82 FR 20450 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 83 (May 2, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 83 (May 2, 2017)
| Page Range | 20450-20453 | |
| FR Document | 2017-08831 |
[Federal Register Volume 82, Number 83 (Tuesday, May 2, 2017)] [Proposed Rules] [Pages 20450-20453] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-08831] ======================================================================== Proposed Rules Federal Register ________________________________________________________________________ This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. ======================================================================== Federal Register / Vol. 82, No. 83 / Tuesday, May 2, 2017 / Proposed Rules [[Page 20450]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0332; Directorate Identifier 2016-NM-164-AD] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 737-200, -200C, -300, -400, and -500 series airplanes. This proposed AD was prompted by reports of skin doublers that disbonded from their skin panels. This proposed AD would require repetitive inspections of fuselage skin panels, and applicable on-condition actions. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by June 16, 2017. 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: 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-2017-0332. 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-2017- 0332; 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: wade.sullivan@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2017-0332; Directorate Identifier 2016-NM-164-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, widespread fatigue damage (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 [[Page 20451]] LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. This approach allows for an implementation strategy that provides flexibility to DAHs in determining the timing of service information development (with FAA approval), while providing operators with certainty regarding the LOV applicable to their airplanes. We have received reports of skin doublers that disbonded from their skin panels on certain Model 737 series airplanes. Bonded skin doublers are part of the back-up structure for the skin panels and are installed from body station (BS) 259.50 through BS 1016 on both sides of the airplane. The airplane manufacturer has attributed the root cause of disbonded skin doublers to improper processing during the phosphoric acid anodization phase of skin panel manufacturing. Disbonding of the skin panel reduces the skin panel's capability to resist cracks in the countersunk holes of fastened joints and can lead to fuselage skin cracking and multi-site damage, predominantly in the lap splices and butt joints. Fuselage skin cracking resulting from disbonded skin panels, if not detected and corrected, could result in rapid decompression and loss of structural integrity of the airplane. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 737-53A1349, dated August 23, 2016. The service information describes procedures for repetitive inspections of fuselage skin panels for cracking, corrosion, and existing disbond repairs; and applicable on-condition actions. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. FAA's Determination We are proposing this AD because we evaluated all the relevant information and determined that the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require accomplishment of the actions identified as ``RC'' (required for compliance) in the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1349, dated August 23, 2016, described previously, except for differences between this proposed AD and the service information that are identified in the regulatory text of this proposed AD. 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-2017-0332. Related Rulemaking AD 2003-14-06, Amendment 39-13225 (68 FR 40759, July 9, 2003; corrected July 21, 2003 (68 FR 42956)) (``AD 2003-14-06''), applies to certain Model 737-200, -200C, -300, -400, and -500 series airplanes. AD 2003-14-06 requires repetitive inspections for cracking of certain lap splices, and corrective action if necessary. Accomplishment of initial inspections specified in this proposed AD would terminate all requirements of AD 2003-14-06. Explanation of Certain Compliance Times The compliance time to replace skin panels, which is one of the actions identified as ``RC'' for certain conditions to address WFD in this NPRM, was established to ensure that discrepant structure is replaced before WFD develops in airplanes. Standard inspection techniques cannot be relied on to detect WFD before it becomes a hazard to flight. We will not grant any extensions of the compliance time to complete any AD-mandated service bulletin related to WFD without extensive new data that would substantiate and clearly warrant such an extension. Table 9 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1349, dated August 23, 2016, does not provide a grace period for airplanes that have exceeded a certain compliance time. Paragraph (h)(3) of this proposed AD adds a grace period of 4,500 flight cycles. We have coordinated this grace period with Boeing. Costs of Compliance We estimate that this proposed AD affects 169 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 ---------------------------------------------------------------------------------------------------------------- External general visual and 180 work-hours x $0 $15,300 per $2,585,700 per detailed inspections. $85 per hour = inspection cycle. inspection cycle. $15,300 per inspection cycle. External high frequency bond test 450 work hours x 0 $38,250 inspection $6,464,250 per inspection. $85 per hour = cycle. inspection cycle. $38,250 per inspection cycle. Ultrasonic disbond inspection and 630 work-hours x 0 $53,550 per $9,049,950 per internal detailed skin $85 per hour = inspection cycle. inspection cycle. inspection. $53,550 per inspection cycle. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary on-condition actions that would be required based on the results of the proposed inspections. We have no way of determining the number of aircraft that might need these on-condition actions: On-Condition Costs per Skin Panel ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- On-condition inspections.......... Up to 25 work-hours x $85 $0................... Up to $2,125. per hour = $2,125. Repairs........................... Up to 68 work-hours x $85 Up to $100........... Up to $5,880. per hour = $5,780. [[Page 20452]] Skin panel replacement............ 304 work-hours x $85 per $95,000.............. $120,840. hour = $25,840. ---------------------------------------------------------------------------------------------------------------- Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): The Boeing Company: Docket No. FAA-2017-0332; Directorate Identifier 2016-NM-164-AD. (a) Comments Due Date We must receive comments by June 16, 2017. (b) Affected ADs This AD affects AD 2003-14-06, Amendment 39-13225 (68 FR 40759, July 9, 2003; corrected July 21, 2003 (68 FR 42956)) (``AD 2003-14- 06''). (c) Applicability This AD applies to The Boeing Company Model 737-200, -200C, - 300, -400, and -500 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 737-53A1349, dated August 23, 2016. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by reports of skin doublers that disbonded from their skin panels. We are issuing this AD to detect and correct disbonded skin panels, which could result in fuselage skin cracking, rapid decompression, and loss of structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Actions Required for Compliance Except as required by paragraph (h) of this AD: Do all applicable actions identified as required for compliance (``RC'') in, and in accordance with, the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1349, dated August 23, 2016. Do the actions at the applicable times specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1349, dated August 23, 2016. (h) Exceptions to Service Information Specifications (1) Where Boeing Alert Service Bulletin 737-53A1349, dated August 23, 2016, uses the phrase ``after the original issue of this service bulletin,'' for purposes of determining compliance with the requirements of this AD, the phrase ``after the effective date of this AD'' must be used. (2) Where Boeing Alert Service Bulletin 737-53A1349, dated August 23, 2016, specifies contacting Boeing for instructions, and specifies that action as ``RC'' (Required for Compliance): This AD requires using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (3) For replaced skin panels identified in table 9 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1349, dated August 23, 2016, on which the one-time internal inspection specified in Service Bulletin 737-53-1179, Revision 2, dated October 25, 2001, has not been done: The compliance time for accomplishment of the actions specified in Part 8 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1349, dated August 23, 2016, is at the latest of the times specified in paragraphs (h)(3)(i), (h)(3)(ii), and (h)(3)(iii) of this AD. (i) Within 50,000 flight cycles after the skin panel replacement. (ii) Within 20,000 flight cycles after July 14, 2003 (the effective date of AD 2003-14-16). (iii) Within 4,500 flight cycles after the effective date of this AD. (i) Terminating Action for This AD Accomplishment of any skin panel replacement, as specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1349, dated August 23, 2016, except as required by paragraph (h)(2) of this AD, terminates the repetitive inspections required by paragraph (g) of this AD at the replaced skin panel only. (j) Terminating Action for AD 2003-14-06 Accomplishment of the initial inspections required by paragraph (g) of this AD terminates all requirements of AD 2003-14-06. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles Aircraft Certification Office, 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 [[Page 20453]] be emailed to: 9-ANM-LAACO-AMOC-Requests@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) Except as required by paragraph (h)(2) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (k)(4)(i) and (k)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or substep is labeled ``RC Exempt,'' then the RC requirement is removed from that step or substep. 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: wade.sullivan@faa.gov. (2) For information about AMOCs, contact Jennifer Tsakoumakis, 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: jennifer.tsakoumakis@faa.gov. (3) For 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. 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 April 24, 2017. Paul Bernado, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-08831 Filed 5-1-17; 8:45 am] BILLING CODE 4910-13-P
![20450
Proposed Rules Federal Register
Vol. 82, No. 83
Tuesday, May 2, 2017
This section of the FEDERAL REGISTER Blvd., MC 110–SK57, Seal Beach, CA will also post a report summarizing each
contains notices to the public of the proposed 90740–5600; telephone 562–797–1717; substantive verbal contact we receive
issuance of rules and regulations. The Internet https:// about this proposed AD.
