82 FR 17773 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 70 (April 13, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 70 (April 13, 2017)
| Page Range | 17773-17776 | |
| FR Document | 2017-07440 |
[Federal Register Volume 82, Number 70 (Thursday, April 13, 2017)] [Proposed Rules] [Pages 17773-17776] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-07440] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0249; Directorate Identifier 2016-NM-138-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 all The Boeing Company Model 757-200, -200PF, and -200CB series airplanes. This proposed AD was prompted by reports of slats disbonding on airplanes on which the terminating actions of AD 2005-07-08 had been performed. We have also received reports of slats disbonding on airplanes outside of the applicability of AD 90-23-06, AD 91-22-51, and AD 2005-07-08. This proposed AD would require determining the type of trailing edge slat wedges of the leading edge slats, repetitive inspections for disbonding on certain trailing edge slat wedges, and corrective actions, if necessary. This proposed AD would also provide an optional terminating action for the repetitive inspections. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by May 30, 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-2017-0249. 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- 0249; 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: Lu Lu, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6577; fax: 425-917-6478; email: [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2017-0249; Directorate Identifier 2016-NM-138-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 [[Page 17774]] 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 We have received reports of slats disbonding on airplanes on which the terminating actions of AD 2005-07-08, Amendment 39-14032 (70 FR 16403, March 31, 2005), had been performed. We have also received reports of slats disbonding on airplanes outside of the applicability of AD 90-23-06, Amendment 39-6794 (55 FR 46499, November 5, 1990); AD 91-22-51, Amendment 39-8129 (57 FR 781, January 9, 1992); and AD 2005- 07-08. Inspection of submitted damaged trailing edge slat wedges indicated that the panels had been contaminated with moisture ingression, as there was evidence of aluminum oxide powder on the core, and the adhesive had failed at the skin-to-core bondline. It is suspected that there was incomplete removal of moisture and honeycomb core corrosion during the repair of the trailing edge slat wedges or that moisture had previously migrated into the panel and was subsequently sealed inside. One operator reported major skin-to-core disbonding of a trailing edge slat wedge when the airplane had accumulated 42,603 total flight hours and 9,808 total flight cycles. Another operator reported the departure of a trailing edge slat wedge during flight when the airplane had accumulated 47,470 total flight hours and 17,579 total flight cycles. We are proposing this AD to prevent delamination of the trailing edge slat wedges of the leading edge slats. This delamination could cause loss of pieces of the trailing edge slat wedge assemblies during flight, reduction of the maneuver and stall margins, and consequent reduced controllability of the airplane. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Special Attention Service Bulletin 757-57-0066, Revision 1, dated June 7, 2016 (``SASB 757-57-0066, R1''). The service information describes procedures for doing inspections on trailing edge slat wedges of the leading edge slats for areas of skin-to-core and aft edge disbonding, and corrective actions including replacement of certain slat wedges. 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 This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ``Differences Between this Proposed AD and the Service Information.'' 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-2017-0249. The phrase ``related investigative actions'' is used in this proposed AD. Related investigative actions are follow-on actions that (1) are related to the primary action, and (2) further investigate the nature of any condition found. Related investigative actions in an AD could include, for example, inspections. The phrase ``corrective actions'' is used in this proposed AD. Corrective actions correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Differences Between This Proposed AD and the Service Information SASB 757-57-0066, R1, specifies to contact the manufacturer for certain instructions, but this proposed AD would require using repair methods, modification deviations, and alteration deviations in one of the following ways: In accordance with a method that we approve; or Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Costs of Compliance We estimate that this proposed AD affects 469 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product Cost on U.S. operators ---------------------------------------------------------------------------------------------------------------- Inspections.................. Up to 24 $0 Up to $2,040 per Up to $956,760 per work[dash]hours x inspection inspection cycle. $85 per hour = cycle. $2,040 per inspection cycle. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary replacements 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 replacements: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Wedge replacement (per wedge).... 