles, not ``at or before'' 53,000 total flight cycles; ``and at or after'' 53,000 total flight cycles, not ``before'' for the terminating action in paragraph (k) of the proposed AD. Boeing explained if a skin panel is replaced at 53,000 total flight cycles, no additional safety inspections would be needed due to the limit of validity (LOV). Boeing also requested that we revise the compliance time for skin panel replacement in paragraph (h)(4) of the proposed AD to a time approved by the FAA through the alternative method of compliance (AMOC) process instead of the time specified in the service information. Boeing asserted that a reset of the compliance times is necessary if the panel is replaced before 53,000 total flight cycles. Since a Boeing authorized representative may not approve extensions of compliance times, Boeing pointed out that the AMOC approval for a reset of the compliance times from total flight cycles to flight cycles from when the panel is replaced would have to come from the FAA. We partially agree with Boeing's requests. We agree to revise the compliance time condition to ``before 53,000 total flight cycles'' in paragraphs (h)(4), (k)(1), and (k)(2) of this AD; and to ``at or after 53,000 total flight cycles'' in paragraph (k) of this AD for the terminating action to address Boeing's LOV concerns. We also acknowledge the request to change the compliance time in paragraph (h)(4) of this AD from the applicable time for the next inspection as specified in the service information to a time approved by the FAA. However, we have determined that a change to this AD is not necessary. Operators may always request approval for alternative compliance times using a method approved in accordance with the procedures specified in paragraph (m) of this AD. The compliance time in paragraph (h)(4) of this AD is an appropriate compliance time and provides an acceptable level of safety. It should also provide operators with sufficient information for maintenance planning purposes and allow the inspections to be done during scheduled maintenance intervals for most affected operators. Request To Provide Specific Service Information References Boeing requested that we revise paragraphs (i)(1) and (i)(2) of the proposed AD to provide reference to the specific part of the service information. Boeing stated that paragraph (g) of the proposed AD includes specific service information part references, so this change would make paragraph (i) consistent with the formatting of paragraph (g) of the proposed AD. We do not agree with Boeing's requests. Paragraph (g) of this AD, in part, specifies the specific service information paragraph reference for doing repairs that are terminating action for the repetitive inspections at the repaired locations only. We determined that this reference is needed for clarity. We do not agree that the other references are needed for clarity. We have not changed this AD in this regard. Request To Clarify Post-modification Airworthiness Limitation Inspections Boeing requested that we revise paragraph (j) of the proposed AD to specify that table 3 of paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 737-53-1315, Revision 1, dated June 30, 2015 (``SASB 737-53-1315 R1''), is for post-modification airworthiness limitation inspections at the modified locations. Boeing explained that, since airworthiness limitation inspections are required by maintenance and operational rules, it is unnecessary to mandate them in this AD. We agree with Boeing's request. We have revised paragraph (j) of this AD to clarify that the post-modification inspections are airworthiness limitations that are required by maintenance and operational rules; therefore, these inspections are not required by this AD. Request To Revise Corrective Actions in Paragraph (k) of the Proposed AD Boeing requested that we revise paragraph (k) of the proposed AD, which specifies replacing the applicable skin panels and doing all applicable related investigative and corrective actions. Boeing requested that we remove the phrases ``do all applicable related investigative and corrective actions,'' in accordance with the Accomplishment Instructions of SASB 737-53-1315 R1 and ``do all applicable related investigative and corrective actions before further flight.'' Boeing suggested replacing these phrases with in accordance with ``Part 2: Skin Panel Replacement of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-53-1315, Revision 1, dated June 30, 2015,'' to be similar to the wording in other NPRMs. We disagree with the request to refer to ``Part 2'' of SASB 737-53- 1315 R1. We do not agree that the reference is needed for clarity. We also do not agree with removing the phrase ``all applicable related investigative and corrective actions'' because