80 FR 32066 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 108 (June 5, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 108 (June 5, 2015)
| Page Range | 32066-32069 | |
| FR Document | 2015-13328 |
[Federal Register Volume 80, Number 108 (Friday, June 5, 2015)] [Proposed Rules] [Pages 32066-32069] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-13328] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-1421; Directorate Identifier 2014-NM-177-AD] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 767-300 and -300F series airplanes. This proposed AD was prompted by reports of fatigue cracking on airplanes with Aviation Partners Boeing winglets installed. This proposed AD would require a high frequency eddy current (HFEC) inspection for cracking of the lower outboard wing skin, and repair or modification if necessary. This proposed AD would also require one of three follow-on actions: Repeating the HFEC inspections; modifying certain internal stringers and oversizing and plugging the existing fastener holes of the lower wing; or modifying the external doubler/ tripler and doing repetitive post-modification inspections. We are proposing this AD to prevent fatigue cracking in the lower outboard wing skin, which could result in failure and subsequent separation of the wing and winglet and consequent reduced controllability of the airplane. DATES: We must receive comments on this proposed AD by July 20, 2015. 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 proposed AD, contact Aviation Partners Boeing, 2811 S. 102nd Street, Suite 200, Seattle, WA 98168; telephone 206-762-1171; Internet https://www.aviationpartnersboeing.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. 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-2015- 1421; 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: Allen Rauschendorfer, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6487; 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 proposal. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2015-1421; Directorate Identifier 2014-NM-177-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 [[Page 32067]] closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We have received reports of fatigue cracking in the lower outboard wing skin at the inboard fastener of stringer L-9.5 on Model 767-300 airplanes with Aviation Partners Boeing winglets installed. The cracks were found at the fastener holes common to the inboard end of the outboard stringer L-9.5 on the left- and right-hand wings. Investigation revealed that these were fatigue cracks related to Aviation Partners Boeing STC ST01920SE winglet retrofit kit installations. If not corrected, these cracks could extend to adjacent structure and could lead to reduced load carrying capability in the lower skin. Later investigation revealed more cracking along the lower wing skin as a result of fatigue due to higher-than-predicted fastener loads and skin stress peaking at the inboard end of stringer L-9.5. These conditions, if not corrected, could result in failure and subsequent separation of the wing and winglet, and consequent reduced controllability of the airplane. Related Service Information Under 1 CFR Part 51 We reviewed Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 7, dated November 4, 2014. The service information describes procedures for inspecting for cracking of the external surface of the lower outboard wing skin, and repair or modification if necessary. The service information also includes certain follow-on actions. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this NPRM. 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 ``Difference Between this Proposed Rule and the Service Information.'' Difference Between Proposed Rule and Service Information Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 7, dated November 4, 2014, specifies to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions 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 140 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs--Required Actions ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- Inspection............................ 3 work-hours x $85 per $0 $255 $35,700 hour = $255. ---------------------------------------------------------------------------------------------------------------- Estimated Costs--Optional Actions ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Repetitive inspections........................ 3 work-hours x $85 per hour = $0 $255 $255 per inspection cycle. Repair/Modification........................... 262 work-hours x $85 per hour = 0 22,270 $22,270. Terminating Modification...................... 262 work-hours x $85 per hour = 0 22,270 $22,270. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We 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 [[Page 32068]] 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-2015-1421; Directorate Identifier 2014-NM-177-AD. (a) Comments Due Date We must receive comments by July 20, 2015. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 767-300 and -300F series airplanes, certificated in any category, with Aviation Partners Boeing winglets installed; as identified in Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 7, dated November 4, 2014. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Unsafe Condition This AD was prompted by reports of fatigue cracking in the lower outboard wing skin at the inboard fastener of stringer L-9.5 on airplanes with winglets installed per Supplemental Type Certificate ST01920SE. We are issuing this AD to prevent fatigue cracking in the lower outboard wing skin, which could result in failure and subsequent separation of the wing and winglet and consequent reduced controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection and Repair or Modification and Post-Repair or Modification Inspections At the applicable time specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767- 57-010, Revision 7, dated November 4, 2014, except as required by paragraph (j) of this AD: Do a high frequency eddy current (HFEC) inspection for cracking of the lower outboard wing skin, as specified in paragraph (g)(1) or (g)(2) of this AD, as applicable. (1) For Groups 1 and 2 airplanes: Do an internal HFEC inspection at the inboard fasteners of stringer L-9.5, in accordance with PART 1 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 7, dated November 4, 2014; and do the applicable actions required by paragraph (g)(1)(i) or (g)(1)(ii) of this AD. (i) If