43 work-hours x $85 per Up to $84,636....... Up to $88,291. hour = $3,655. ---------------------------------------------------------------------------------------------------------------- The on-condition costs are an estimate of the cost of replacing a type A wedge with a type B wedge, which is a terminating action for the required inspections. There are up to 10 wedge assemblies per airplane, and the price range for a new assembly is $50,923 to $84,636 based on the information provided by Boeing. The cost of repairing a type A wedge cannot be estimated because damage type and size may vary widely. 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 [[Page 17775]] 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-2017-0249; Directorate Identifier 2016-NM-138-AD. (a) Comments Due Date We must receive comments by May 30, 2017. (b) Affected ADs This AD affects AD 90-23-06, Amendment 39-6794 (55 FR 46499, November 5, 1990) (``AD 90-23-06''); AD 91-22-51, Amendment 39-8129 (57 FR 781, January 9, 1992) (``AD 91-22-51''); and AD 2005-07-08, Amendment 39-14032 (70 FR 16403, March 31, 2005) (``AD 2005-07- 08''). (c) Applicability This AD applies to all The Boeing Company Model 757-200, -200PF, and -200CB series airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Unsafe Condition This AD was prompted by reports of slats disbonding on airplanes on which the terminating actions of AD 2005-07-08 had been performed. We have also received reports of slats disbonding on airplanes outside of the applicability of AD 90-23-06, AD 91-22-51, and AD 2005-07-08. We are issuing this AD to prevent delamination of the trailing edge slat wedges of the leading edge slats. This delamination could cause loss of pieces of the trailing edge slat wedge assemblies during flight, reduction of the maneuver and stall margins, and consequent reduced controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection to Determine Slat Wedge Type At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service Bulletin 757-57- 0066, Revision 1, dated June 7, 2016 (``SASB 757-57-0066, R1''), except as specified in paragraph (j)(1) of this AD: Inspect each trailing edge slat wedge of the leading edge slats in accordance with Appendices A, B, C, and D of SASB 757-57-0066, R1, or review the airplane maintenance records, to determine whether the slat wedge is a type A or a type B. If a maintenance records review cannot conclusively determine a slat wedge is a type B, it must be assumed to be a type A slat wedge or a physical inspection must be done as specified in this paragraph. (h) Type A Slat Wedge Repetitive Inspections, Related Investigative Actions, and Corrective Actions For each type A trailing edge slat wedge found during the inspection or records review required by paragraph (g) of this AD: At the applicable time specified in paragraph 1.E., ``Compliance,'' of SASB 757-57-0066, R1, except as specified in paragraph (j)(1) of this AD, do an ultrasonic low frequency bond test inspection, a tap test inspection, or a through transmission ultrasonic (TTU) inspection for skin-to-core disbonds of the honeycomb area of the trailing edge slat wedge; do a detailed inspection for aft edge disbonds of the aft edge of the trailing edge slat wedge; do a general visual inspection for any previously accomplished repair; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of SASB 757-57- 0066, R1, except as specified in paragraphs (i) and (j)(2) of this AD. Do all applicable related investigative and corrective actions at the applicable time specified in paragraph 1.E., ``Compliance,'' of SASB 757-57-0066, R1. Repeat the applicable inspections on each type A trailing edge slat wedge thereafter at the applicable intervals specified in paragraph 1.E., ``Compliance,'' of SASB 757- 57-0066, R1. (i) Repaired Type A Slat Wedge Repetitive Inspections, Related Investigative Actions and Corrective Actions (1) For each type A trailing edge slat wedge with any class 1 disbond repair or any previously accomplished repair subject to the Part 2 inspection as identified in SASB 757-57-0066, R1: At the applicable time specified in paragraph 1.E., ``Compliance,'' of SASB 757-57-0066, R1, do an ultrasonic low frequency bond test inspection, a tap test inspection, or a TTU inspection for skin-to- core disbonds in the repaired area of the trailing edge slat wedge; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of SASB 757-57- 0066, R1, except as specified in paragraph (j)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspection on each type A trailing edge slat wedge thereafter at the applicable interval specified in paragraph 1.E., ``Compliance,'' of SASB 757-57-0066, R1. (2) For each type A trailing edge slat wedge with any time- limited class 2 disbond repair as identified in SASB 757-57-0066, R1: At the applicable time specified in paragraph 1.E., ``Compliance,'' of SASB 757-57-0066, R1, do a detailed inspection for any peeling or deterioration of the aluminum foil tape of the repaired area on the trailing edge slat wedge; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of SASB 757-57-0066, R1, except as specified in paragraph (j)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspection on each type A trailing edge slat wedge thereafter at the applicable