81 FR 10533 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 40 (March 1, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 40 (March 1, 2016)
| Page Range | 10533-10535 | |
| FR Document | 2016-03695 |
[Federal Register Volume 81, Number 40 (Tuesday, March 1, 2016)] [Proposed Rules] [Pages 10533-10535] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-03695] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-3700; Directorate Identifier 2015-NM-171-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 and -200CB series airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that the lap splices at stringer (S)-14R, lower fastener row, are subject to widespread fatigue damage (WFD). This proposed AD would require repetitive external dual frequency eddy current (DFEC) or internal high frequency eddy current (HFEC) inspections of the lap splice, inner skin fasteners, at S-14R, station (STA) 440 through STA 540, and corrective action if necessary. We are proposing this AD to detect and correct cracking of the fuselage skin lap splice. Such cracking could result in reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by April 15, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone: 206-544-5000, extension 1; fax: 206-766-5680; Internet: https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 3700. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 3700; 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: Eric Schrieber, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, California 90712- 4137; phone: 562-627-5348; fax: 562-627-5210; 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-2016-3700; Directorate Identifier 2015-NM-171-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion Structural fatigue damage is progressive. It begins as minute cracks, and those cracks grow under the action of repeated stresses. This can happen because of normal operational conditions and design attributes, or because of isolated situations or incidents such as material defects, poor fabrication quality, or corrosion pits, dings, or scratches. Fatigue damage can occur locally, in small areas or structural design details, or globally. Global fatigue damage is general degradation of large areas of structure with similar structural details and stress levels. Multiple-site damage is global damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Global damage can also occur in multiple elements such as adjacent frames or stringers. Multiple- site-damage and multiple-element-damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane, in a condition known as WFD. As an airplane ages, WFD will likely occur, and will certainly occur if the airplane is operated long enough without any intervention. [[Page 10534]] The FAA's WFD final rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent structural failure due to WFD throughout the operational life of certain existing transport category airplanes and all of these airplanes that will be certificated in the future. For existing and future airplanes subject to the WFD rule, the rule requires that DAHs establish a limit of validity (LOV) of the engineering data that support the structural maintenance program. Operators affected by the WFD rule may not fly an airplane beyond its LOV, unless an extended LOV is approved. The WFD rule (75 FR 69746, November 15, 2010) does not require identifying and developing maintenance actions if the DAHs can show that such actions are not necessary to prevent WFD before the airplane reaches the LOV. Many LOVs, however, do depend on accomplishment of future maintenance actions. As stated in the WFD rule, any maintenance actions necessary to reach the LOV will be mandated by airworthiness directives through separate rulemaking actions. In the context of WFD, this action is necessary to enable DAHs to propose LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. This approach allows for an implementation strategy that provides flexibility to DAHs in determining the timing of service information development (with FAA approval), while providing operators with certainty regarding the LOV applicable to their airplanes. We have received reports indicating that the lap splices at S-14R, lower fastener row, are subject to WFD. This condition, if not corrected, could result in cracking of the fuselage skin lap splice and potential reduced structural integrity of the airplane. Related Service Information Under 1 CFR Part 51 The Boeing Company has issued Boeing Service Bulletin 757-53A0102, dated October 8, 2015. The service information describes procedures for performing repetitive external DFEC or HFEC inspections of the lap splice, inner skin fasteners, at S-14R, STA 440--STA 540, and corrective action if necessary. 