purpose of these notices is to give interested www.myboeingfleet.com. You may view
persons an opportunity to participate in the Discussion
this referenced service information at
rule making prior to the adoption of the final Fatigue damage can occur locally, in
rules.
the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., small areas or structural design details,
Renton, WA. For information on the or globally, in widespread areas.
availability of this material at the FAA, Multiple-site damage is widespread
DEPARTMENT OF TRANSPORTATION
call 425–227–1221. It is also available damage that occurs in a large structural
Federal Aviation Administration on the Internet at http:// element such as a single rivet line of a
www.regulations.gov by searching for lap splice joining two large skin panels.
14 CFR Part 39 and locating Docket No. FAA–2017– Widespread damage can also occur in
0332. multiple elements such as adjacent
[Docket No. FAA–2017–0332; Directorate frames or stringers. Multiple-site
Identifier 2016–NM–164–AD] Examining the AD Docket damage and multiple-element damage
RIN 2120–AA64 You may examine the AD docket on cracks are typically too small initially to
the Internet at http:// be reliably detected with normal
Airworthiness Directives; The Boeing www.regulations.gov by searching for inspection methods. Without
Company Airplanes and locating Docket No. FAA–2017– intervention, these cracks will grow,
0332; or in person at the Docket and eventually compromise the
AGENCY: Federal Aviation Management Facility between 9 a.m. structural integrity of the airplane. This
Administration (FAA), DOT. and 5 p.m., Monday through Friday, condition is known as widespread
ACTION: Notice of proposed rulemaking except Federal holidays. The AD docket fatigue damage. It is associated with
(NPRM). contains this proposed AD, the general degradation of large areas of
regulatory evaluation, any comments structure with similar structural details
SUMMARY: We propose to adopt a new and stress levels. As an airplane ages,
received, and other information. The
airworthiness directive (AD) for certain widespread fatigue damage (WFD) will
street address for the Docket Office
The Boeing Company Model 737–200, likely occur, and will certainly occur if
(phone: 800–647–5527) is in the
–200C, –300, –400, and –500 series the airplane is operated long enough
ADDRESSES section. Comments will be
airplanes. This proposed AD was without any intervention.
available in the AD docket shortly after
prompted by reports of skin doublers The FAA’s WFD final rule (75 FR
receipt.
that disbonded from their skin panels. 69746, November 15, 2010) became
FOR FURTHER INFORMATION CONTACT:
This proposed AD would require effective on January 14, 2011. The WFD
repetitive inspections of fuselage skin Wade Sullivan, Aerospace Engineer, rule requires certain actions to prevent
panels, and applicable on-condition Airframe Branch, ANM–120S, FAA, structural failure due to WFD
actions. We are proposing this AD to Seattle Aircraft Certification Office throughout the operational life of
address the unsafe condition on these (ACO), 1601 Lind Avenue SW., Renton, certain existing transport category
products. WA 98057–3356; phone: 425–917–6430; airplanes and all of these airplanes that
fax: 425–917–6590; email: will be certificated in the future. For
DATES: We must receive comments on wade.sullivan@faa.gov.
