81 FR 29202 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 91 (May 11, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 91 (May 11, 2016)
| Page Range | 29202-29206 | |
| FR Document | 2016-11095 |
[Federal Register Volume 81, Number 91 (Wednesday, May 11, 2016)] [Proposed Rules] [Pages 29202-29206] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-11095] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-6430; Directorate Identifier 2015-NM-176-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) 2005-13- 30, which applies to all Boeing Model 737-100, -200, and -200C series airplanes. AD 2005-13-30 currently requires repetitive inspections to detect discrepancies of certain fuselage skin panels located just aft of the wheel well, and repair if necessary. Since we issued AD 2005-13- 30, an evaluation by the design approval holder (DAH) indicates that the fuselage skin is subject to widespread fatigue damage (WFD), and we have received reports of cracks at the chem-milled steps in the fuselage skin. This proposed AD would 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 proposing this AD to detect and correct fatigue cracking of the fuselage skin panels, which could cause rapid decompression of the airplane. DATES: We must receive comments on this proposed AD by June 27, 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-2016-6430. 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- 6430; 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 this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2016-6430; Directorate Identifier 2015-NM-176-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:// [[Page 29203]] 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 June 24, 2005, we issued AD 2005-13-30, Amendment 39-14167 (70 FR 36829, June 27, 2005) (``AD 2005-13-30''), for all Boeing Model 737- 100, -200, and -200C series airplanes. AD 2005-13-30 requires repetitive inspections to detect discrepancies of certain fuselage skin panels located just aft of the wheel well, and repair if necessary. AD 2005-13-30 resulted from reports of fatigue cracking of the skins and doublers located aft of the wing, between body station (BS) 727 and BS 1016, and between body stringers S-14 and S-25 on numerous Boeing Model 737-100, -200, and -200C series airplanes. On some airplanes, reinforcing angles had been installed on the skin doublers; however, cracking was detected on both modified and unmodified airplanes. The cracking has been attributed to fatigue from a combination of shear stresses due to repeated wrinkling of the skin, and the skin chem- milled pockets configuration. We issued AD 2005-13-30 to detect and correct fatigue cracking of the fuselage skin panels, which could cause rapid decompression of the airplane. Actions Since AD 2005-13-30 Was Issued Since we issued AD 2005-13-30, an evaluation by the DAH indicates that the fuselage skin is subject to WFD, and we have received reports of cracks at the chem-milled steps in the fuselage skin. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015. The service information describes procedures for inspection and repair of the fuselage skin panels between BS 727 and BS 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. FAA's Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements Although this proposed AD does not explicitly restate the requirements of AD 2005-13-30, this proposed AD would retain certain requirements of AD 2005-13-30. Those requirements are referenced in the service information identified previously, which, in turn, is referenced in paragraph (h) of 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 airplanes having line numbers 1 through 291, this proposed AD would require actions done in accordance with a method approved by the Manager, Seattle ACO, FAA. The phrase ``related investigative actions'' is used in this proposed AD. ``Related investigative actions'' are follow-on actions that (1) are related to the primary actions, and (2) further investigate the nature of any condition found. Related investigative actions in an AD could include, for example, inspections. The phrase ``corrective actions'' is used in this proposed AD. ``Corrective actions'' are actions that correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Differences Between This Proposed AD and the Service Information Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015, specifies to contact the manufacturer for instructions on how to repair certain conditions and also to obtain certain work instructions, but this proposed AD would require repairing those conditions and also to obtain those work instructions 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. Explanation of Compliance Time The compliance time for the replacement specified in this proposed AD for addressing WFD 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 [[Page 29204]] 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. Costs of Compliance We estimate that this proposed AD affects 9 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspection [actions retained Up to 88 work- $0................ Up to $7,480 per Up to $67,320 per from AD 2005-13-30]. hours x $85 per inspection cycle. inspection cycle. hour = $7,480 per inspection cycle. Inspection [new proposed action] Up to 1,914 work- $0................ Up to $162,690 per Up to $1,464,210 hours x $85 per inspection cycle. per inspection hour = $162,690 cycle. per inspection cycle. Skin panel replacement [new 688 work-hours x $96,000........... $154,480.......... $1,390,320. proposed action]. $85 per hour = $58,480. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs that would be required based on the results of the proposed inspection. We have no way of determining the number of aircraft that might need these repairs: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Time-limited repair........................... 