any cracking is found, before further flight, do the repair or modification specified in paragraph (h) of this AD. (ii) If no cracking is found, do the applicable actions specified in paragraph (g)(1)(ii)(A), (g)(1)(ii)(B), or (g)(1)(ii)(C) of this AD at the time specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767- 57-010, Revision 7, dated November 4, 2014. (A) Repeat the HFEC inspection. (B) Do a preventive modification of the external doubler/tripler filler and stringer L-6.5, in accordance with PART 2 through 6, or PART 8, as applicable, of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 7, dated November 4, 2014. If PART 8 was done, do repetitive HFEC inspections for cracking of the lower outboard wing skin common to the external doubler/tripler repair, in accordance with PART 9 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 7, dated November 4, 2014, except as required by paragraph (j)(2) of this AD. If any cracking is found: Before further flight, do a repair or modification using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (C) Do a repair or modification in accordance with PART 8, and do repetitive HFEC inspections for cracking of the lower outboard wing skin common to the external doubler/tripler repair, in accordance with PART 9 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 7, dated November 4, 2014, except as required by paragraph (j)(2) of this AD. If any cracking is found: Before further flight, do a repair or modification using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (2) For Group 3 airplanes: Do an internal HFEC inspection at the inboard fasteners of stringer L-9.5, in accordance with PART 7a of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 7, dated November 4, 2014. Do an external HFEC inspection at the inboard fasteners of stringer L-6.5 in accordance with PART 7b of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 7, dated November 4, 2014; and do the applicable actions required by paragraph (g)(2)(i) or (g)(2)(ii) of this AD, at the time specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 7, dated November 4, 2014. (i) If any cracking is found: Before further flight, do a repair or modification using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (ii) If no cracking is found: Repeat the HFEC inspections at the time specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 7, dated November 4, 2014. (h) Terminating Modification and Repair and Post-Repair or Modification Inspections Modification of the external doubler/tripler filler and stringer L-6.5, in accordance with PART 2 through PART 6, or repair or modification in accordance with PART 8, of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57- 010, Revision 7, dated November 4, 2014, except as required by paragraph (j)(2) of this AD, terminates the repetitive inspections specified in paragraph (g)(1)(ii)(A) of this AD, provided the conditions specified in paragraphs (h)(1) and (h)(2) of this AD are met. If any cracking is found: Before further flight, do a repair or modification using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (1) The repair or modification must be done within the applicable time specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 7, dated November 4, 2014, except as required by paragraph (j) of this AD. (2) Repetitive post-repair or modification inspections for cracking of the lower outboard wing skin common to the external doubler/tripler repair must be done in accordance with PART 9 of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 7, dated November 4, 2014, within the applicable time specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 7, dated November 4, 2014, except as required by paragraph (j)(2) of this AD. If any cracking is found: Before further flight, do a repair or modification using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (i) Credit for Previous Actions This paragraph provides credit for the actions specified in paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using the service information identified in paragraph (i)(1), (i)(2), or (i)(3) of this AD; which is not incorporated by reference in this AD. (1) Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 2, dated January 23, 2014. (2) Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 4, dated April 22, 2014. (3) Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 6, dated August 15, 2014. (j) Exceptions to Service Information Specifications (1) Where paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 7, dated November [[Page 32069]] 4, 2014, specifies a compliance time ``after the initial issue date on this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Where Aviation Partners Boeing Service Bulletin AP767-57- 010, Revision 7, dated November 4, 2014, specifies to contact Boeing for repair instructions: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, 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 (l)(1) of this AD. Information may be emailed to: [email protected]. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair 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. For a repair method to be approved the repair must meet the certification basis of the airplane and the approval must specifically refer to this AD. (l) Related Information (1) For more information about this AD, contact Allen Rauschendorfer, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6487; fax: 425-917-6590; email: [email protected]. (2) For service information identified in this AD, contact Aviation Partners Boeing, 2811 S. 102nd Street, Suite 200, Seattle, WA 98168; telephone 206-762-1171; Internet https://www.aviationpartnersboeing.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 May 13, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-13328 Filed 6-4-15; 8:45 am] BILLING CODE 4910-13-P
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March 17, 1997: At the later of the times searching for and locating Docket No. FAA– 11.43 and 11.45, by any of the following
specified by paragraphs (h)(3)(i) and (h)(3)(ii) 2015–1422. methods:
of this AD: (2) For service information identified in • Federal eRulemaking Portal: Go to
(i) Within 24,900 flight cycles or 49,800 this AD, contact Airbus, Airworthiness
flight hours, whichever occurs first, since the Office—EIAS, 1 Rond Point Maurice http://www.regulations.gov. Follow the
modification specified in Airbus Service Bellonte, 31707 Blagnac Cedex, France; instructions for submitting comments.