interval specified in paragraph 1.E., ``Compliance,'' of SASB 757-57-0066, R1, until a permanent repair is done to complete the actions required for the time-limited class 2 disbond repair, specified as corrective actions in paragraph (h) of this AD. (3) For each type A trailing edge slat wedge with any permanent class 2 disbond repair as identified in SASB 757-57-0066, R1: At the applicable time specified in paragraph 1.E., ``Compliance,'' of SASB 757-57-0066, R1, do an ultrasonic low frequency bond test [[Page 17776]] inspection or a TTU inspection for any disbonding of the aft edge repaired areas; a detailed inspection for disbonds along the aft edge of the repaired areas; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of SASB 757-57-0066, R1, except as specified in paragraph (j)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspection on each type A trailing edge slat wedge thereafter at the applicable interval specified in paragraph 1.E., ``Compliance,'' of SASB 757-57-0066, R1. (4) For each type A trailing edge slat wedge with any class 3 or class 4 disbond repair, or any previously accomplished repair subject to Part 5 inspection as identified in SASB 757-57-0066, R1: At the applicable time specified in paragraph 1.E., ``Compliance,'' of SASB 757-57-0066, R1, do the applicable actions specified in paragraphs (i)(4)(i) and (i)(4)(ii) of this AD. (i) For any class 3 disbond repair with a repair doubler common to the aft edge of the trailing edge slat wedge; for any previously accomplished repair with a repair doubler common to the aft edge of the trailing edge slat wedge; and for any class 4 disbond repair: Do an ultrasonic low frequency bond test inspection or a TTU inspection for any disbonding of the aft edge repaired areas; a detailed inspection for disbonds along the aft edge of the repaired areas; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of SASB 757-57- 0066, R1, except as specified in paragraph (j)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspection on each type A trailing edge slat wedge thereafter at the applicable interval specified in paragraph 1.E., ``Compliance,'' of SASB 757-57-0066, R1. (ii) For any class 3 disbond repair without a repair doubler common to the aft edge of the trailing edge slat wedge; and for any previously accomplished repair without a repair doubler common to the aft edge of the trailing edge slat wedge: Do an ultrasonic low frequency bond test inspection, a tap test inspection, or a TTU inspection for skin-to-core disbonds of the honeycomb area of the trailing edge slat wedge in the repaired area; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of SASB 757-57-0066, R1, except as specified in paragraph (j)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the applicable inspection on each type A trailing edge slat wedge thereafter at the applicable interval specified in paragraph 1.E., ``Compliance,'' of SASB 757-57-0066, R1. (j) Exceptions to Service Information (1) Where paragraph 1.E., ``Compliance,'' of SASB 757-57-0066, R1, specifies a compliance time ``after the Revision 1 date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) If any disbonding is found during any inspection required by this AD, and SASB 757-57-0066, R1, specifies to contact Boeing for appropriate action: Before further flight, repair the disbonding using a method approved in accordance with the procedures specified in paragraph (n) of this AD. (k) Optional Terminating Action for Repetitive Inspections Replacing a type A trailing edge slat wedge with a type B trailing edge slat wedge in accordance with the Accomplishment Instructions of SASB 757-57-0066, R1, terminates the repetitive inspections required by this AD for the replaced wedge. (l) Terminating Action for Certain Other ADs Accomplishing the initial inspections required by paragraphs (g) and (h) of this AD on a trailing edge slat wedge terminates all the requirements of AD 90-23-06, AD 91-22-51, and AD 2005-07-08 for that slat wedge. (m) Parts Installation Limitation As of the effective date of this AD: A replacement type A wedge may be installed provided that the initial and repetitive inspections specified in paragraph (h) and (i) of this AD are done within the applicable compliance times specified in paragraph (h) and (i) of this AD and all applicable related investigative and corrective actions are done within the applicable compliance times specified in paragraphs (h) and (i) of this AD. (n) 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 (o)(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) Except as required by paragraph (j)(2) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (n)(4)(i) and (n)(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. (o) Related Information (1) For more information about this AD, contact Lu Lu, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6478; fax: 425- 917-6590; email: [email protected]. (2) 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 5, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-07440 Filed 4-12-17; 8:45 am] BILLING CODE 4910-13-P
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A319/A320/A321 Airworthiness Limitations airbus.com; Internet: http://www.airbus.com. W12–140, 1200 New Jersey Avenue SE.,
Section, ALS Part 4, ‘‘System Equipment You may view this service information at the Washington, DC 20590.