24 work-hours x $85 per hour = (1) \1\ $2,040 $2,040. Permanent repair.............................. 43 work-hours x $85 per hour = (1) \1\ $3,655 $3,655. Permanent repair inspection................... 7 work-hours x $85 per hour = (1) \1\ $595 $595. ---------------------------------------------------------------------------------------------------------------- \1\ We have received no definitive data that would enable us to provide parts cost estimates for the on- condition actions specified in this proposed AD. According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all available costs in our cost estimate. 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) 2005-13-30, Amendment 39-14167 (70 FR 36829, June 27, 2005), and adding the following new AD: The Boeing Company: Docket No. FAA-2016-6430; Directorate Identifier 2015-NM-176-AD. (a) Comments Due Date The FAA must receive comments on this AD action by June 27, 2016. (b) Affected ADs This AD replaces AD 2005-13-30, Amendment 39-14167 (70 FR 36829, June 27, 2005) (``AD 2005-13-30''). (c) Applicability This AD applies to all The Boeing Company Model 737-100, -200, and -200C series airplanes, certificated in any category. [[Page 29205]] (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 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 fatigue cracking of the fuselage skin panels, which could cause rapid decompression of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Actions for Group 1 Airplanes For Group 1 airplanes identified in Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015: Within 120 days after the effective date of this AD, accomplish actions to correct the unsafe condition (e.g., inspections, repairs, modifications, and related investigative and corrective actions) using a method approved in accordance with the procedures specified in paragraph (o) of this AD. (h) Inspections, Related Investigative and Corrective Actions Except for Group 1 airplanes identified in Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015: At the applicable times specified in tables 1 and 2 of paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015, except as required by paragraphs (i)(1) and (i)(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 Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015, except as required by paragraphs (i)(3) and (i)(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 Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015. Accomplishment of a repair in accordance with ``Part 3: Repair'' of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015, except as required by paragraph (i)(3) of this AD, is terminating action for the repetitive inspections required by this paragraph at the repaired locations only. (i) Exceptions to Boeing Special Attention Service Bulletin 737-53- 1065, Revision 3, Dated June 30, 2015 (1) Where Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015, specifies compliance times ``after the Revision 3 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 paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015, refers to airplanes in certain configurations as of the ``issue date of Revision 3 of this service bulletin.'' However, this AD applies to airplanes in the specified configurations ``as of the effective date of this AD.'' (3) Where Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015, 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 (o) of this AD, except as required by paragraph (i)(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 at or before 59,000 total flight cycles: At the applicable time for the next inspection as specified in tables 1 and 2 of paragraph 1.E., ``Compliance,'' Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015, except as provided by paragraphs (i)(1) and (i)(2) of this AD: Perform inspections and applicable corrective actions using a method approved in accordance with the procedures specified in paragraph (o) of this AD. (j) Actions for Airplanes With a Time Limited Repair Installed Except for Group 1 airplanes identified in Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015: Do the applicable actions required by paragraphs (j)(1) and (j)(2) of this AD. (1) For airplanes with a time limited repair installed as specified in Boeing Special Attention Service Bulletin 737-53-1065, Revision 2, dated April 19, 2001: At the applicable times specified in table 3 of paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015, except as provided by paragraphs (i)(1) and (i)(2) of this AD: Do the actions specified in paragraphs (j)(1)(i) and (j)(1)(ii) of this AD. (i) 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 Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015, except as required by paragraph (i)(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 Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015. (ii) Make the time limited repair permanent; and do all applicable related investigative and corrective actions; in accordance the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015, except as required by paragraph (i)(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 (j)(1)(i) of this AD for the permanently repaired area only. (2) For airplanes with a time limited repair installed as specified in Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015: At the applicable times specified in table 4 of paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015: Do the actions specified in paragraphs (j)(2)(i) and (j)(2)(ii) of this AD. (i) 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 Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015, except as required by paragraph (i)(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 Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015. (ii) Make the time limited repair permanent; and do all applicable related investigative and corrective actions; in accordance the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015, except as required by paragraph (i)(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 (j)(2)(i) of this AD for the permanently repaired area only. (k) Modification of Certain Permanent Repairs Except for Group 1 airplanes identified in Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015: For airplanes with an existing time limited repair that was made permanent as specified in Boeing Special Attention Service Bulletin 737-53-1065, Revision 2, dated April 19, 2001: At the applicable times specified in table 5 of paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 737-53- 1065, Revision 3, dated June 30, 2015, except as required by paragraph (i)(1) of this AD: Modify the existing permanent repair; and do all applicable related investigative and corrective actions; in accordance the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015, except as required by paragraph (i)(3) of this AD. Do all applicable related investigative and corrective actions before further flight. (l) Certain Post-Repair Inspections For airplanes with a permanent repair installed as specified in Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015: At the applicable time specified in table 6 of paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 737-53- [[Page 29206]] 1065, Revision 3, dated June 30, 2015: Do an external low frequency eddy current (LFEC) inspection for cracking of the skin at the critical fastener row of the repair doubler; and do all applicable corrective actions; in accordance the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015, except as required by paragraph (i)(3) of this AD. Do all applicable corrective actions before further flight. Repeat the LFEC inspection thereafter at the applicable intervals specified in Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015. (m) Skin Panel Replacement Except for Group 1 airplanes identified in Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015: At the later of the times specified in paragraphs (m)(1) and (m)(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 Boeing Special Attention Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015. 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 (h) of this AD for that skin panel only, provided the skin panel was replaced with a production skin panel after 59,000 total flight cycles. (1) Before 60,000 total flight cycles, but not at or before 59,000 total flight cycles. (2) Within 6,000 flight cycles after the effective date of this AD, but not at or before 59,000 total flight cycles. (n) Credit for Previous Actions This paragraph provides credit for the actions required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using Boeing Special Attention Service Bulletin 737-53-1065, Revision 2, dated April 19, 2001, which was incorporated by reference in AD 2005-13-30. (o) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (p)(1) of this AD. Information may be emailed to: [email protected]. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) AMOCs approved previously for AD 2005-13-30, are approved as AMOCs for the corresponding provisions of paragraph (h) of this AD. (p) Related Information (1) For more information about this AD, contact Wade Sullivan, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle 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 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on May 4, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-11095 Filed 5-10-16; 8:45 am] BILLING CODE 4910-13-P
![29202 Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules
(j) New No Alternative Actions and/or Issued in Renton, Washington, on May 3, • Hand Delivery: Deliver to Mail
Intervals 2016. address above between 9 a.m. and 5
After accomplishing the revision required Michael Kaszycki, p.m., Monday through Friday, except
by paragraph (i) of this AD, no alternative Acting Manager, Transport Airplane Federal holidays.
actions (e.g., inspections) and/or intervals Directorate, Aircraft Certification Service. For service information identified in
may be used unless the actions and/or [FR Doc. 2016–10914 Filed 5–10–16; 8:45 am] this NPRM, contact Boeing Commercial
intervals are approved as an AMOC in
accordance with the procedures specified in BILLING CODE 4910–13–P Airplanes, Attention: Data & Services
paragraph (k)(1) of this AD. Management, P.O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone
(k) Other FAA AD Provisions DEPARTMENT OF TRANSPORTATION 206–544–5000, extension 1; fax 206–
The following provisions also apply to this 766–5680; Internet https://
AD: Federal Aviation Administration www.myboeingfleet.com. You may view
(1) Alternative Methods of Compliance this referenced service information at
(AMOCs): The Manager, International 14 CFR Part 39 the FAA, Transport Airplane
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to [Docket No. FAA–2016–6430; Directorate Directorate, 1601 Lind Avenue SW.,
approve AMOCs for this AD, if requested Identifier 2015–NM–176–AD;] Renton, WA. For information on the
using the procedures found in 14 CFR 39.19. availability of this material at the FAA,
RIN 2120–AA64
In accordance with 14 CFR 39.19, send your call 425–227–1221. It is also available
request to your principal inspector or local Airworthiness Directives; The Boeing on the Internet at http://
Flight Standards District Office, as www.regulations.gov by searching for
appropriate. If sending information directly Company Airplanes
and locating Docket No. FAA–2016–
to the International Branch, send it to ATTN: AGENCY: Federal Aviation 6430.