this proposed AD by June 16, 2017. existing and future airplanes subject to
SUPPLEMENTARY INFORMATION: the WFD rule, the rule requires that
ADDRESSES: You may send comments, DAHs establish a limit of validity (LOV)
using the procedures found in 14 CFR Comments Invited
of the engineering data that support the
11.43 and 11.45, by any of the following We invite you to send any written structural maintenance program.
methods: relevant data, views, or arguments about Operators affected by the WFD rule may
• Federal eRulemaking Portal: Go to this proposal. Send your comments to not fly an airplane beyond its LOV,
http://www.regulations.gov. Follow the an address listed under the ADDRESSES unless an extended LOV is approved.
instructions for submitting comments. section. Include ‘‘Docket No. FAA– The WFD rule (75 FR 69746,
• Fax: 202–493–2251. 2017–0332; Directorate Identifier 2016– November 15, 2010) does not require
• Mail: U.S. Department of NM–164–AD’’ at the beginning of your identifying and developing maintenance
Transportation, Docket Operations, M– comments. We specifically invite actions if the DAHs can show that such
30, West Building Ground Floor, Room comments on the overall regulatory, actions are not necessary to prevent
W12–140, 1200 New Jersey Avenue SE., economic, environmental, and energy WFD before the airplane reaches the
Washington, DC 20590. aspects of this proposed AD. We will LOV. Many LOVs, however, do depend
jstallworth on DSK7TPTVN1PROD with PROPOSALS
• Hand Delivery: Deliver to Mail consider all comments received by the on accomplishment of future
address above between 9 a.m. and 5 closing date and may amend this maintenance actions. As stated in the
p.m., Monday through Friday, except proposed AD because of those WFD rule, any maintenance actions
Federal holidays. comments. necessary to reach the LOV will be
For service information identified in We will post all comments we mandated by airworthiness directives
this NPRM, contact Boeing Commercial receive, without change, to http:// through separate rulemaking actions.
Airplanes, Attention: Contractual & Data www.regulations.gov, including any In the context of WFD, this action is
Services (C&DS), 2600 Westminster personal information you provide. We necessary to enable DAHs to propose
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![20452 Federal Register / Vol. 82, No. 83 / Tuesday, May 2, 2017 / Proposed Rules
ON-CONDITION COSTS PER SKIN PANEL—Continued
Cost per
Action Labor cost Parts cost product
Skin panel replacement ........................................ 304 work-hours × $85 per hour = $25,840 ........ $95,000 ........................ $120,840.
Authority for This Rulemaking the FAA proposes to amend 14 CFR part (h) Exceptions to Service Information
39 as follows: Specifications
Title 49 of the United States Code
(1) Where Boeing Alert Service Bulletin
specifies the FAA’s authority to issue PART 39—AIRWORTHINESS 737–53A1349, dated August 23, 2016, uses
rules on aviation safety. Subtitle I, DIRECTIVES the phrase ‘‘after the original issue of this
section 106, describes the authority of service bulletin,’’ for purposes of determining
the FAA Administrator. Subtitle VII: compliance with the requirements of this AD,
■ 1. The authority citation for part 39
Aviation Programs, describes in more the phrase ‘‘after the effective date of this
continues to read as follows: AD’’ must be used.
detail the scope of the Agency’s
authority. Authority: 49 U.S.C. 106(g), 40113, 44701. (2) Where Boeing Alert Service Bulletin
737–53A1349, dated August 23, 2016,
We are issuing this rulemaking under
§ 39.13 [Amended] specifies contacting Boeing for instructions,
the authority described in Subtitle VII, and specifies that action as ‘‘RC’’ (Required
Part A, Subpart III, Section 44701: ■ 2. The FAA amends § 39.13 by adding for Compliance): This AD requires using a
‘‘General requirements.’’ Under that the following new airworthiness method approved in accordance with the
section, Congress charges the FAA with directive (AD): procedures specified in paragraph (k) of this
promoting safe flight of civil aircraft in AD.