that phrase indicates there are on-condition actions. The skin panel replacement includes a conditional action that specifies reinstalling a certain lap joint modification. The sentence ``do all applicable related investigative and corrective actions before further flight'' is included to reinforce the compliance time for the on-condition actions. We have not changed this AD in regard to these requests. Request To Revise the NPRM To Address Certain Repaired Areas For airplanes subject to the requirements of paragraph (g) of the proposed AD, Boeing requested that we add a paragraph that specifies that inspections are not required in areas that are spanned by an FAA- approved repair that has met certain conditions. Boeing submitted specific conditions. Boeing stated that its request is to address elimination of inspections for repairs that have been accomplished for damage other than chem-mill cracking. We do not agree with Boeing's request. Paragraph (g) of this AD specifies to do the applicable inspections and related investigative and corrective actions specified in the Accomplishment Instructions of SASB 737-53-1315 R1. This service information already contains the criteria Boeing proposed. Therefore, this criteria does not need to be repeated in this AD. We have not changed this AD in this regard. Effect of Winglets on Accomplishment of the Proposed Actions Aviation Partners Boeing stated that accomplishing the Supplemental Type Certificate (STC) ST01219SE does not affect the actions specified in the NPRM. We concur with the commenter. We have redesignated paragraph (c) of the proposed AD as (c)(1) and added paragraph (c)(2) to this AD to state that installation of STC ST01219SE does not affect the ability to accomplish the actions required by this final rule. Therefore, for airplanes on which STC ST01219SE is installed, a ``change in product'' alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously, and minor editorial changes. We have determined that these minor changes: [[Page 11142]]Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed SASB 737-53-1315 R1. The service information describes procedures for inspection and repair of the fuselage skin panels between station 727 and station 1016, and between stringers S-14 and S- 25; and also describes procedures for skin panel replacement. 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. Costs of Compliance We estimate that this AD affects 33 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Parts Cost on U.S. Action Labor cost cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspections (actions retained 23 work-hours x $85 per $0 $1,955 per $64,515 per from AD 2012-16[dash]07). hour = $1,955 per inspection cycle. inspection cycle. inspection cycle. Inspections (new action)......... Up to 1,515 work-hours x 0 Up to $128,775 per Up to $4,249,575 $85 per hour = $128,775 inspection cycle. per inspection per inspection cycle. cycle. Skin panel replacement (new 688 work-hours x $85 per 96,000 $154,480........... $5,097,840. action). hour = $58,480. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs that would be required based on the results of the inspection. We have no way of determining the number of aircraft that might need these repairs: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Time-limited repair................... 24 work-hours x $85 per hour = (\1\) $2,040. $2,040.. Permanent repair...................... 31 work-hours x $85 per hour = (\1\) 2,635. $2,635.. Permanent repair inspection........... 4 work-hours x $85 per hour = (\1\) 340 per inspection $340 per inspection cycle. cycle. ---------------------------------------------------------------------------------------------------------------- \1\ We have received no definitive data that would enable us to provide parts cost estimates for the on- condition actions specified in this 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 AD will not have federalism implications under Executive Order 13132. This AD will 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 this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under 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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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) 2012-16-07, Amendment 39-17154 (77 FR 48423, August 14, 2012), and adding the following new AD: 2017-03-04 The Boeing Company: Amendment 39-18795; Docket No. FAA- 2016-6664; Directorate Identifier 2015-NM-177-AD. (a) Effective Date This AD is effective March 28, 2017. (b) Affected ADs This AD replaces AD 2012-16-07, Amendment 39-17154 (77 FR 48423, August 14, 2012) (``AD 2012-16-07''). (c) Applicability (1) This AD applies to all The Boeing Company Model 737-500 series airplanes, certificated in