Sanjay Ralhan, Aerospace Engineer,
Administration (FAA), DOT.
International Branch, ANM–116, Transport Examining the AD Docket
Airplane Directorate, FAA, 1601 Lind ACTION: Notice of proposed rulemaking
Avenue SW., Renton, WA 98057–3356; (NPRM). You may examine the AD docket on
telephone 425–227–1405; fax 425–227–1149. the Internet at http://
Information may be emailed to: 9-ANM-116- SUMMARY: We propose to supersede www.regulations.gov by searching for
AMOC-REQUESTS@faa.gov. Airworthiness Directive (AD) 2005–13– and locating Docket No. FAA–2016–
(i) Before using any approved AMOC, 30, which applies to all Boeing Model 6430; or in person at the Docket
notify your appropriate principal inspector, 737–100, –200, and –200C series Management Facility between 9 a.m.
or lacking a principal inspector, the manager airplanes. AD 2005–13–30 currently and 5 p.m., Monday through Friday,
of the local flight standards district office/
requires repetitive inspections to detect except Federal holidays. The AD docket
certificate holding district office. The AMOC
approval letter must specifically reference discrepancies of certain fuselage skin contains this proposed AD, the
this AD. panels located just aft of the wheel well, regulatory evaluation, any comments
(ii) AMOCs approved previously for AD and repair if necessary. Since we issued received, and other information. The
2015–05–02, are approved as AMOCs for the AD 2005–13–30, an evaluation by the street address for the Docket Office
corresponding provisions of paragraphs (g) design approval holder (DAH) indicates (phone: 800–647–5527) is in the
and (h) of this AD. that the fuselage skin is subject to ADDRESSES section. Comments will be
(2) Contacting the Manufacturer: As of the widespread fatigue damage (WFD), and available in the AD docket shortly after
effective date of this AD, for any requirement we have received reports of cracks at the receipt.
in this AD to obtain corrective actions from
chem-milled steps in the fuselage skin. FOR FURTHER INFORMATION CONTACT:
a manufacturer, the action must be
accomplished using a method approved by This proposed AD would add new Wade Sullivan, Aerospace Engineer,
the Manager, International Branch, ANM– fuselage skin inspections for cracking, Airframe Branch, ANM–120S, FAA,
116, Transport Airplane Directorate, FAA; or inspections to detect missing or loose Seattle Aircraft Certification Office
the European Aviation Safety Agency fasteners and any disbonding or (ACO), 1601 Lind Avenue SW., Renton,
(EASA); or Airbus’s EASA Design cracking of bonded doublers, permanent WA 98057–3356; phone: 425–917–6430;
Organization Approval (DOA). If approved by repairs of time-limited repairs, related fax: 425–917–6590; email:
the DOA, the approval must include the investigative and corrective actions if
DOA-authorized signature. wade.sullivan@faa.gov.
necessary, and skin panel replacement.
SUPPLEMENTARY INFORMATION:
(l) Related Information We are proposing this AD to detect and
(1) Refer to Mandatory Continuing correct fatigue cracking of the fuselage Comments Invited
Airworthiness Information (MCAI) EASA skin panels, which could cause rapid We invite you to send any written
Airworthiness Directive 2015–0083, dated decompression of the airplane. relevant data, views, or arguments about
May 12, 2015, for related information. This DATES: We must receive comments on this proposed AD. Send your comments
MCAI may be found in the AD docket on the this proposed AD by June 27, 2016.
Internet at http://www.regulations.gov by to an address listed under the
searching for and locating Docket No. FAA– ADDRESSES: You may send comments, ADDRESSES section. Include ‘‘Docket No.
2016–6429. using the procedures found in 14 CFR FAA–2016–6430; Directorate Identifier
(2) For service information identified in 11.43 and 11.45, by any of the following 2015–NM–176–AD’’ at the beginning of
this AD, contact Airbus, Airworthiness methods: your comments. We specifically invite
Office—EIAS, 1 Rond Point Maurice • Federal eRulemaking Portal: Go to comments on the overall regulatory,
mstockstill on DSK3G9T082PROD with PROPOSALS
Bellonte, 31707 Blagnac Cedex, France; http://www.regulations.gov. Follow the economic, environmental, and energy
telephone +33 5 61 93 36 96; fax +33 5 61 instructions for submitting comments. aspects of this proposed AD. We will
93 44 51; email account.airworth-eas@
• Fax: 202–493–2251. consider all comments received by the
airbus.com; Internet http://www.airbus.com.