Maintenance Requirements (SEMR)’’ FAA, Transport Airplane Directorate, 1601 • Hand Delivery: Deliver to Mail
Revision 03 at Issue 02, dated January 22, Lind Avenue SW., Renton, WA. For address above between 9 a.m. and 5
2016; or within 2 weeks after revising the information on the availability of this
maintenance or inspection program;
p.m., Monday through Friday, except
material at the FAA, call 425–227–1221.
whichever occurs later. Accomplishing the Federal holidays.
actions specified in this paragraph terminates Issued in Renton, Washington, on April 5, For service information identified in
the requirements of paragraph (g) of this AD. 2017. this NPRM, contact Boeing Commercial
Michael Kaszycki, Airplanes, Attention: Contractual & Data
(j) New Provision: No Alternative Actions or
Acting Manager, Transport Airplane Services (C&DS), 2600 Westminster
Intervals
Directorate, Aircraft Certification Service. Blvd., MC 110–SK57, Seal Beach, CA
After the action required by paragraph (i) [FR Doc. 2017–07441 Filed 4–12–17; 8:45 am] 90740–5600; telephone 562–797–1717;
of this AD has been done, no alternative
BILLING CODE 4910–13–P Internet https://
actions (e.g., inspections) or intervals may be
used unless the actions or intervals are www.myboeingfleet.com. You may view
approved as an AMOC in accordance with this referenced service information at
the procedures specified in paragraph (k)(1) DEPARTMENT OF TRANSPORTATION the FAA, Transport Airplane
of this AD. Directorate, 1601 Lind Avenue SW.,
Federal Aviation Administration Renton, WA. For information on the
(k) Other FAA AD Provisions
availability of this material at the FAA,
The following provisions also apply to this 14 CFR Part 39 call 425–227–1221. It is also available
AD:
[Docket No. FAA–2017–0249; Directorate on the Internet at http://
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International Identifier 2016–NM–138–AD] www.regulations.gov by searching for
Branch, ANM–116, Transport Airplane and locating Docket No. FAA–2017–
Directorate, FAA, has the authority to RIN 2120–AA64 0249.
approve AMOCs for this AD, if requested
Airworthiness Directives; The Boeing Examining the AD Docket
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your Company Airplanes You may examine the AD docket on
request to your principal inspector or local the Internet at http://
Flight Standards District Office, as AGENCY: Federal Aviation
www.regulations.gov by searching for
appropriate. If sending information directly Administration (FAA), DOT.
and locating Docket No. FAA–2017–
to the International Branch, send it to ATTN: ACTION: Notice of proposed rulemaking 0249; or in person at the Docket
Sanjay Ralhan, Aerospace Engineer, (NPRM).
International Branch, ANM–116, Transport
Management Facility between 9 a.m.
Airplane Directorate, FAA, 1601 Lind SUMMARY: We propose to adopt a new and 5 p.m., Monday through Friday,
Avenue SW., Renton, WA 98057–3356; airworthiness directive (AD) for all The except Federal holidays. The AD docket
telephone: 425–227–1405; fax: 425–227– contains this proposed AD, the
Boeing Company Model 757–200,
1149. Information may be emailed to: 9– regulatory evaluation, any comments
ANM–116–AMOC–REQUESTS@faa.gov.
–200PF, and –200CB series airplanes.
received, and other information. The
(i) Before using any approved AMOC, This proposed AD was prompted by
street address for the Docket Office
notify your appropriate principal inspector, reports of slats disbonding on airplanes
(phone: 800–647–5527) is in the
or lacking a principal inspector, the manager on which the terminating actions of AD
ADDRESSES section. Comments will be
of the local flight standards district office/ 2005–07–08 had been performed. We
certificate holding district office. available in the AD docket shortly after
have also received reports of slats
(ii) AMOCs approved previously for AD receipt.
disbonding on airplanes outside of the
2014–26–10 are approved as AMOCs for the FOR FURTHER INFORMATION CONTACT: Lu
applicability of AD 90–23–06, AD 91–
corresponding provisions of paragraph (g) of
22–51, and AD 2005–07–08. This Lu, Aerospace Engineer, Airframe
this AD. Branch, ANM–120S, FAA, Seattle
(2) Contacting the Manufacturer: As of the proposed AD would require
determining the type of trailing edge slat Aircraft Certification Office (ACO), 1601
effective date of this AD, for any requirement Lind Avenue SW., Renton, WA 98057–
in this AD to obtain corrective actions from wedges of the leading edge slats,
a manufacturer, the action must be repetitive inspections for disbonding on 3356; phone: 425–917–6577; fax: 425–
accomplished using a method approved by certain trailing edge slat wedges, and 917–6478; email: lu.lu@faa.gov.