any category. (2) Installation of Supplemental Type Certificate (STC) ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/ rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf) [[Page 11143]] does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01219SE is installed, a ``change in product'' alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. (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) that indicates that the fuselage skin is subject to widespread fatigue damage (WFD), and reports of cracks at the chem- milled steps in the fuselage skin. We are issuing this AD to detect and correct cracking on the aft lower lobe fuselage skins, which could result in rapid decompression of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections, Related Investigative and Corrective Actions At the applicable times specified in table 1 of paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 737-53- 1315, Revision 1, dated June 30, 2015 (``SASB 737-53-1315 R1''), except as required by paragraphs (h)(1) and (h)(2) of this AD: Do the applicable inspections to detect cracks in the fuselage skin panels; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of SASB 737-53-1315 R1, except as required by paragraphs (h)(3) and (h)(4) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspections thereafter at the applicable intervals specified SASB 737-53-1315 R1. Accomplishment of a repair in accordance with ``Part 3: Repair'' of the Accomplishment Instructions of SASB 737-53-1315 R1, except as required by paragraph (h)(3) of this AD, is terminating action for the repetitive inspections required by this paragraph at the repaired locations only. (h) Exceptions to SASB 737-53-1315 R1 (1) Where SASB 737-53-1315 R1, specifies compliance times ``after the Revision 1 date of this service bulletin,'' this AD requires compliance within the specified compliance times after the effective date of this AD. (2) The Condition column of table 1 of Paragraph 1.E., ``Compliance,'' of SASB 737-53-1315 R1, refers to airplanes in certain configurations as of the ``issue date of Revision 1 of this service bulletin.'' However, this AD applies to airplanes in the specified configurations ``as of the effective date of this AD.'' (3) Where SASB 737-53-1315 R1, specifies contacting Boeing for repair instructions or work instructions, before further flight, repair or perform the work instructions using a method approved in accordance with the procedures specified in paragraph (m) of this AD, except as required by paragraph (h)(4) of this AD. (4) For airplanes on which an operator has a record that a skin panel was replaced with a production skin panel before 53,000 total flight cycles: At the applicable time for the next inspection as specified in table 1 of paragraph 1.E., ``Compliance,'' SASB 737-53- 1315 R1, except as provided by paragraphs (h)(1) and (h)(2) of this AD: Perform inspections and applicable corrective actions using a method approved in accordance with the procedures specified in paragraph (m) of this AD. (5) The Condition column of table 2 of Paragraph 1.E., ``Compliance,'' of SASB 737-53-1315 R1, refers to airplanes in certain configurations as of the ``issue date of Revision 1 of this service bulletin.'' However, this AD applies to airplanes in the specified configurations regardless of when the time limited repair is installed. (i) Actions for Airplanes With a Time Limited Repair Installed For airplanes with a time limited repair installed as specified in Boeing Special Attention Service Bulletin 737-53-1315, dated July 29, 2011; or SASB 737-53-1315 R1: At the applicable times specified in table 2 of paragraph 1.E., ``Compliance,'' of SASB 737-53-1315 R1, except as provided by paragraphs (h)(1) and (h)(5) of this AD, do the actions specified in paragraphs (i)(1) and (i)(2) of this AD. (1) Do the applicable inspections to detect missing or loose fasteners and any disbonding or cracking of bonded doublers; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of SASB 737-53-1315 R1, except as required by paragraph (h)(3) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspections thereafter at the applicable intervals specified SASB 737-53-1315 R1. (2) Make the time limited repair permanent and do all applicable related investigative and corrective actions in accordance with the Accomplishment Instructions of SASB 737-53-1315 R1, except as required by paragraph (h)(3) of this AD. Do all applicable related investigative and corrective actions before further flight. Accomplishing the permanent repair required by this paragraph terminates the inspections required by paragraph (i)(1) of this AD for the permanently repaired area only. (j) AD Provisions for Part 26 Supplemental Inspections Table 3 of paragraph 1.E., ``Compliance,'' of