Bulletin A320–57–1017, dated September 3, telephone +33 5 61 93 36 96; fax +33 5 61 • Fax: 202–493–2251.
1991; or Airbus Service Bulletin A320–57– 93 44 51; email account.airworth-eas@ • Mail: U.S. Department of
1017, Revision 01, dated March 17, 1997, was airbus.com; Internet http://www.airbus.com. Transportation, Docket Operations,
accomplished. You may view this service information at the M–30, West Building Ground Floor,
(ii) Within 850 flight cycles or 1,700 flight FAA, Transport Airplane Directorate, 1601 Room W12–140, 1200 New Jersey
hours, whichever occurs first, after the Lind Avenue SW., Renton, WA. For
information on the availability of this
Avenue SE., Washington, DC 20590.
effective date of this AD.
(4) For Configuration 4 airplanes, having material at the FAA, call 425–227–1221. • Hand Delivery: Deliver to Mail
MSN 0080 to 0155 inclusive: address above between 9 a.m. and 5
Issued in Renton, Washington, on May 18,
At the later of the times specified in p.m., Monday through Friday, except
2015.
paragraphs (h)(4)(i) or (h)(4)(ii) of this AD: Federal holidays.
John P. Piccola, Jr.,
(i) Before exceeding 54,300 flight cycles or For service information identified in
108,600 flight hours, whichever occurs first Acting Manager, Transport Airplane this proposed AD, contact Aviation
since airplane first flight. Directorate, Aircraft Certification Service.
Partners Boeing, 2811 S. 102nd Street,
(ii) Within 60 days after the effective date [FR Doc. 2015–13342 Filed 6–4–15; 8:45 am] Suite 200, Seattle, WA 98168; telephone
of this AD. BILLING CODE 4910–13–P 206–762–1171; Internet https://
(i) Repair www.aviationpartnersboeing.com. You
If any crack is detected during any may view this referenced service
DEPARTMENT OF TRANSPORTATION
inspection required by paragraph (g) of this information at the FAA, Transport
AD: Before further flight, repair using a Airplane Directorate, 1601 Lind Avenue
method approved by the Manager,
Federal Aviation Administration
SW., Renton, WA. For information on
International Branch, ANM–116, Transport the availability of this material at the
Airplane Directorate, FAA; or the European 14 CFR Part 39
Aviation Safety Agency (EASA); or Airbus’s
FAA, call 425–227–1221.
[Docket No. FAA–2015–1421; Directorate
EASA Design Organization Approval (DOA). Identifier 2014–NM–177–AD] Examining the AD Docket
(j) Other FAA AD Provisions RIN 2120–AA64 You may examine the AD docket on
The following provisions also apply to this the Internet at http://
AD: Airworthiness Directives; The Boeing www.regulations.gov by searching for
(1) Alternative Methods of Compliance Company Airplanes and locating Docket No. FAA–2015–
(AMOCs): The Manager, International 1421; or in person at the Docket
Branch, ANM–116, FAA, has the authority to AGENCY: Federal Aviation
Administration (FAA), DOT. Management Facility between 9 a.m.
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. and 5 p.m., Monday through Friday,
ACTION: Notice of proposed rulemaking
In accordance with 14 CFR 39.19, send your except Federal holidays. The AD docket
(NPRM). contains this proposed AD, the
request to your principal inspector or local
Flight Standards District Office, as SUMMARY: We propose to adopt a new regulatory evaluation, any comments
appropriate. If sending information directly airworthiness directive (AD) for certain received, and other information. The
to the International Branch, send it to ATTN: The Boeing Company Model 767–300 street address for the Docket Office
Sanjay Ralhan, Aerospace Engineer, (phone: 800–647–5527) is in the
International Branch, ANM–116, Transport
and –300F series airplanes. This
proposed AD was prompted by reports ADDRESSES section. Comments will be
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356; of fatigue cracking on airplanes with available in the AD docket shortly after
telephone 425–227–1405; fax 425–227–1149. Aviation Partners Boeing winglets receipt.