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 accomplishment of the actions specified in the service information described previously, except as discussed under ``Differences Between this Proposed AD and the Service Information.'' Differences Between This Proposed AD and the Service Information Boeing Alert Service Bulletin 757-53A0102, dated October 8, 2015, 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 572 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Option 1: External DFEC 4 work-hours x $85 per $0 $340 per $194,480 per inspection. hour = $340 per inspection cycle. inspection cycle. inspection cycle. Option 2: Internal HFEC 10 work-hours x $85 per $0 $850 per $486,200 per inspection. hour = $850 per inspection cycle. inspection cycle. inspection cycle. ---------------------------------------------------------------------------------------------------------------- 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 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, [[Page 10535]] 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-2016-3700; Directorate Identifier 2015-NM-171-AD. (a) Comments Due Date We must receive comments by April 15, 2016. (b) Affected ADs None. (c) Applicability This AD applies to all The Boeing Company Model 757-200 and - 200CB, series airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the lap splices at stringer (S)-14R, lower fastener row, are subject to widespread fatigue damage (WFD). We are issuing this AD to detect and correct cracking of the fuselage skin lap splice. Such cracking could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Initial Inspection At the applicable time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 757-53A0102, dated October 8, 2015, except as required by paragraph (h) of this AD: Do an external dual frequency eddy current inspection or internal high frequency eddy current inspection for cracking of the lap splice, inner skin lower fastener row, at S-14R, station (STA) 440 through STA 540, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757-53A0102, dated October 8, 2015. Repeat either inspection thereafter at the time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 757-53A0102, dated October 8, 2015. (h) Service Information Exceptions (1) Where Boeing Alert Service Bulletin 757-53A0102, dated October 8, 2015, specifies a compliance time ``after the original issue date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) The Condition column of paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 757-53A0102, dated October 8, 2015, refers to total flight cycles and total flight hours ``as of the original issue date of this service bulletin.'' This AD, however, applies to the airplanes with the specified total flight cycles or total flight hours as of the effective date of this AD. (i) Repair If any crack is found during any inspection required by this AD, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (j) of this AD. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (k) 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 ODA that has been authorized by the Manager, Los Angeles ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) Except as required by paragraph (h) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (j)(4)(i) and (j)(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. 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. (k) Related Information (1) For more information about this AD, contact Eric Schrieber, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, California 90712-4137; phone: 562-627-5348; fax: 562-627-5210; email: [email protected]. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone: 206-544- 5000, extension 1; fax: 206-766-5680; Internet: https://www.myboeingfleet.com. You may view this referenced service information at the FAA, 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 February 15, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-03695 Filed 2-29-16; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules 10533
§ 1214.8 Fiscal period. (S)–14R, lower fastener row, are subject FOR FURTHER INFORMATION CONTACT: Eric
Fiscal period means the period to widespread fatigue damage (WFD). Schrieber, Aerospace Engineer,
August 1 through July 31 or such other This proposed AD would require Airframe Branch, ANM–120L, FAA, Los
period as approved by the Secretary. repetitive external dual frequency eddy Angeles Aircraft Certification Office
■ 4. Subpart C—Rules and Regulations current (DFEC) or internal high (ACO), 3960 Paramount Boulevard,
is added to read as follows: frequency eddy current (HFEC) Lakewood, California 90712–4137;
inspections of the lap splice, inner skin phone: 562–627–5348; fax: 562–627–
Subpart C—Provisions Implementing fasteners, at S–14R, station (STA) 440 5210; email: eric.schrieber@faa.gov.
the Christmas Tree Promotion, through STA 540, and corrective action SUPPLEMENTARY INFORMATION:
Research, and Information Order if necessary. We are proposing this AD
to detect and correct cracking of the Comments Invited
§ 1214.520 Late payment and interest We invite you to send any written
fuselage skin lap splice. Such cracking
charges for past due assessments.