The Boeing Company: Docket No. FAA–
air commerce by prescribing regulations (3) For replaced skin panels identified in
2017–0332; Directorate Identifier 2016– table 9 of paragraph 1.E., ‘‘Compliance,’’ of
for practices, methods, and procedures NM–164–AD. Boeing Alert Service Bulletin 737–53A1349,
the Administrator finds necessary for dated August 23, 2016, on which the one-
(a) Comments Due Date
safety in air commerce. This regulation time internal inspection specified in Service
is within the scope of that authority We must receive comments by June 16, Bulletin 737–53–1179, Revision 2, dated
because it addresses an unsafe condition 2017. October 25, 2001, has not been done: The
that is likely to exist or develop on (b) Affected ADs compliance time for accomplishment of the
products identified in this rulemaking actions specified in Part 8 of the
This AD affects AD 2003–14–06, Accomplishment Instructions of Boeing Alert
action. Amendment 39–13225 (68 FR 40759, July 9, Service Bulletin 737–53A1349, dated August
Regulatory Findings 2003; corrected July 21, 2003 (68 FR 42956)) 23, 2016, is at the latest of the times specified
(‘‘AD 2003–14–06’’). in paragraphs (h)(3)(i), (h)(3)(ii), and
We determined that this proposed AD (h)(3)(iii) of this AD.
would not have federalism implications (c) Applicability
(i) Within 50,000 flight cycles after the skin
under Executive Order 13132. This This AD applies to The Boeing Company panel replacement.
proposed AD would not have a Model 737–200, –200C, –300, –400, and –500 (ii) Within 20,000 flight cycles after July
substantial direct effect on the States, on series airplanes, certificated in any category, 14, 2003 (the effective date of AD 2003–14–
the relationship between the national as identified in Boeing Alert Service Bulletin 16).
Government and the States, or on the 737–53A1349, dated August 23, 2016. (iii) Within 4,500 flight cycles after the
effective date of this AD.
distribution of power and (d) Subject
responsibilities among the various Air Transport Association (ATA) of (i) Terminating Action for This AD
levels of government. America Code 53, Fuselage. Accomplishment of any skin panel
For the reasons discussed above, I replacement, as specified in the
certify this proposed regulation: (e) Unsafe Condition Accomplishment Instructions of Boeing Alert
(1) Is not a ‘‘significant regulatory This AD was prompted by reports of skin Service Bulletin 737–53A1349, dated August
action’’ under Executive Order 12866, doublers that disbonded from their skin 23, 2016, except as required by paragraph
panels. We are issuing this AD to detect and (h)(2) of this AD, terminates the repetitive
(2) Is not a ‘‘significant rule’’ under inspections required by paragraph (g) of this
the DOT Regulatory Policies and correct disbonded skin panels, which could
result in fuselage skin cracking, rapid AD at the replaced skin panel only.
Procedures (44 FR 11034, February 26,
decompression, and loss of structural (j) Terminating Action for AD 2003–14–06
1979), integrity of the airplane.
(3) Will not affect intrastate aviation Accomplishment of the initial inspections
in Alaska, and (f) Compliance required by paragraph (g) of this AD
terminates all requirements of AD 2003–14–
(4) Will not have a significant Comply with this AD within the
06.
economic impact, positive or negative, compliance times specified, unless already
on a substantial number of small entities done. (k) Alternative Methods of Compliance
under the criteria of the Regulatory (AMOCs)
(g) Actions Required for Compliance
Flexibility Act. (1) The Manager, Los Angeles Aircraft
Except as required by paragraph (h) of this Certification Office, FAA, has the authority to
jstallworth on DSK7TPTVN1PROD with PROPOSALS
List of Subjects in 14 CFR Part 39 AD: Do all applicable actions identified as approve AMOCs for this AD, if requested
required for compliance (‘‘RC’’) in, and in using the procedures found in 14 CFR 39.19.