Information may be emailed to: 9-ANM-116- installed. This proposed AD would FOR FURTHER INFORMATION CONTACT:
AMOC-REQUESTS@faa.gov. Before using require a high frequency eddy current Allen Rauschendorfer, Aerospace
any approved AMOC, notify your appropriate (HFEC) inspection for cracking of the Engineer, Airframe Branch, ANM–120S,
principal inspector, or lacking a principal lower outboard wing skin, and repair or FAA, Seattle Aircraft Certification
inspector, the manager of the local flight modification if necessary. This
standards district office/certificate holding Office, 1601 Lind Avenue SW., Renton,
district office. The AMOC approval letter
proposed AD would also require one of WA 98057–3356; phone: 425–917–6487;
must specifically reference this AD. three follow-on actions: Repeating the fax: 425–917–6590; email:
(2) Contacting the Manufacturer: As of the HFEC inspections; modifying certain Allen.Rauschendorfer@faa.gov.
effective date of this AD, for any requirement internal stringers and oversizing and SUPPLEMENTARY INFORMATION:
in this AD to obtain corrective actions from plugging the existing fastener holes of
a manufacturer, the action must be the lower wing; or modifying the Comments Invited
accomplished using a method approved by external doubler/tripler and doing
the Manager, International Branch, ANM– We invite you to send any written
repetitive post-modification inspections. relevant data, views, or arguments about
116, Transport Airplane Directorate, FAA; or
We are proposing this AD to prevent this proposal. Send your comments to
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
the EASA; or Airbus’s EASA DOA. If
approved by the DOA, the approval must fatigue cracking in the lower outboard an address listed under the ADDRESSES
include the DOA-authorized signature. wing skin, which could result in failure section. Include ‘‘Docket No. FAA–
and subsequent separation of the wing 2015–1421; Directorate Identifier 2014–
(k) Related Information
and winglet and consequent reduced NM–177–AD’’ at the beginning of your
(1) Refer to Mandatory Continuing controllability of the airplane.
Airworthiness Information (MCAI) EASA
comments. We specifically invite
DATES: We must receive comments on comments on the overall regulatory,
Airworthiness Directive 2014–0069, dated
March 19, 2014, for related information. This this proposed AD by July 20, 2015. economic, environmental, and energy
MCAI may be found in the AD docket on the ADDRESSES: You may send comments, aspects of this proposed AD. We will
Internet at http://www.regulations.gov by using the procedures found in 14 CFR consider all comments received by the
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under the criteria of the Regulatory AD: Do a high frequency eddy current (i) If any cracking is found: Before further
Flexibility Act. (HFEC) inspection for cracking of the lower flight, do a repair or modification using a
outboard wing skin, as specified in paragraph method approved in accordance with the
List of Subjects in 14 CFR Part 39 (g)(1) or (g)(2) of this AD, as applicable. procedures specified in paragraph (k) of this
(1) For Groups 1 and 2 airplanes: Do an AD.
Air transportation, Aircraft, Aviation (ii) If no cracking is found: Repeat the
internal HFEC inspection at the inboard
safety, Incorporation by reference, fasteners of stringer L–9.5, in accordance HFEC inspections at the time specified in
Safety. with PART 1 of the Accomplishment paragraph 1.E., ‘‘Compliance,’’ of Aviation
Instructions of Aviation Partners Boeing Partners Boeing Service Bulletin AP767–57–
The Proposed Amendment 010, Revision 7, dated November 4, 2014.
Service Bulletin AP767–57–010, Revision 7,
Accordingly, under the authority dated November 4, 2014; and do the
(h) Terminating Modification and Repair
delegated to me by the Administrator, applicable actions required by paragraph
and Post-Repair or Modification Inspections
the FAA proposes to amend 14 CFR part (g)(1)(i) or (g)(1)(ii) of this AD.