You may view this service information at the • Mail: U.S. Department of closing date and may amend this
FAA, Transport Airplane Directorate, 1601 Transportation, Docket Operations, M– proposed AD because of those
Lind Avenue SW., Renton, WA. For 30, West Building Ground Floor, Room comments.
information on the availability of this W12–140, 1200 New Jersey Avenue SE., We will post all comments we
material at the FAA, call 425–227–1221. Washington, DC 20590. receive, without change, to http://
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![29204 Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules
flight. We will not grant any extensions would substantiate and clearly warrant Costs of Compliance
of the compliance time to complete any such an extension. We estimate that this proposed AD
AD-mandated service bulletin related to affects 9 airplanes of U.S. registry.
WFD without extensive new data that We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Parts Cost on U.S.
Action Labor cost Cost per product
cost operators
Inspection [actions retained Up to 88 work-hours × $85 per $0 .......... Up to $7,480 per inspection Up to $67,320 per inspection
from AD 2005–13–30]. hour = $7,480 per inspection cycle. cycle.
cycle.
Inspection [new proposed ac- Up to 1,914 work-hours × $85 $0 .......... Up to $162,690 per inspection Up to $1,464,210 per inspec-
tion]. per hour = $162,690 per in- cycle. tion cycle.
spection cycle.
Skin panel replacement [new 688 work-hours × $85 per hour $96,000 $154,480 .................................. $1,390,320.
proposed action]. = $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 proposed inspection. We have no way of might need these repairs:
ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Time-limited repair ........................................................ 24 work-hours × $85 per hour = $2,040 ...................... ( 1) 1 $2,040
Permanent repair .......................................................... 43 work-hours × $85 per hour = $3,655 ...................... (1) 1 $3,655
Permanent repair inspection ........................................ 7 work-hours × $85 per hour = $595 ........................... (1) 1 $595
1 We have received no definitive data that would enable us to provide parts cost estimates for the on-condition actions specified in this pro-
posed AD.
According to the manufacturer, some Regulatory Findings The Proposed Amendment
of the costs of this proposed AD may be Accordingly, under the authority
covered under warranty, thereby We have determined that this
proposed AD would not have federalism delegated to me by the Administrator,
reducing the cost impact on affected the FAA proposes to amend 14 CFR part
individuals. We do not control warranty implications under Executive Order
39 as follows:
coverage for affected individuals. As a 13132. This proposed AD would not
result, we have included all available have a substantial direct effect on the PART 39—AIRWORTHINESS
costs in our cost estimate. States, on the relationship between the DIRECTIVES
national Government and the States, or
Authority for This Rulemaking on the distribution of power and ■ 1. The authority citation for part 39
responsibilities among the various continues to read as follows:
Title 49 of the United States Code
levels of government. Authority: 49 U.S.C. 106(g), 40113, 44701.
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I, For the reasons discussed above, I
§ 39.13 [Amended]
Section 106, describes the authority of certify that the proposed regulation:
■ 2. The FAA amends § 39.13 by
the FAA Administrator. Subtitle VII, (1) Is not a ‘‘significant regulatory removing Airworthiness Directive (AD)
Aviation Programs, describes in more action’’ under Executive Order 12866, 2005–13–30, Amendment 39–14167 (70
detail the scope of the Agency’s (2) Is not a ‘‘significant rule’’ under FR 36829, June 27, 2005), and adding
authority. the DOT Regulatory Policies and the following new AD:
We are issuing this rulemaking under Procedures (44 FR 11034, February 26, The Boeing Company: Docket No. FAA–
the authority described in Subtitle VII, 1979), 2016–6430; Directorate Identifier 2015–
Part A, Subpart III, Section 44701, (3) Will not affect intrastate aviation NM–176–AD.