SASB 737-53-1315 R1, specifies post-modification airworthiness limitation inspections in compliance with 14 CFR 25.571(a)(3) at the modified locations, which support compliance with 14 CFR 121.1109(c)(2) or 129.109(b)(2). As airworthiness limitations, these inspections are required by maintenance and operational rules. It is therefore unnecessary to mandate them in this AD. Deviations from these inspections require FAA approval, but do not require an alternative method of compliance. (k) Skin Panel Replacement At the later of the times specified in paragraphs (k)(1) and (k)(2) of this AD: Replace the applicable skin panels, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of SASB 737-53-1315 R1. Do all applicable related investigative and corrective actions before further flight. Doing the skin panel replacement required by this paragraph terminates the inspection requirements of paragraph (g) of this AD for that skin panel only, provided the skin panel replacement was done with a production skin panel at or after 53,000 total flight cycles. (1) Before 60,000 total flight cycles, but not before 53,000 total flight cycles. (2) Within 6,000 flight cycles after the effective date of this AD, but not before 53,000 total flight cycles. (l) Credit for Previous Actions This paragraph provides credit for the zone 1 actions required by paragraph (g) of this AD, as described in SASB 737-53-1315 R1, if the zone 1, 2, and 3 actions, as described in Boeing Special Attention Service Bulletin 737-53-1315, dated July 29, 2011, were performed before the effective date of this AD using Boeing Special Attention Service Bulletin 737-53-1315, dated July 29, 2011, except as required by paragraph (h)(4) of this AD. Boeing Special Attention Bulletin 737-53-1315, dated July 29, 2011, was incorporated by reference in AD 2012-16-07. (m) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (n)(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 2012-16-07 are approved as AMOCs for the corresponding provisions of paragraph (g) of this AD. (n) Related Information (1) For more information about this AD, contact Jennifer Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification [[Page 11144]] Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5264; fax: 562-627-5210; email: [email protected]. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(3) and (o)(4) of this AD. (o) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Boeing Special Attention Service Bulletin 737-53-1315, Revision 1, dated June 30, 2015. (ii) Reserved. (3) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600; telephone 562-797-1717; Internet https://www.myboeingfleet.com. (4) You may view this 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on January 31, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-02661 Filed 2-17-17; 8:45 am] BILLING CODE 4910-13-P
![11140 Federal Register / Vol. 82, No. 33 / Tuesday, February 21, 2017 / Rules and Regulations
still be done as specified, and the airplane SUMMARY: We are superseding Boulevard, Lakewood, CA 90712–4137;
can be put back in an airworthy condition. Airworthiness Directive (AD) 2012–16– phone: 562–627–5264; fax: 562–627–
(i) Related Information 07 for certain The Boeing Company 5210; email: jennifer.tsakoumakis@
For more information about this AD,
Model 737–500 series airplanes. AD faa.gov.
contact Myra Kuck, Aerospace Engineer, 2012–16–07 required inspections of the SUPPLEMENTARY INFORMATION:
Cabin Safety/Mechanical & Environmental fuselage skin at the chem-milled steps,
Systems branch, ANM–150L, FAA, Los and repair if necessary. This new AD Discussion
Angeles Aircraft Certification Office (ACO), adds new inspections, permanent We issued a notice of proposed
3960 Paramount Boulevard, Lakewood, repairs of time-limited repairs, related rulemaking (NPRM) to amend 14 CFR
California 90712–4137; phone: 562–627– investigative and corrective actions if part 39 to supersede AD 2012–16–07,
5316; fax: 562–627–5210; email: necessary, and skin panel replacement. Amendment 39–17154 (77 FR 48423,
myra.j.kuck@faa.gov. This AD was prompted by evaluation by August 14, 2012) (‘‘AD 2012–16–07’’).
(j) Material Incorporated by Reference the design approval holder (DAH) that AD 2012–16–07 applied to certain The
(1) The Director of the Federal Register indicates that the fuselage skin is Boeing Company Model 737–500 series
approved the incorporation by reference subject to widespread fatigue damage airplanes. The NPRM published in the
(IBR) of the service information listed in this (WFD), and reports of cracking in Federal Register on May 13, 2016 (81
paragraph under 5 U.S.C. 552(a) and 1 CFR certain areas of the fuselage skin. We are FR 29813) (‘‘the NPRM’’). The NPRM
part 51. issuing this AD to address the unsafe was prompted by evaluation by the