the Manager, International Branch, ANM– corrective actions, if necessary. This SUPPLEMENTARY INFORMATION:
116, Transport Airplane Directorate, FAA; or proposed AD would also provide an
the European Aviation Safety Agency
Comments Invited
optional terminating action for the
(EASA); or EASA Design Organization We invite you to send any written
Approval (DOA). If approved by the DOA, repetitive inspections. We are proposing
relevant data, views, or arguments about
the approval must include the DOA- this AD to address the unsafe condition
this proposal. Send your comments to
authorized signature. on these products.
an address listed under the ADDRESSES
(l) Related Information DATES: We must receive comments on section. Include ‘‘Docket No. FAA–
this proposed AD by May 30, 2017. 2017–0249; Directorate Identifier 2016–
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD ADDRESSES: You may send comments, NM–138–AD’’ at the beginning of your
2016–0093, dated May 13, 2016, for related using the procedures found in 14 CFR comments. We specifically invite
information. This MCAI may be found in the 11.43 and 11.45, by any of the following comments on the overall regulatory,
nlaroche on DSK30NT082PROD with PROPOSALS
AD docket on the Internet at http:// methods: economic, environmental, and energy
www.regulations.gov by searching for and • Federal eRulemaking Portal: Go to aspects of this proposed AD. We will
locating Docket No. FAA–2017–0248. http://www.regulations.gov. Follow the
(2) For service information identified in
consider all comments received by the
this AD, contact Airbus, Airworthiness
instructions for submitting comments. closing date and may amend this
Office—EIAS, 1 Rond Point Maurice • Fax: 202–493–2251. proposed AD because of those
Bellonte, 31707 Blagnac Cedex, France; • Mail: U.S. Department of comments.
telephone: +33 5 61 93 36 96; fax: +33 5 61 Transportation, Docket Operations, M– We will post all comments we
93 44 51; email: account.airworth-eas@ 30, West Building Ground Floor, Room receive, without change, to
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the FAA Administrator. Subtitle VII: The Boeing Company: Docket No. FAA– through transmission ultrasonic (TTU)
Aviation Programs, describes in more 2017–0249; Directorate Identifier 2016– inspection for skin-to-core disbonds of the
detail the scope of the Agency’s NM–138–AD. honeycomb area of the trailing edge slat
wedge; do a detailed inspection for aft edge
authority. (a) Comments Due Date disbonds of the aft edge of the trailing edge
We are issuing this rulemaking under We must receive comments by May 30, slat wedge; do a general visual inspection for
the authority described in Subtitle VII, 2017. any previously accomplished repair; and do
Part A, Subpart III, Section 44701: all applicable related investigative and
(b) Affected ADs
‘‘General requirements.’’ Under that corrective actions; in accordance with the
section, Congress charges the FAA with This AD affects AD 90–23–06, Amendment Accomplishment Instructions of SASB 757–
promoting safe flight of civil aircraft in 39–6794 (55 FR 46499, November 5, 1990) 57–0066, R1, except as specified in
(‘‘AD 90–23–06’’); AD 91–22–51, paragraphs (i) and (j)(2) of this AD. Do all
air commerce by prescribing regulations Amendment 39–8129 (57 FR 781, January 9,
for practices, methods, and procedures applicable related investigative and
1992) (‘‘AD 91–22–51’’); and AD 2005–07–08, corrective actions at the applicable time
the Administrator finds necessary for Amendment 39–14032 (70 FR 16403, March specified in paragraph 1.E., ‘‘Compliance,’’ of
safety in air commerce. This regulation 31, 2005) (‘‘AD 2005–07–08’’). SASB 757–57–0066, R1. Repeat the
is within the scope of that authority applicable inspections on each type A
(c) Applicability
because it addresses an unsafe condition trailing edge slat wedge thereafter at the
that is likely to exist or develop on This AD applies to all The Boeing applicable intervals specified in paragraph
Company Model 757–200, –200PF, and 1.E., ‘‘Compliance,’’ of SASB 757–57–0066,
products identified in this rulemaking –200CB series airplanes, certificated in any
action. R1.
category.
Regulatory Findings (i) Repaired Type A Slat Wedge Repetitive
(d) Subject Inspections, Related Investigative Actions
We determined that this proposed AD Air Transport Association (ATA) of and Corrective Actions
would not have federalism implications America Code 57, Wings.