(i) If any cracking is found, before further Modification of the external doubler/tripler
39 as follows: filler and stringer L–6.5, in accordance with
flight, do the repair or modification specified
in paragraph (h) of this AD. PART 2 through PART 6, or repair or
PART 39—AIRWORTHINESS modification in accordance with PART 8, of
(ii) If no cracking is found, do the
DIRECTIVES the Accomplishment Instructions of Aviation
applicable actions specified in paragraph
(g)(1)(ii)(A), (g)(1)(ii)(B), or (g)(1)(ii)(C) of this Partners Boeing Service Bulletin AP767–57–
■ 1. The authority citation for part 39 010, Revision 7, dated November 4, 2014,
AD at the time specified in paragraph 1.E.,
continues to read as follows: ‘‘Compliance,’’ of Aviation Partners Boeing except as required by paragraph (j)(2) of this
Authority: 49 U.S.C. 106(g), 40113, 44701. Service Bulletin AP767–57–010, Revision 7, AD, terminates the repetitive inspections
dated November 4, 2014. specified in paragraph (g)(1)(ii)(A) of this AD,
§ 39.13 [Amended] (A) Repeat the HFEC inspection. provided the conditions specified in
■ 2. The FAA amends § 39.13 by adding (B) Do a preventive modification of the paragraphs (h)(1) and (h)(2) of this AD are
external doubler/tripler filler and stringer L– met. If any cracking is found: Before further
the following new airworthiness
6.5, in accordance with PART 2 through 6, flight, do a repair or modification using a
directive (AD): method approved in accordance with the
or PART 8, as applicable, of the
The Boeing Company: Docket No. FAA– Accomplishment Instructions of Aviation procedures specified in paragraph (k) of this
2015–1421; Directorate Identifier 2014– Partners Boeing Service Bulletin AP767–57– AD.
NM–177–AD. 010, Revision 7, dated November 4, 2014. If (1) The repair or modification must be
PART 8 was done, do repetitive HFEC done within the applicable time specified in
(a) Comments Due Date paragraph 1.E., ‘‘Compliance,’’ of Aviation
inspections for cracking of the lower
We must receive comments by July 20, outboard wing skin common to the external Partners Boeing Service Bulletin AP767–57–
2015. doubler/tripler repair, in accordance with 010, Revision 7, dated November 4, 2014,
PART 9 of the Accomplishment Instructions except as required by paragraph (j) of this
(b) Affected ADs AD.
of Aviation Partners Boeing Service Bulletin
None. AP767–57–010, Revision 7, dated November (2) Repetitive post-repair or modification
4, 2014, except as required by paragraph (j)(2) inspections for cracking of the lower
(c) Applicability
of this AD. If any cracking is found: Before outboard wing skin common to the external
This AD applies to The Boeing Company doubler/tripler repair must be done in
further flight, do a repair or modification
Model 767–300 and –300F series airplanes, accordance with PART 9 of Aviation Partners
using a method approved in accordance with
certificated in any category, with Aviation Boeing Service Bulletin AP767–57–010,
the procedures specified in paragraph (k) of
Partners Boeing winglets installed; as Revision 7, dated November 4, 2014, within
this AD.
identified in Aviation Partners Boeing the applicable time specified in paragraph
(C) Do a repair or modification in
Service Bulletin AP767–57–010, Revision 7, 1.E., ‘‘Compliance,’’ of Aviation Partners
accordance with PART 8, and do repetitive
dated November 4, 2014. Boeing Service Bulletin AP767–57–010,
HFEC inspections for cracking of the lower
Revision 7, dated November 4, 2014, except
(d) Subject outboard wing skin common to the external
as required by paragraph (j)(2) of this AD. If
Air Transport Association (ATA) of doubler/tripler repair, in accordance with
any cracking is found: Before further flight,
America Code 57, Wings. PART 9 of the Accomplishment Instructions
do a repair or modification using a method
of Aviation Partners Boeing Service Bulletin
approved in accordance with the procedures
(e) Unsafe Condition AP767–57–010, Revision 7, dated November specified in paragraph (k) of this AD.
This AD was prompted by reports of 4, 2014, except as required by paragraph (j)(2)
fatigue cracking in the lower outboard wing of this AD. If any cracking is found: Before (i) Credit for Previous Actions
skin at the inboard fastener of stringer L–9.5 further flight, do a repair or modification This paragraph provides credit for the
on airplanes with winglets installed per using a method approved in accordance with actions specified in paragraphs (g) and (h) of
Supplemental Type Certificate ST01920SE. the procedures specified in paragraph (k) of this AD, if those actions were performed
We are issuing this AD to prevent fatigue this AD. before the effective date of this AD using the
cracking in the lower outboard wing skin, (2) For Group 3 airplanes: Do an internal service information identified in paragraph
which could result in failure and subsequent HFEC inspection at the inboard fasteners of (i)(1), (i)(2), or (i)(3) of this AD; which is not
separation of the wing and winglet and stringer L–9.5, in accordance with PART 7a incorporated by reference in this AD.
consequent reduced controllability of the of the Accomplishment Instructions of (1) Aviation Partners Boeing Service
airplane. Aviation Partners Boeing Service Bulletin Bulletin AP767–57–010, Revision 2, dated
AP767–57–010, Revision 7, dated November January 23, 2014.