‘‘General requirements.’’ Under that in Alaska, and (a) Comments Due Date
section, Congress charges the FAA with
(4) Will not have a significant The FAA must receive comments on this
promoting safe flight of civil aircraft in AD action by June 27, 2016.
air commerce by prescribing regulations economic impact, positive or negative,
mstockstill on DSK3G9T082PROD with PROPOSALS
for practices, methods, and procedures on a substantial number of small entities (b) Affected ADs
the Administrator finds necessary for under the criteria of the Regulatory This AD replaces AD 2005–13–30,
safety in air commerce. This regulation Flexibility Act. Amendment 39–14167 (70 FR 36829, June
is within the scope of that authority 27, 2005) (‘‘AD 2005–13–30’’).
List of Subjects in 14 CFR Part 39
because it addresses an unsafe condition (c) Applicability
that is likely to exist or develop on Air transportation, Aircraft, Aviation This AD applies to all The Boeing
products identified in this rulemaking safety, Incorporation by reference, Company Model 737–100, –200, and –200C
action. Safety. series airplanes, certificated in any category.
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![29206 Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules
1065, Revision 3, dated June 30, 2015: Do an been authorized by the Manager, Seattle fittings and upper side-of-body rib
external low frequency eddy current (LFEC) ACO, to make those findings. To be chord with tapered sleeve bolts. We are
inspection for cracking of the skin at the approved, the repair method, modification proposing this AD to prevent an
critical fastener row of the repair doubler; deviation, or alteration deviation must meet
and do all applicable corrective actions; in
unacceptable reduction of the fatigue
the certification basis of the airplane, and the
accordance the Accomplishment Instructions approval must specifically refer to this AD. life in the upper side-of-body rib chord.
of Boeing Special Attention Service Bulletin (4) AMOCs approved previously for AD Associated fatigue cracks can reduce the
737–53–1065, Revision 3, dated June 30, 2005–13–30, are approved as AMOCs for the structural capability to a point where it
2015, except as required by paragraph (i)(3) corresponding provisions of paragraph (h) of cannot sustain limit load, which could
of this AD. Do all applicable corrective this AD. adversely affect the structural integrity
actions before further flight. Repeat the LFEC of the airplane.
inspection thereafter at the applicable (p) Related Information
intervals specified in Boeing Special DATES: We must receive comments on
(1) For more information about this AD,
Attention Service Bulletin 737–53–1065, contact Wade Sullivan, Aerospace Engineer, this proposed AD by June 27, 2016.
Revision 3, dated June 30, 2015. Airframe Branch, ANM–120S, FAA, Seattle ADDRESSES: You may send comments,
(m) Skin Panel Replacement ACO, 1601 Lind Avenue SW., Renton, WA using the procedures found in 14 CFR
98057–3356; phone: 425–917–6430; fax: 425– 11.43 and 11.45, by any of the following
Except for Group 1 airplanes identified in 917–6590; email: wade.sullivan@faa.gov.
Boeing Special Attention Service Bulletin
methods:
737–53–1065, Revision 3, dated June 30,
(2) For service information identified in • Federal eRulemaking Portal: Go to
this AD, contact Boeing Commercial
2015: At the later of the times specified in http://www.regulations.gov. Follow the
Airplanes, Attention: Data & Services
paragraphs (m)(1) and (m)(2) of this AD: Management, P. O. Box 3707, MC 2H–65, instructions for submitting comments.
Replace the applicable skin panels, and do Seattle, WA 98124–2207; telephone 206– • Fax: 202–493–2251.
all applicable related investigative and 544–5000, extension 1; fax 206–766–5680; • Mail: U.S. Department of
corrective actions, in accordance with the Internet https://www.myboeingfleet.com. You Transportation, Docket Operations, M–
Accomplishment Instructions of Boeing may view this referenced service information 30, West Building Ground Floor, Room
Special Attention Service Bulletin 737–53– at the FAA, 1601 Lind Avenue SW., Renton, W12–140, 1200 New Jersey Avenue SE.,
1065, Revision 3, dated June 30, 2015. Do all Washington. For information on the
applicable related investigative and
Washington, DC 20590.
corrective actions before further flight. Doing
availability of this material at the FAA, call • Hand Delivery: Deliver to Mail
425–227–1221. address above between 9 a.m. and 5
the skin panel replacement required by this
paragraph terminates the inspection Issued in Renton, Washington, on May 4, p.m., Monday through Friday, except
requirements of paragraph (h) of this AD for 2016. Federal holidays.