(1) For each type A trailing edge slat wedge
under Executive Order 13132. This (e) Unsafe Condition with any class 1 disbond repair or any
proposed AD would not have a previously accomplished repair subject to the
This AD was prompted by reports of slats
substantial direct effect on the States, on disbonding on airplanes on which the Part 2 inspection as identified in SASB 757–
the relationship between the national terminating actions of AD 2005–07–08 had 57–0066, R1: At the applicable time specified
Government and the States, or on the been performed. We have also received in paragraph 1.E., ‘‘Compliance,’’ of SASB
distribution of power and reports of slats disbonding on airplanes 757–57–0066, R1, do an ultrasonic low
responsibilities among the various outside of the applicability of AD 90–23–06, frequency bond test inspection, a tap test
AD 91–22–51, and AD 2005–07–08. We are inspection, or a TTU inspection for skin-to-
levels of government. core disbonds in the repaired area of the
For the reasons discussed above, I issuing this AD to prevent delamination of
the trailing edge slat wedges of the leading trailing edge slat wedge; and do all
certify this proposed regulation: applicable related investigative and
edge slats. This delamination could cause
(1) Is not a ‘‘significant regulatory corrective actions; in accordance with the
loss of pieces of the trailing edge slat wedge
action’’ under Executive Order 12866, assemblies during flight, reduction of the Accomplishment Instructions of SASB 757–
(2) Is not a ‘‘significant rule’’ under maneuver and stall margins, and consequent 57–0066, R1, except as specified in paragraph
the DOT Regulatory Policies and reduced controllability of the airplane. (j)(2) of this AD. Do all applicable related
Procedures (44 FR 11034, February 26, investigative and corrective actions before
(f) Compliance further flight. Repeat the applicable
1979),
(3) Will not affect intrastate aviation Comply with this AD within the inspection on each type A trailing edge slat
compliance times specified, unless already wedge thereafter at the applicable interval
in Alaska, and specified in paragraph 1.E., ‘‘Compliance,’’ of
(4) Will not have a significant done.
SASB 757–57–0066, R1.
economic impact, positive or negative, (g) Inspection to Determine Slat Wedge Type (2) For each type A trailing edge slat wedge
on a substantial number of small entities At the applicable time specified in with any time-limited class 2 disbond repair
under the criteria of the Regulatory paragraph 1.E., ‘‘Compliance,’’ of Boeing as identified in SASB 757–57–0066, R1: At
Flexibility Act. Special Attention Service Bulletin 757–57– the applicable time specified in paragraph
0066, Revision 1, dated June 7, 2016 (‘‘SASB 1.E., ‘‘Compliance,’’ of SASB 757–57–0066,
List of Subjects in 14 CFR Part 39 757–57–0066, R1’’), except as specified in R1, do a detailed inspection for any peeling
Air transportation, Aircraft, Aviation paragraph (j)(1) of this AD: Inspect each or deterioration of the aluminum foil tape of
safety, Incorporation by reference, trailing edge slat wedge of the leading edge the repaired area on the trailing edge slat
slats in accordance with Appendices A, B, C, wedge; and do all applicable related
Safety. investigative and corrective actions; in
and D of SASB 757–57–0066, R1, or review
The Proposed Amendment the airplane maintenance records, to accordance with the Accomplishment
determine whether the slat wedge is a type Instructions of SASB 757–57–0066, R1,
Accordingly, under the authority A or a type B. If a maintenance records except as specified in paragraph (j)(2) of this
delegated to me by the Administrator, review cannot conclusively determine a slat AD. Do all applicable related investigative
the FAA proposes to amend 14 CFR part wedge is a type B, it must be assumed to be and corrective actions before further flight.
39 as follows: a type A slat wedge or a physical inspection Repeat the applicable inspection on each
must be done as specified in this paragraph. type A trailing edge slat wedge thereafter at
PART 39—AIRWORTHINESS the applicable interval specified in paragraph
(h) Type A Slat Wedge Repetitive 1.E., ‘‘Compliance,’’ of SASB 757–57–0066,
DIRECTIVES
Inspections, Related Investigative Actions, R1, until a permanent repair is done to
and Corrective Actions
nlaroche on DSK30NT082PROD with PROPOSALS
■ 1. The authority citation for part 39 complete the actions required for the time-
continues to read as follows: For each type A trailing edge slat wedge limited class 2 disbond repair, specified as
found during the inspection or records corrective actions in paragraph (h) of this AD.