could result in reduced structural relevant data, views, or arguments about
(1) A late payment charge shall be integrity of the airplane. this proposal. Send your comments to
imposed on any producer or importer an address listed under the ADDRESSES
DATES: We must receive comments on
who fails to make timely remittance to this proposed AD by April 15, 2016. section. Include ‘‘Docket No. FAA–
the Board of the total assessments for 2016–3700; Directorate Identifier 2015–
ADDRESSES: You may send comments,
which such producer or importer is NM–171–AD’’ at the beginning of your
liable. The late payment charge will be using the procedures found in 14 CFR
11.43 and 11.45, by any of the following comments. We specifically invite
imposed on any assessments not comments on the overall regulatory,
methods:
received within 30 calendar days of the
• Federal eRulemaking Portal: Go to economic, environmental, and energy
date they are due. This one-time late http://www.regulations.gov. Follow the aspects of this proposed AD. We will
payment charge shall be $250 and instructions for submitting comments. consider all comments received by the
would be increased to $500 after 90 • Fax: 202–493–2251. closing date and may amend this
days of delinquency. • Mail: U.S. Department of proposed AD because of those
(2) In addition to the late payment Transportation, Docket Operations, M– comments.
charge, 1.5 percent per month interest 30, West Building Ground Floor, Room We will post all comments we
on the outstanding balance, including W12–140, 1200 New Jersey Avenue SE., receive, without change, to http://
any late payment charge and accrued Washington, DC 20590. www.regulations.gov, including any
interest, will be added to any accounts • Hand Delivery: Deliver to Mail personal information you provide. We
for which payment has not been address above between 9 a.m. and 5 will also post a report summarizing each
received by the Board within 30 p.m., Monday through Friday, except substantive verbal contact we receive
calendar days after the date the Federal holidays. about this proposed AD.
assessments are due. Such interest will For service information identified in
Discussion
continue to accrue monthly until the this proposed AD, contact Boeing
outstanding balance is paid to the Commercial Airplanes, Attention: Data Structural fatigue damage is
Board. & Services Management, P. O. Box 3707, progressive. It begins as minute cracks,
MC 2H–65, Seattle, WA 98124–2207; and those cracks grow under the action
Dated: February 25, 2016.
telephone: 206–544–5000, extension 1; of repeated stresses. This can happen
Elanor Starmer, because of normal operational
fax: 206–766–5680; Internet: https://
Acting Administrator. conditions and design attributes, or
www.myboeingfleet.com. You may view
[FR Doc. 2016–04469 Filed 2–29–16; 8:45 am] because of isolated situations or
this referenced service information at
BILLING CODE 3410–02–P the FAA, Transport Airplane incidents such as material defects, poor
Directorate, 1601 Lind Avenue SW., fabrication quality, or corrosion pits,
Renton, WA. For information on the dings, or scratches. Fatigue damage can
DEPARTMENT OF TRANSPORTATION availability of this material at the FAA, occur locally, in small areas or
call 425–227–1221. It is also available structural design details, or globally.
Federal Aviation Administration on the Internet at http:// Global fatigue damage is general
www.regulations.gov by searching for degradation of large areas of structure
14 CFR Part 39 and locating Docket No. FAA–2016– with similar structural details and stress
[Docket No. FAA–2016–3700; Directorate 3700. levels. Multiple-site damage is global
Identifier 2015–NM–171–AD] damage that occurs in a large structural
Examining the AD Docket element such as a single rivet line of a
RIN 2120–AA64 You may examine the AD docket on lap splice joining two large skin panels.
the Internet at http:// Global damage can also occur in
Airworthiness Directives; The Boeing
www.regulations.gov by searching for multiple elements such as adjacent
Company Airplanes
and locating Docket No. FAA–2016– frames or stringers. Multiple-site-
AGENCY: Federal Aviation 3700; or in person at the Docket damage and multiple-element-damage
Administration (FAA), DOT. Management Facility between 9 a.m. cracks are typically too small initially to
and 5 p.m., Monday through Friday, be reliably detected with normal
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
ACTION: Notice of proposed rulemaking
(NPRM). except Federal holidays. The AD docket inspection methods. Without
contains this proposed AD, the intervention, these cracks will grow,
SUMMARY: We propose to adopt a new regulatory evaluation, any comments and eventually compromise the
airworthiness directive (AD) for all The received, and other information. The structural integrity of the airplane, in a
Boeing Company Model 757–200 and street address for the Docket Office condition known as WFD. As an
–200CB series airplanes. This proposed (phone: 800–647–5527) is in the airplane ages, WFD will likely occur,
AD was prompted by an evaluation by ADDRESSES section. Comments will be and will certainly occur if the airplane
the design approval holder (DAH) available in the AD docket shortly after is operated long enough without any
indicating that the lap splices at stringer receipt. intervention.