Air transportation, Aircraft, Aviation accordance with, the Accomplishment In accordance with 14 CFR 39.19, send your
safety, Incorporation by reference, Instructions of Boeing Alert Service Bulletin request to your principal inspector or local
Safety. 737–53A1349, dated August 23, 2016. Do the Flight Standards District Office, as
The Proposed Amendment actions at the applicable times specified in appropriate. If sending information directly
paragraph 1.E., ‘‘Compliance,’’ of Boeing to the manager of the ACO, send it to the
Accordingly, under the authority Alert Service Bulletin 737–53A1349, dated attention of the person identified in
delegated to me by the Administrator, August 23, 2016. paragraph (l)(1) of this AD. Information may
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![Federal Register / Vol. 82, No. 83 / Tuesday, May 2, 2017 / Proposed Rules 20453
be emailed to: 9-ANM-LAACO-AMOC- Issued in Renton, Washington, on April 24, Directorate, 1601 Lind Avenue SW.,
Requests@faa.gov. 2017. Renton, WA. For information on the
(2) Before using any approved AMOC, Paul Bernado, availability of this material at the FAA,
notify your appropriate principal inspector, Acting Manager, Transport Airplane call 425–227–1221.
or lacking a principal inspector, the manager Directorate, Aircraft Certification Service.
of the local flight standards district office/ Examining the AD Docket
[FR Doc. 2017–08831 Filed 5–1–17; 8:45 am]
certificate holding district office. BILLING CODE 4910–13–P You may examine the AD docket on
(3) An AMOC that provides an acceptable the Internet at http://
level of safety may be used for any repair, www.regulations.gov by searching for
modification, or alteration required by this DEPARTMENT OF TRANSPORTATION and locating Docket No. FAA–2017–
AD if it is approved by the Boeing 0331; or in person at the Docket
Commercial Airplanes Organization Federal Aviation Administration Management Facility between 9 a.m.
Designation Authorization (ODA) that has and 5 p.m., Monday through Friday,
been authorized by the Manager, Seattle 14 CFR Part 39 except Federal holidays. The AD docket
ACO, to make those findings. To be contains this proposed AD, the
[Docket No. FAA–2017–0331; Directorate
approved, the repair method, modification regulatory evaluation, any comments
Identifier 2016–NM–213–AD]
deviation, or alteration deviation must meet received, and other information. The
the certification basis of the airplane, and the RIN 2120–AA64
street address for the Docket Operations
approval must specifically refer to this AD. office (telephone 800–647–5527) is in
(4) Except as required by paragraph (h)(2) Airworthiness Directives; Bombardier,
Inc. Airplanes the ADDRESSES section. Comments will
of this AD: For service information that
be available in the AD docket shortly
contains steps that are labeled as Required AGENCY: Federal Aviation after receipt.
for Compliance (RC), the provisions of
Administration (FAA), DOT. FOR FURTHER INFORMATION CONTACT:
paragraphs (k)(4)(i) and (k)(4)(ii) of this AD
apply. ACTION: Notice of proposed rulemaking Fabio Buttitta, Aerospace Engineer,
(i) The steps labeled as RC, including (NPRM). Airframe and Mechanical Systems
substeps under an RC step and any figures Branch, ANE–171, FAA, New York
SUMMARY: We propose to adopt a new Aircraft Certification Office (ACO), 1600
identified in an RC step, must be done to airworthiness directive (AD) for certain
comply with the AD. If a step or substep is Stewart Avenue, Suite 410, Westbury,
Bombardier, Inc. Model DHC–8–102, NY 11590; telephone 516–228–7303; fax
labeled ‘‘RC Exempt,’’ then the RC
–103, –106, –201, –202, –301, –311, and 516–794–5531.
requirement is removed from that step or
–315 airplanes. This proposed AD was
substep. An AMOC is required for any SUPPLEMENTARY INFORMATION:
prompted by reports of undamped main
deviations to RC steps, including substeps
landing gear (MLG) extension in-service. Comments Invited
and identified figures.