Authority: 49 U.S.C. 106(g), 40113, 44701. review required by paragraph (g) of this AD: (3) For each type A trailing edge slat wedge
At the applicable time specified in paragraph with any permanent class 2 disbond repair as
§ 39.13 [Amended]
1.E., ‘‘Compliance,’’ of SASB 757–57–0066, identified in SASB 757–57–0066, R1: At the
■ 2. The FAA amends § 39.13 by adding R1, except as specified in paragraph (j)(1) of applicable time specified in paragraph 1.E.,
the following new airworthiness this AD, do an ultrasonic low frequency bond ‘‘Compliance,’’ of SASB 757–57–0066, R1, do
directive (AD): test inspection, a tap test inspection, or a an ultrasonic low frequency bond test
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![17776 Federal Register / Vol. 82, No. 70 / Thursday, April 13, 2017 / Proposed Rules
inspection or a TTU inspection for any 757–57–0066, R1, specifies to contact Boeing labeled ‘‘RC Exempt,’’ then the RC
disbonding of the aft edge repaired areas; a for appropriate action: Before further flight, requirement is removed from that step or
detailed inspection for disbonds along the aft repair the disbonding using a method substep. An AMOC is required for any
edge of the repaired areas; and do all approved in accordance with the procedures deviations to RC steps, including substeps
applicable related investigative and specified in paragraph (n) of this AD. and identified figures.
corrective actions; in accordance with the (ii) Steps not labeled as RC may be
Accomplishment Instructions of SASB 757– (k) Optional Terminating Action for
deviated from using accepted methods in
57–0066, R1, except as specified in paragraph Repetitive Inspections
accordance with the operator’s maintenance
(j)(2) of this AD. Do all applicable related Replacing a type A trailing edge slat wedge or inspection program without obtaining
investigative and corrective actions before with a type B trailing edge slat wedge in approval of an AMOC, provided the RC steps,
further flight. Repeat the applicable accordance with the Accomplishment including substeps and identified figures, can
inspection on each type A trailing edge slat Instructions of SASB 757–57–0066, R1, still be done as specified, and the airplane
wedge thereafter at the applicable interval terminates the repetitive inspections required can be put back in an airworthy condition.
specified in paragraph 1.E., ‘‘Compliance,’’ of by this AD for the replaced wedge.
SASB 757–57–0066, R1. (o) Related Information
(4) For each type A trailing edge slat wedge (l) Terminating Action for Certain Other ADs
(1) For more information about this AD,
with any class 3 or class 4 disbond repair, or Accomplishing the initial inspections contact Lu Lu, Aerospace Engineer, Airframe
any previously accomplished repair subject required by paragraphs (g) and (h) of this AD Branch, ANM–120S, FAA, Seattle ACO, 1601
to Part 5 inspection as identified in SASB on a trailing edge slat wedge terminates all Lind Avenue SW., Renton, WA 98057–3356;
757–57–0066, R1: At the applicable time the requirements of AD 90–23–06, AD 91– phone: 425–917–6478; fax: 425–917–6590;
specified in paragraph 1.E., ‘‘Compliance,’’ of 22–51, and AD 2005–07–08 for that slat email: lu.lu@faa.gov.
SASB 757–57–0066, R1, do the applicable wedge. (2) For service information identified in
actions specified in paragraphs (i)(4)(i) and this AD, contact Boeing Commercial
(i)(4)(ii) of this AD. (m) Parts Installation Limitation
Airplanes, Attention: Contractual & Data
(i) For any class 3 disbond repair with a As of the effective date of this AD: A Services (C&DS), 2600 Westminster Blvd.,
repair doubler common to the aft edge of the replacement type A wedge may be installed MC 110–SK57, Seal Beach, CA 90740–5600;
trailing edge slat wedge; for any previously provided that the initial and repetitive
telephone 562–797–1717; Internet https://
accomplished repair with a repair doubler inspections specified in paragraph (h) and (i)
www.myboeingfleet.com. You may view this
common to the aft edge of the trailing edge of this AD are done within the applicable
referenced service information at the FAA,
slat wedge; and for any class 4 disbond compliance times specified in paragraph (h)
Transport Airplane Directorate, 1601 Lind
repair: Do an ultrasonic low frequency bond and (i) of this AD and all applicable related
Avenue SW., Renton, WA. For information
test inspection or a TTU inspection for any investigative and corrective actions are done
on the availability of this material at the
disbonding of the aft edge repaired areas; a within the applicable compliance times
FAA, call 425–227–1221.
detailed inspection for disbonds along the aft specified in paragraphs (h) and (i) of this AD.
edge of the repaired areas; and do all Issued in Renton, Washington, on April 5,
(n) Alternative Methods of Compliance 2017.
applicable related investigative and
(AMOCs)
corrective actions; in accordance with the Michael Kaszycki,
Accomplishment Instructions of SASB 757– (1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the Acting Manager, Transport Airplane
57–0066, R1, except as specified in paragraph Directorate, Aircraft Certification Service.