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the FAA proposes to amend 14 CFR part specified compliance time after the effective 562–627–5348; fax: 562–627–5210; email:
39 as follows: date of this AD. eric.schrieber@faa.gov.
(2) The Condition column of paragraph (2) For service information identified in
PART 39—AIRWORTHINESS 1.E., ‘‘Compliance,’’ of Boeing Alert Service this AD, contact Boeing Commercial
DIRECTIVES Bulletin 757–53A0102, dated October 8, Airplanes, Attention: Data & Services
2015, refers to total flight cycles and total Management, P.O. Box 3707, MC 2H–65,
flight hours ‘‘as of the original issue date of Seattle, WA 98124–2207; telephone: 206–
■ 1. The authority citation for part 39
this service bulletin.’’ This AD, however, 544–5000, extension 1; fax: 206–766–5680;
continues to read as follows: applies to the airplanes with the specified Internet: https://www.myboeingfleet.com.
Authority: 49 U.S.C. 106(g), 40113, 44701. total flight cycles or total flight hours as of You may view this referenced service
the effective date of this AD. information at the FAA, Transport Airplane
§ 39.13 [Amended] Directorate, 1601 Lind Avenue SW., Renton,
(i) Repair
■ 2. The FAA amends § 39.13 by adding WA. For information on the availability of
If any crack is found during any inspection this material at the FAA, call 425–227–1221.
the following new airworthiness
required by this AD, before further flight,
directive (AD): repair using a method approved in Issued in Renton, Washington, on February
The Boeing Company: Docket No. FAA– accordance with the procedures specified in 15, 2016.
2016–3700; Directorate Identifier 2015– paragraph (j) of this AD. Michael Kaszycki,
NM–171–AD. Acting Manager, Transport Airplane
(j) Alternative Methods of Compliance
(a) Comments Due Date (AMOCs) Directorate, Aircraft Certification Service.
(1) The Manager, Los Angeles Aircraft [FR Doc. 2016–03695 Filed 2–29–16; 8:45 am]
We must receive comments by April 15,
2016. Certification Office (ACO), FAA, has the BILLING CODE 4910–13–P
authority to approve AMOCs for this AD, if
(b) Affected ADs requested using the procedures found in 14
None. CFR 39.19. In accordance with 14 CFR 39.19, DEPARTMENT OF TRANSPORTATION
send your request to your principal inspector
(c) Applicability or local Flight Standards District Office, as Federal Aviation Administration
This AD applies to all The Boeing appropriate. If sending information directly
Company Model 757–200 and –200CB, series to the manager of the ACO, send it to the 14 CFR Part 39
airplanes, certificated in any category. attention of the person identified in
paragraph (k) of this AD. Information may be [Docket No. FAA–2016–3987; Directorate
(d) Subject Identifier 2015–NM–165–AD]
emailed to: 9-ANM-LAACO-AMOC-
Air Transport Association (ATA) of Requests@faa.gov.