(2) You must use this service information condition on these products. DAH that indicates that the fuselage
as applicable to do the actions required by skin is subject to WFD, and reports of
this AD, unless the AD specifies otherwise. DATES: This AD is effective March 28,
(i) Boeing Alert Service Bulletin 757– 2017. cracks at the chem-milled steps in the
27A0154, dated July 22, 2016. The Director of the Federal Register fuselage skin. The NPRM proposed to
(ii) Reserved. approved the incorporation by reference continue to require inspections of the
(3) For Boeing service information of a certain publication listed in this AD fuselage skin at the chem-milled steps,
identified in this AD, contact Boeing as of March 28, 2017. and repair if necessary. The NPRM also
Commercial Airplanes, Attention: ADDRESSES: For service information proposed to add new fuselage skin
Contractual & Data Services (C&DS), 2600 inspections for cracking, inspections to
identified in this final rule, contact
Westminster Blvd., MC 110–SK57, Seal detect missing or loose fasteners and
Beach, CA 90740–5600; telephone 562–797– Boeing Commercial Airplanes,
Attention: Contractual & Data Services any disbonding or cracking of bonded
1717; Internet https:// doublers, permanent repairs of time-
www.myboeingfleet.com. (C&DS), 2600 Westminster Blvd., MC
(4) You may view this referenced service 110–SK57, Seal Beach, CA 90740–5600; limited repairs, related investigative and
information at the FAA, Transport Airplane telephone 562–797–1717; Internet corrective actions if necessary, and skin
Directorate, 1601 Lind Avenue SW., Renton, https://www.myboeingfleet.com. You panel replacement. We are issuing this
WA. For information on the availability of may view this referenced service AD to detect and correct cracking on the
this material at the FAA, call 425–227–1221. information at the FAA, Transport aft lower lobe fuselage skins, which
(5) You may view this service information could result in rapid decompression of
Airplane Directorate, 1601 Lind Avenue
that is incorporated by reference at the the airplane.
National Archives and Records SW., Renton, WA. For information on
Administration (NARA). For information on the availability of this material at the Comments
the availability of this material at NARA, call FAA, call 425–227–1221. It is also
We gave the public the opportunity to
202–741–6030, or go to: http:// available on the Internet at http://
participate in developing this AD. The
www.archives.gov/federal-register/cfr/ibr- www.regulations.gov by searching for
locations.html.
following presents the comments
and locating Docket No. FAA–2016–
received on the NPRM and the FAA’s
Issued in Renton, Washington, on January 6664.
response to each comment.
23, 2017.
Examining the AD Docket Request To Remove Time-Limited
Dionne Palermo,
Acting Manager, Transport Airplane
You may examine the AD docket on Repair Exception From Paragraph (g) of
Directorate, Aircraft Certification Service. the Internet at http:// the Proposed AD
[FR Doc. 2017–03030 Filed 2–17–17; 8:45 am]
www.regulations.govby searching for Boeing requested that we remove the
and locating Docket No. FAA–2016– paragraph (h)(5) exception specified in
BILLING CODE 4910–13–P
6664; or in person at the Docket paragraph (g) of the proposed AD.
Management Facility between 9 a.m. Boeing stated that paragraph (h)(5) of
DEPARTMENT OF TRANSPORTATION and 5 p.m., Monday through Friday, the proposed AD refers to structure with
except Federal holidays. The AD docket time-limited repairs and is not
Federal Aviation Administration contains this AD, the regulatory applicable to paragraph (g) of the
evaluation, any comments received, and proposed AD, which deals with actions
14 CFR Part 39 other information. The address for the on unrepaired structure.
Docket Office (phone: 800–647–5527) is We agree with Boeing’s request to
[Docket No. FAA–2016–6664; Directorate Docket Management Facility, U.S.
Identifier 2015–NM–177–AD; Amendment remove the paragraph (h)(5) reference in
Department of Transportation, Docket paragraph (g) of this AD for the reason
39–18795; AD 2017–03–04]
Operations, M–30, West Building provided by Boeing. We have revised
RIN 2120–AA64 Ground Floor, Room W12–140, 1200 paragraph (g) of this AD accordingly.
New Jersey Avenue SE., Washington,
rmajette on DSK2TPTVN1PROD with RULES
Airworthiness Directives; The Boeing DC 20590. Request To Revise Proposed
Company Airplanes FOR FURTHER INFORMATION CONTACT: Compliance Time and Method of
Jennifer Tsakoumakis, Aerospace Compliance
AGENCY: Federal Aviation
Administration (FAA), DOT. Engineer, Airframe Branch, ANM–120L, Boeing requested that we revise
FAA, Los Angeles Aircraft Certification paragraphs (h)(4), (k)(1), and (k)(2) of
ACTION: Final rule.