that skin panel only, provided the skin panel Michael Kaszycki, For service information identified in
was replaced with a production skin panel Acting Manager, Transport Airplane this NPRM, contact Boeing Commercial
after 59,000 total flight cycles. Directorate, Aircraft Certification Service. Airplanes, Attention: Data & Services
(1) Before 60,000 total flight cycles, but not
[FR Doc. 2016–11095 Filed 5–10–16; 8:45 am] Management, P.O. Box 3707, MC 2H–65,
at or before 59,000 total flight cycles.
(2) Within 6,000 flight cycles after the BILLING CODE 4910–13–P Seattle, WA 98124–2207; telephone
effective date of this AD, but not at or before 206–544–5000, extension 1; fax 206–
59,000 total flight cycles. 766–5680; Internet https://
DEPARTMENT OF TRANSPORTATION www.myboeingfleet.com. You may view
(n) Credit for Previous Actions
this referenced service information at
This paragraph provides credit for the Federal Aviation Administration the FAA, Transport Airplane
actions required by paragraph (h) of this AD, Directorate, 1601 Lind Avenue SW.,
if those actions were performed before the 14 CFR Part 39
effective date of this AD using Boeing Special
Renton, WA. For information on the
Attention Service Bulletin 737–53–1065, [Docket No. FAA–2016–6428; Directorate availability of this material at the FAA,
Revision 2, dated April 19, 2001, which was Identifier 2015–NM–119–AD] call 425–227–1221. It is also available
incorporated by reference in AD 2005–13–30. on the Internet at http://
RIN 2120–AA64 www.regulations.gov by searching for
(o) Alternative Methods of Compliance
(AMOCs) and locating Docket No. FAA–2016–
Airworthiness Directives; The Boeing
6428.
(1) The Manager, Seattle Aircraft Company Airplanes
Certification Office (ACO), FAA, has the Examining the AD Docket
authority to approve AMOCs for this AD, if AGENCY: Federal Aviation
requested using the procedures found in 14 Administration (FAA), DOT. You may examine the AD docket on
CFR 39.19. In accordance with 14 CFR 39.19, ACTION: Notice of proposed rulemaking
the Internet at http://
send your request to your principal inspector (NPRM). www.regulations.gov by searching for
or local Flight Standards District Office, as and locating Docket No. FAA–2016–
appropriate. If sending information directly SUMMARY: We propose to adopt a new 6428; or in person at the Docket
to the manager of the ACO, send it to the airworthiness directive (AD) for certain Management Facility between 9 a.m.
attention of the person identified in and 5 p.m., Monday through Friday,
paragraph (p)(1) of this AD. Information may
The Boeing Company Model 787–8
airplanes. This proposed AD was except Federal holidays. The AD docket
be emailed to: 9–ANM-Seattle-ACO–AMOC-
Requests@faa.gov. prompted by reports indicating that contains this proposed AD, the
(2) Before using any approved AMOC, certain wing side-of-body stringer regulatory evaluation, any comments
notify your appropriate principal inspector, fittings have been installed with faying received, and other information. The
mstockstill on DSK3G9T082PROD with PROPOSALS
or lacking a principal inspector, the manager surface mismatch beyond the allowed street address for the Docket Office
of the local flight standards district office/ machining tolerance. This proposed AD (phone: 800–647–5527) is in the
certificate holding district office. would require inspection of certain ADDRESSES section. Comments will be
(3) An AMOC that provides an acceptable available in the AD docket shortly after
level of safety may be used for any repair,
stringer fittings for faying surface
mismatch common to the side-of-body receipt.
modification, or alteration required by this
AD if it is approved by the Boeing rib chord, replacement if necessary, and FOR FURTHER INFORMATION CONTACT:
Commercial Airplanes Organization replacement of the clearance fit Allen Rauschendorfer, Aerospace
Designation Authorization (ODA) that has fasteners common to the side-of-body Engineer, Airframe Branch, ANM–120S,
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Document Created: 2016-05-11 01:11:48
Document Modified: 2016-05-11 01:11:48
| 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 27, 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 29202 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft and Aviation Safety |
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