America Code 53, Fuselage. (2) Before using any approved AMOC, RIN 2120–AA64
notify your appropriate principal inspector,
(e) Unsafe Condition Airworthiness Directives; Dassault
or lacking a principal inspector, the manager
This AD was prompted by an evaluation by of the local flight standards district office/ Aviation Airplanes
the design approval holder (DAH) indicating certificate holding district office.
that the lap splices at stringer (S)–14R, lower (3) An AMOC that provides an acceptable
AGENCY: Federal Aviation
fastener row, are subject to widespread level of safety may be used for any repair, Administration (FAA), DOT.
fatigue damage (WFD). We are issuing this modification, or alteration required by this ACTION: Notice of proposed rulemaking
AD to detect and correct cracking of the AD if it is approved by the Boeing (NPRM).
fuselage skin lap splice. Such cracking could Commercial Airplanes ODA that has been
result in reduced structural integrity of the authorized by the Manager, Los Angeles SUMMARY: We propose to adopt a new
airplane. ACO, to make those findings. To be airworthiness directive (AD) for certain
approved, the repair method, modification Dassault Aviation Model FALCON 7X
(f) Compliance
deviation, or alteration deviation must meet airplanes. This proposed AD was
Comply with this AD within the the certification basis of the airplane, and the
compliance times specified, unless already approval must specifically refer to this AD.
prompted by a report of improperly
done. (4) Except as required by paragraph (h) of drilled bores, located on upper and
this AD: For service information that lower stiffener joints to the web at a
(g) Initial Inspection
contains steps that are labeled as Required certain frame. This proposed AD would
At the applicable time specified in for Compliance (RC), the provisions of require a one-time inspection of the
paragraph 1.E., ‘‘Compliance,’’ of Boeing paragraphs (j)(4)(i) and (j)(4)(ii) of this AD bores, and repair if necessary. We are
Alert Service Bulletin 757–53A0102, dated apply. proposing this AD to detect and correct
October 8, 2015, except as required by (i) The steps labeled as RC, including
paragraph (h) of this AD: Do an external dual an unsatisfactory bore that can
substeps under an RC step and any figures
frequency eddy current inspection or internal identified in an RC step, must be done to
adversely affect the structural integrity
high frequency eddy current inspection for comply with the AD. An AMOC is required of the airplane.
cracking of the lap splice, inner skin lower for any deviations to RC steps, including DATES: We must receive comments on
fastener row, at S–14R, station (STA) 440 substeps and identified figures. this proposed AD by April 15, 2016.
through STA 540, in accordance with the (ii) Steps not labeled as RC may be ADDRESSES: You may send comments,
Accomplishment Instructions of Boeing Alert deviated from using accepted methods in
Service Bulletin 757–53A0102, dated October accordance with the operator’s maintenance using the procedures found in 14 CFR
8, 2015. Repeat either inspection thereafter at or inspection program without obtaining 11.43 and 11.45, by any of the following
the time specified in paragraph 1.E., methods:
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
approval of an AMOC, provided the RC steps,
‘‘Compliance,’’ of Boeing Alert Service including substeps and identified figures, can • Federal eRulemaking Portal: Go to
Bulletin 757–53A0102, dated October 8, still be done as specified, and the airplane http://www.regulations.gov. Follow the
2015. can be put back in an airworthy condition. instructions for submitting comments.
(h) Service Information Exceptions (k) Related Information • Fax: 202–493–2251.
(1) Where Boeing Alert Service Bulletin (1) For more information about this AD,
• Mail: U.S. Department of
757–53A0102, dated October 8, 2015, contact Eric Schrieber, Aerospace Engineer, Transportation, Docket Operations,
specifies a compliance time ‘‘after the Airframe Branch, ANM–120L, FAA, Los M–30, West Building Ground Floor,
original issue date of this service bulletin,’’ Angeles ACO, 3960 Paramount Boulevard, Room W12–140, 1200 New Jersey
this AD requires compliance within the Lakewood, California 90712–4137; phone: Avenue SE., Washington, DC 20590.
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Document Created: 2018-02-02 14:59:53
Document Modified: 2018-02-02 14:59:53
| 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 April 15, 2016. | |
| Contact | Eric Schrieber, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, California 90712- 4137; phone: 562-627-5348; fax: 562-627-5210; email: [email protected] | |
| FR Citation | 81 FR 10533 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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