(f) Compliance 4, 2014. Do an external HFEC inspection at (2) Aviation Partners Boeing Service
Comply with this AD within the the inboard fasteners of stringer L–6.5 in
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Bulletin AP767–57–010, Revision 4, dated
compliance times specified, unless already accordance with PART 7b of the April 22, 2014.
done. Accomplishment Instructions of Aviation (3) Aviation Partners Boeing Service
Partners Boeing Service Bulletin AP767–57– Bulletin AP767–57–010, Revision 6, dated
(g) Inspection and Repair or Modification 010, Revision 7, dated November 4, 2014; August 15, 2014.
and Post-Repair or Modification Inspections and do the applicable actions required by
At the applicable time specified in paragraph (g)(2)(i) or (g)(2)(ii) of this AD, at (j) Exceptions to Service Information
paragraph 1.E., ‘‘Compliance,’’ of Aviation the time specified in paragraph 1.E., Specifications
Partners Boeing Service Bulletin AP767–57– ‘‘Compliance,’’ of Aviation Partners Boeing (1) Where paragraph 1.E., ‘‘Compliance,’’ of
010, Revision 7, dated November 4, 2014, Service Bulletin AP767–57–010, Revision 7, Aviation Partners Boeing Service Bulletin
except as required by paragraph (j) of this dated November 4, 2014. AP767–57–010, Revision 7, dated November
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![Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules 32069
4, 2014, specifies a compliance time ‘‘after DEPARTMENT OF TRANSPORTATION www.lockheedmartin.com/ams/tools/
the initial issue date on this service bulletin,’’ TechPubs.html. You may view this
this AD requires compliance within the Federal Aviation Administration referenced service information at the
specified compliance time after the effective FAA, Transport Airplane Directorate,
date of this AD. 14 CFR Part 39 1601 Lind Avenue SW., Renton, WA.
(2) Where Aviation Partners Boeing Service For information on the availability of
[Docket No. FAA–2015–1419; Directorate
Bulletin AP767–57–010, Revision 7, dated this material at the FAA, call 425–227–
Identifier 2014–NM–183–AD]
November 4, 2014, specifies to contact 1221.
Boeing for repair instructions: Before further RIN 2120–AA64
flight, repair the cracking using a method Examining the AD Docket
approved in accordance with the procedures Airworthiness Directives; Lockheed You may examine the AD docket on
specified in paragraph (k) of this AD. Martin Corporation/Lockheed Martin the Internet at http://
Aeronautics Company Airplanes www.regulations.gov by searching for
(k) Alternative Methods of Compliance
(AMOCs) AGENCY: Federal Aviation and locating Docket No. FAA–2015–
Administration (FAA), DOT. 1419; or in person at the Docket
(1) The Manager, Seattle Aircraft Management Facility between 9 a.m.
Certification Office (ACO), FAA, has the ACTION: Notice of proposed rulemaking
and 5 p.m., Monday through Friday,
authority to approve AMOCs for this AD, if (NPRM). except Federal holidays. The AD docket
requested using the procedures found in 14 contains this proposed AD, the
CFR 39.19. In accordance with 14 CFR 39.19, SUMMARY: We propose to adopt a new
airworthiness directive (AD) for all regulatory evaluation, any comments
send your request to your principal inspector received, and other information. The
or local Flight Standards District Office, as Lockheed Martin Corporation/Lockheed
Martin Aeronautics Company Model street address for the Docket Office
appropriate. If sending information directly (phone: 800–647–5527) is in the
to the manager of the ACO, send it to the 188 series airplanes. This proposed AD
was prompted by an evaluation by the ADDRESSES section. Comments will be
attention of the person identified in available in the AD docket shortly after
paragraph (l)(1) of this AD. Information may design approval holder (DAH)
indicating the left and right lower receipt.
be emailed to: 9-ANM-Seattle-ACO-AMOC-
surface panels of the wings are subject FOR FURTHER INFORMATION CONTACT: Carl
Requests@faa.gov.