This proposed AD would require
(ii) Steps not labeled as RC may be We invite you to send any written
replacement of the MLG retraction
deviated from using accepted methods in relevant data, views, or arguments about
accordance with the operator’s maintenance
actuator rod-ends on both MLG
this proposal. Send your comments to
or inspection program without obtaining
assemblies. We are proposing this AD to
an address listed under the ADDRESSES
approval of an AMOC, provided the RC steps, address the unsafe condition on these
section. Include ‘‘Docket No. FAA–
including substeps and identified figures, can products.
2017–0331; Directorate Identifier 2016–
still be done as specified, and the airplane DATES: We must receive comments on NM–213–AD’’ at the beginning of your
can be put back in an airworthy condition. this proposed AD by June 16, 2017. comments. We specifically invite
(l) Related Information ADDRESSES: You may send comments, comments on the overall regulatory,
using the procedures found in 14 CFR economic, environmental, and energy
(1) For more information about this AD,
11.43 and 11.45, by any of the following aspects of this proposed AD. We will
contact Wade Sullivan, Aerospace Engineer,
methods: consider all comments received by the
Airframe Branch, ANM–120S, FAA, Seattle
• Federal eRulemaking Portal: Go to closing date and may amend this
Aircraft Certification Office (ACO), 1601 Lind
http://www.regulations.gov. Follow the proposed AD based on those comments.
Avenue SW., Renton, WA 98057–3356;
instructions for submitting comments. We will post all comments we
phone: 425–917–6430; fax: 425–917–6590;
• Fax: 202–493–2251. receive, without change, to http://
email: wade.sullivan@faa.gov.
• Mail: U.S. Department of www.regulations.gov, including any
(2) For information about AMOCs, contact
Jennifer Tsakoumakis, Airframe Branch,
Transportation, Docket Operations, M– personal information you provide. We
ANM–120L, FAA, Los Angeles Aircraft
30, West Building Ground Floor, Room will also post a report summarizing each
Certification Office (ACO), 3960 Paramount
W12–140, 1200 New Jersey Avenue SE., substantive verbal contact we receive
Boulevard, Lakewood, CA 90712–4137; Washington, DC 20590. about this proposed AD.
phone: 562–627–5264; fax: 562–627–5210; • Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5 Discussion
email: jennifer.tsakoumakis@faa.gov.
(3) For service information identified in p.m., Monday through Friday, except Transport Canada Civil Aviation
this AD, contact Boeing Commercial Federal holidays. (TCCA), which is the aviation authority
Airplanes, Attention: Contractual & Data For service information identified in for Canada, has issued Canadian
this NPRM, contact Bombardier, Inc., Q- Airworthiness Directive CF–2016–36,
jstallworth on DSK7TPTVN1PROD with PROPOSALS
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600; Series Technical Help Desk, 123 Garratt dated December 6, 2016, (referred to
telephone 562–797–1717; Internet https:// Boulevard, Toronto, Ontario M3K 1Y5, after this as the Mandatory Continuing
www.myboeingfleet.com. You may view this Canada; telephone 416–375–4000; fax Airworthiness Information, or ‘‘the
referenced service information at the FAA, 416–375–4539; email thd.qseries@ MCAI’’), to correct an unsafe condition
Transport Airplane Directorate, 1601 Lind aero.bombardier.com; Internet http:// for certain Bombardier, Inc. Model
Avenue SW., Renton, WA. For information www.bombardier.com. You may view DHC–8–102, –103, –106, –201, –202,
on the availability of this material at the this referenced service information at –301, –311, and –315 airplanes. The
FAA, call 425–227–1221. the FAA, Transport Airplane MCAI states:
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Document Created: 2017-05-02 00:04:48
Document Modified: 2017-05-02 00:04:48
| 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 June 16, 2017. | |
| 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 | 82 FR 20450 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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