Office (ACO), 3960 Paramount the proposed AD to specify that the skin
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![11142 Federal Register / Vol. 82, No. 33 / Tuesday, February 21, 2017 / Rules and Regulations
• Are consistent with the intent that Related Service Information Under 1 reasonably available because the
was proposed in the NPRM for CFR Part 51 interested parties have access to it
correcting the unsafe condition; and through their normal course of business
We reviewed SASB 737–53–1315 R1. or by the means identified in the
• Do not add any additional burden The service information describes
upon the public than was already ADDRESSES section.
procedures for inspection and repair of
proposed in the NPRM. the fuselage skin panels between station Costs of Compliance
We also determined that these 727 and station 1016, and between We estimate that this AD affects 33
changes will not increase the economic stringers S–14 and S–25; and also airplanes of U.S. registry.
burden on any operator or increase the describes procedures for skin panel We estimate the following costs to
scope of this AD. replacement. This service information is comply with this AD:
ESTIMATED COSTS
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
Inspections (actions retained from AD 23 work-hours × $85 per hour = $1,955 $0 $1,955 per inspec- $64,515 per inspection
2012–16-07). per inspection cycle. tion cycle. cycle.
Inspections (new action) ......................... Up to 1,515 work-hours × $85 per hour 0 Up to $128,775 per Up to $4,249,575 per in-
= $128,775 per inspection cycle. inspection cycle. spection cycle.
Skin panel replacement (new action) ..... 688 work-hours × $85 per hour = 96,000 $154,480 ............... $5,097,840.
$58,480.
We estimate the following costs to do required based on the results of the determining the number of aircraft that
any necessary repairs that would be inspection. We have no way of might need these repairs:
ON-CONDITION COSTS
Action Labor cost Parts cost Cost per product
Time-limited repair ................... 24 work-hours × $85 per hour = $2,040. ................................. (1 ) $2,040.
Permanent repair ..................... 31 work-hours × $85 per hour = $2,635. ................................. (1 ) 2,635.
Permanent repair inspection ... 4 work-hours × $85 per hour = $340 per inspection cycle ...... ( 1) 340 per inspection cycle.
1 We have received no definitive data that would enable us to provide parts cost estimates for the on-condition actions specified in this AD.
Authority for This Rulemaking or on the distribution of power and Authority: 49 U.S.C. 106(g), 40113, 44701.
Title 49 of the United States Code responsibilities among the various
§ 39.13 [Amended]
specifies the FAA’s authority to issue levels of government.
rules on aviation safety. Subtitle I, For the reasons discussed above, I ■ 2. The FAA amends § 39.13 by
Section 106, describes the authority of certify that this AD: removing Airworthiness Directive (AD)
(1) Is not a ‘‘significant regulatory 2012–16–07, Amendment 39–17154 (77
the FAA Administrator. Subtitle VII,
action’’ under Executive Order 12866,
Aviation Programs, describes in more (2) Is not a ‘‘significant rule’’ under FR 48423, August 14, 2012), and adding
detail the scope of the Agency’s DOT Regulatory Policies and Procedures the following new AD:
authority. (44 FR 11034, February 26, 1979), 2017–03–04 The Boeing Company:
We are issuing this rulemaking under (3) Will not affect intrastate aviation Amendment 39–18795; Docket No.
the authority described in Subtitle VII, in Alaska, and FAA–2016–6664; Directorate Identifier
Part A, Subpart III, Section 44701, (4) Will not have a significant 2015–NM–177–AD.
‘‘General requirements.’’ Under that economic impact, positive or negative,
section, Congress charges the FAA with (a) Effective Date
on a substantial number of small entities
promoting safe flight of civil aircraft in under the criteria of the Regulatory This AD is effective March 28, 2017.
air commerce by prescribing regulations Flexibility Act.
for practices, methods, and procedures (b) Affected ADs
the Administrator finds necessary for List of Subjects in 14 CFR Part 39 This AD replaces AD 2012–16–07,
safety in air commerce. This regulation Air transportation, Aircraft, Aviation Amendment 39–17154 (77 FR 48423, August
is within the scope of that authority safety, Incorporation by reference, 14, 2012) (‘‘AD 2012–16–07’’).