(2) Before using any approved AMOC, to widespread fatigue damage (WFD). Gray, Aerospace Engineer, Airframe
notify your appropriate principal inspector, This proposed AD would require Branch, ACE–117A, FAA, Atlanta
or lacking a principal inspector, the manager repetitive inspections for cracking at Aircraft Certification Office (ACO), 1701
of the local flight standards district office/ these panels, and repair if necessary. Columbia Avenue, College Park, GA
certificate holding district office. The proposed AD would also require a 30337; phone: 404–474–5554; fax: 404–
(3) An AMOC that provides an acceptable one-time bolt-hole eddy current 474–5605; email: carl.w.gray@faa.gov.
level of safety may be used for any repair inspection of all open holes for SUPPLEMENTARY INFORMATION:
required by this AD if it is approved by the cracking, repair if necessary, and Comments Invited
Boeing Commercial Airplanes Organization modification. We are proposing this AD
Designation Authorization (ODA) that has to prevent fatigue cracking of the left We invite you to send any written
been authorized by the Manager, Seattle and right lower surface panels of the relevant data, views, or arguments about
ACO, to make those findings. For a repair wings, which could result in reduced this proposal. Send your comments to
method to be approved the repair must meet structural integrity of the airplane. an address listed under the ADDRESSES
the certification basis of the airplane and the section. Include ‘‘Docket No. FAA–
DATES: We must receive comments on
approval must specifically refer to this AD. 2015–1419; Directorate Identifier 2014–
this proposed AD by July 20, 2015. NM–183–AD’’ at the beginning of your
(l) Related Information ADDRESSES: You may send comments, comments. We specifically invite
(1) For more information about this AD, using the procedures found in 14 CFR comments on the overall regulatory,
contact Allen Rauschendorfer, Aerospace 11.43 and 11.45, by any of the following economic, environmental, and energy
Engineer, Airframe Branch, ANM–120S, methods: aspects of this proposed AD. We will
FAA, Seattle Aircraft Certification Office, • Federal eRulemaking Portal: Go to consider all comments received by the
1601 Lind Avenue SW., Renton, WA 98057– http://www.regulations.gov. Follow the closing date and may amend this
3356; phone: 425–917–6487; fax: 425–917– instructions for submitting comments. proposed AD because of those
6590; email: Allen.Rauschendorfer@faa.gov. • Fax: 202–493–2251. comments.
(2) For service information identified in • Mail: U.S. Department of We will post all comments we
this AD, contact Aviation Partners Boeing, Transportation, Docket Operations, M– receive, without change, to http://
2811 S. 102nd Street, Suite 200, Seattle, WA 30, West Building Ground Floor, Room www.regulations.gov, including any
98168; telephone 206–762–1171; Internet W12–140, 1200 New Jersey Avenue SE., personal information you provide. We
https://www.aviationpartnersboeing.com. Washington, DC 20590. will also post a report summarizing each
You may view this referenced service • Hand Delivery: Deliver to Mail substantive verbal contact we receive
information at the FAA, Transport Airplane address above between 9 a.m. and 5 about this proposed AD.
Directorate, 1601 Lind Avenue SW., Renton, p.m., Monday through Friday, except
WA. For information on the availability of Federal holidays. Discussion
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
this material at the FAA, call 425–227–1221. For service information identified in Structural fatigue damage is
this proposed AD, contact Lockheed progressive. It begins as minute cracks,
Issued in Renton, Washington, on May 13,
2015.
Martin Corporation/Lockheed Martin and those cracks grow under the action
Aeronautics Company, Airworthiness of repeated stresses. This can happen
Jeffrey E. Duven, Office, Dept. 6A0M, Zone 0252, Column because of normal operational
Manager, Transport Airplane Directorate, P–58, 86 S. Cobb Drive, Marietta, GA conditions and design attributes, or
Aircraft Certification Service. 30063; telephone 770–494–5444; fax because of isolated situations or
[FR Doc. 2015–13328 Filed 6–4–15; 8:45 am] 770–494–5445; email ams.portal@ incidents such as material defects, poor
BILLING CODE 4910–13–P lmco.com; Internet http:// fabrication quality, or corrosion pits,
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Document Created: 2015-12-15 15:20:37
Document Modified: 2015-12-15 15:20:37
| 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 July 20, 2015. | |
| Contact | Allen Rauschendorfer, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6487; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 80 FR 32066 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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