(j)(2) of this AD. Do all applicable related authority to approve AMOCs for this AD, if
investigative and corrective actions before requested using the procedures found in 14 [FR Doc. 2017–07440 Filed 4–12–17; 8:45 am]
further flight. Repeat the applicable CFR 39.19. In accordance with 14 CFR 39.19, BILLING CODE 4910–13–P
inspection on each type A trailing edge slat send your request to your principal inspector
wedge thereafter at the applicable interval or local Flight Standards District Office, as
specified in paragraph 1.E., ‘‘Compliance,’’ of appropriate. If sending information directly DEPARTMENT OF TRANSPORTATION
SASB 757–57–0066, R1. to the manager of the ACO, send it to the
(ii) For any class 3 disbond repair without attention of the person identified in Federal Aviation Administration
a repair doubler common to the aft edge of paragraph (o)(1) of this AD. Information may
the trailing edge slat wedge; and for any be emailed to: 9-ANM-LAACO-AMOC-
Requests@faa.gov.
14 CFR Part 71
previously accomplished repair without a
repair doubler common to the aft edge of the (2) Before using any approved AMOC, [Docket No. FAA–2017–0195; Airspace
trailing edge slat wedge: Do an ultrasonic low notify your appropriate principal inspector, Docket No. 16–ANM–14]
frequency bond test inspection, a tap test or lacking a principal inspector, the manager
inspection, or a TTU inspection for skin-to- of the local flight standards district office/ Proposed Amendment of Class E
core disbonds of the honeycomb area of the certificate holding district office. Airspace; Medford, OR
trailing edge slat wedge in the repaired area; (3) An AMOC that provides an acceptable
and do all applicable related investigative level of safety may be used for any repair, AGENCY: Federal Aviation
and corrective actions; in accordance with modification, or alteration required by this Administration (FAA), DOT.
the Accomplishment Instructions of SASB AD if it is approved by the Boeing ACTION: Notice of proposed rulemaking
757–57–0066, R1, except as specified in Commercial Airplanes Organization
Designation Authorization (ODA) that has (NPRM).
paragraph (j)(2) of this AD. Do all applicable
related investigative and corrective actions been authorized by the Manager, Seattle SUMMARY: This action proposes to
before further flight. Repeat the applicable ACO, to make those findings. To be
approved, the repair method, modification modify Class E airspace designated as
inspection on each type A trailing edge slat
wedge thereafter at the applicable interval deviation, or alteration deviation must meet an extension to a Class D or E surface
specified in paragraph 1.E., ‘‘Compliance,’’ of the certification basis of the airplane, and the area, modify Class E airspace extending
SASB 757–57–0066, R1. approval must specifically refer to this AD. upward from 700 feet above the surface,
(4) Except as required by paragraph (j)(2) and remove Class E airspace upward
nlaroche on DSK30NT082PROD with PROPOSALS
(j) Exceptions to Service Information of this AD: For service information that from 1,200 feet above the surface at
(1) Where paragraph 1.E., ‘‘Compliance,’’ of contains steps that are labeled as Required Rogue Valley International-Medford
SASB 757–57–0066, R1, specifies a for Compliance (RC), the provisions of Airport, Medford, OR. This action is
compliance time ‘‘after the Revision 1 date of paragraphs (n)(4)(i) and (n)(4)(ii) of this AD
this service bulletin,’’ this AD requires apply. necessary due to the proposed
compliance within the specified compliance (i) The steps labeled as RC, including decommissioning of the PUMIE locator
time after the effective date of this AD. substeps under an RC step and any figures outer marker and removal of the VHF
(2) If any disbonding is found during any identified in an RC step, must be done to Omnidirectional Range/Tactical Air
inspection required by this AD, and SASB comply with the AD. If a step or substep is Navigation (VORTAC) from the airspace
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Document Created: 2017-04-13 01:09:12
Document Modified: 2017-04-13 01:09:12
| 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 May 30, 2017. | |
| Contact | Lu Lu, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6577; fax: 425-917-6478; email: [email protected] | |
| FR Citation | 82 FR 17773 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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