because it addresses an unsafe condition Safety. (c) Applicability
that is likely to exist or develop on
Adoption of the Amendment (1) This AD applies to all The Boeing
products identified in this rulemaking
Company Model 737–500 series airplanes,
action. Accordingly, under the authority
certificated in any category.
delegated to me by the Administrator,
Regulatory Findings (2) Installation of Supplemental Type
the FAA amends 14 CFR part 39 as
rmajette on DSK2TPTVN1PROD with RULES
We have determined that this AD will Certificate (STC) ST01219SE (http://rgl.faa.
follows: gov/Regulatory_and_Guidance_Library/
not have federalism implications under
rgstc.nsf/0/ebd1cec7b301293e86257cb
Executive Order 13132. This AD will PART 39—AIRWORTHINESS
30045557a/$FILE/ST01219SE.pdf)
not have a substantial direct effect on DIRECTIVES
the States, on the relationship between
the national government and the States, ■ 1. The authority citation for part 39
continues to read as follows:
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![11144 Federal Register / Vol. 82, No. 33 / Tuesday, February 21, 2017 / Rules and Regulations
Office (ACO), 3960 Paramount Boulevard, CL–600–2B19 (Regional Jet Series 100 & SUPPLEMENTARY INFORMATION:
Lakewood, CA 90712–4137; phone: 562–627– 440) airplanes. AD 2014–23–06 required
5264; fax: 562–627–5210; email: modifying the main landing gear (MLG) Discussion
jennifer.tsakoumakis@faa.gov.
by installing a new bracket on the left We issued a notice of proposed
(2) Service information identified in this
AD that is not incorporated by reference is and right lower aft-wing planks. This rulemaking (NPRM) to amend 14 CFR
available at the addresses specified in new AD requires modification of the part 39 to supersede AD 2014–23–06,
paragraphs (o)(3) and (o)(4) of this AD. MLG with an improved design. This AD Amendment 39–18022 (79 FR 69037,
was prompted by a report indicating November 20, 2014) (‘‘AD 2014–23–
(o) Material Incorporated by Reference
that inboard and outboard hydraulic 06’’). AD 2014–23–06 applied to certain
(1) The Director of the Federal Register lines of the brakes were found
approved the incorporation by reference Bombardier, Inc. Model CL–600–2B19
connected to the incorrect ports on the
(IBR) of the service information listed in this (Regional Jet Series 100 & 440)
paragraph under 5 U.S.C. 552(a) and 1 CFR swivel assembly of the MLG. We are
airplanes. The NPRM published in the
part 51. issuing this AD to address the unsafe
condition on these products. Federal Register on October 24, 2016
(2) You must use this service information
as applicable to do the actions required by
(81 FR 73042). The NPRM was
DATES: This AD is effective March 28,
this AD, unless the AD specifies otherwise. prompted by a report indicating that
2017.
(i) Boeing Special Attention Service The Director of the Federal Register inboard and outboard hydraulic lines of
Bulletin 737–53–1315, Revision 1, dated June approved the incorporation by reference the brakes were found connected to the
30, 2015. incorrect ports on the swivel assembly
(ii) Reserved.
of a certain publication listed in this AD
as of March 28, 2017. of the MLG. The NPRM proposed to
(3) For Boeing service information require modification of the MLG with an
identified in this AD, contact Boeing ADDRESSES: For service information
Commercial Airplanes, Attention: identified in this final rule, contact improved design. We are issuing this
Contractual & Data Services (C&DS), 2600 Bombardier, Inc., 400 Côte-Vertu Road AD to prevent incorrect installation of
Westminster Blvd., MC 110–SK57, Seal West, Dorval, Québec H4S 1Y9, Canada; the brake hydraulic lines, which could
Beach, CA 90740–5600; telephone 562–797– Widebody Customer Response Center cause the brakes and the anti-skid
1717; Internet https:// system to operate incorrectly, and result
www.myboeingfleet.com. North America toll-free telephone 1–
866–538–1247 or direct-dial telephone in catastrophic failure of the airplane
(4) You may view this service information
1–514–855–2999; fax 514–855–7401; during a high-speed rejected takeoff.
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For email ac.yul@aero.bombardier.com; Transport Canada Civil Aviation
information on the availability of this Internet http://www.bombardier.com. (TCCA), which is the aviation authority
material at the FAA, call 425–227–1221. You may view this referenced service for Canada, has issued Canadian
(5) You may view this service information information at the FAA, Transport Airworthiness Directive CF–2014–10R1,
that is incorporated by reference at the Airplane Directorate, 1601 Lind Avenue dated May 4, 2016 (referred to after this
National Archives and Records
SW., Renton, WA. For information on as the Mandatory Continuing
Administration (NARA). For information on
the availability of this material at NARA, call the availability of this material at the Airworthiness Information, or ‘‘the
202–741–6030, or go to: http:// FAA, call 425–227–1221. It is also MCAI’’), to correct an unsafe condition
www.archives.gov/federal-register/cfr/ibr- available on the Internet at http:// for certain Bombardier, Inc. Model CL–
locations.html. www.regulations.gov by searching for 600–2B19 (Regional Jet Series 100 &
Issued in Renton, Washington, on January and locating Docket No. FAA–2016– 440) airplanes. The MCAI states:
31, 2017. 9190.
Cases of inboard and outboard hydraulic
Michael Kaszycki, Examining the AD Docket brake lines connected to the incorrect port of
Acting Manager, Transport Airplane You may examine the AD docket on the swivel assembly on the main landing gear
Directorate, Aircraft Certification Service. were found in service. Cross-connected brake
the Internet at http://
[FR Doc. 2017–02661 Filed 2–17–17; 8:45 am]
www.regulations.gov by searching for hydraulic lines can cause the brakes and/or
BILLING CODE 4910–13–P and locating Docket No. FAA–2016– the anti-skid system to operate incorrectly.
9190; or in person at the Docket During a high speed rejected take-off,
Management Facility between 9 a.m. inability for the brakes to operate correctly
DEPARTMENT OF TRANSPORTATION and 5 p.m., Monday through Friday, could be catastrophic. The original issue of
except Federal holidays. The AD docket this [Canadian] AD mandated the
Federal Aviation Administration modification to prevent inadvertent cross-
contains this AD, the regulatory
connection of the inboard and outboard
14 CFR Part 39 evaluation, any comments received, and
hydraulic brake lines.
other information. The address for the
[Docket No. FAA–2016–9190; Directorate Following the initial release of this
Docket Office (telephone 800–647–5527)
Identifier 2016–NM–087–AD; Amendment [Canadian] AD, operators reported that the
is Docket Management Facility, U.S.
39–18797; AD 2017–04–02] modifications required by Bombardier
Department of Transportation, Docket
Service Bulletin (SB) 601R–32–110 Rev. NC.,
RIN 2120–AA64 Operations, M–30, West Building dated 19 December 2013, still have a
Ground Floor, Room W12–140, 1200 potential for incorrect connection.
Airworthiness Directives; Bombardier, New Jersey Avenue SE., Washington, Subsequently, the SB has been revised to
Inc. Airplanes DC 20590. introduce a modified design and this
AGENCY: Federal Aviation FOR FURTHER INFORMATION CONTACT: [Canadian] AD revision is issued to mandate
Fabio Buttitta, Aerospace Engineer,
rmajette on DSK2TPTVN1PROD with RULES
Administration (FAA), Department of the incorporation of the modified design.
Transportation (DOT). Airframe and Mechanical Systems
ACTION: Final rule. Branch, ANE–171, FAA, New York You may examine the MCAI in the AD
Aircraft Certification Office, 1600 docket on the Internet at http://
SUMMARY: We are superseding Stewart Avenue, Suite 410, Westbury, www.regulations.gov by searching for
Airworthiness Directive (AD) 2014–23– NY 11590; telephone 516–228–7303; fax and locating Docket No. FAA–2016–
06 for certain Bombardier, Inc. Model 516–794–5531. 9190.
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Document Created: 2018-02-01 15:04:16
Document Modified: 2018-02-01 15:04:16
| 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 | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective March 28, 2017. | |
| Contact | Jennifer Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5264; fax: 562-627-5210; email: [email protected] | |
| FR Citation | 82 FR 11140 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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