81 FR 49873 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 146 (July 29, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 146 (July 29, 2016)
| Page Range | 49873-49876 | |
| FR Document | 2016-17861 |
[Federal Register Volume 81, Number 146 (Friday, July 29, 2016)] [Rules and Regulations] [Pages 49873-49876] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-17861] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-3700; Directorate Identifier 2015-NM-171-AD; Amendment 39-18595; AD 2016-15-04] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 757-200 and -200CB series airplanes. 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). This AD requires external dual frequency eddy current (DFEC) or internal high frequency eddy current (HFEC) inspections of the lap splice, inner skin [[Page 49874]] fasteners, at stringer S-14R, station (STA) 440 through STA 540, and corrective action if necessary. 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. DATES: This AD is effective September 2, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of September 2, 2016. ADDRESSES: For service information identified in this final rule, 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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800-647- 5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Eric Schrieber, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5348; fax: 562-627-5210; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all The Boeing Company Model 757-200 and -200CB series airplanes. The NPRM published in the Federal Register on March 1, 2016 (81 FR 10533) (``the NPRM''). The NPRM was prompted by an evaluation by the DAH indicating that the lap splices at stringer S-14R, lower fastener row, are subject to WFD. The NPRM proposed to require repetitive external DFEC or internal HFEC inspections of the lap splice, inner skin fasteners, at stringer S-14R, STA 440 through STA 540, and corrective action if necessary. 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. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Boeing indicated its support for the NPRM. Request for Updated Service Information United Airlines generally concurred with the NPRM, but requested that repairs be incorporated into a subsequent revision of Boeing Alert Service Bulletin 757-53A0102, dated October 8, 2015. According to United Airlines, the lack of certain approved repairs adds a significant level of burden on the operators. We acknowledge United Airlines' comment and concerns. We have been advised that Boeing is working on revising the referenced service information to include repair information, but Boeing cannot provide a fixed date when the next revision will be published. To delay this AD until this service information is available is inappropriate since we have determined that an unsafe condition exists and that inspections must be conducted to ensure continued safety. If the updated service information is approved and published, any operator may request approval of an alternative method of compliance (AMOC) as specified in paragraph (j) of this AD. We may also consider further rulemaking after reviewing any updated service information. We have not changed this AD regarding this issue. Request To Add Exclusion to the Service Information United Airlines requested that the note under step 3.B.1. of the Accomplishment Instructions of Boeing Alert Service Bulletin 757- 53A0102, dated October 8, 2015, be changed so that any FAA-approved repair that meets the minimum 3 rows on either side of the lap splice would qualify as exempt from the initial and repeat inspections. United Airlines stated that this change would remove the need to request approval of an AMOC. The FAA does not make changes to service bulletins. The commenter's request could be incorporated into the AD, but we do not agree with the requested change because each existing repair affected by this AD needs to be evaluated in accordance with paragraph (g) of this AD. For any repair in the affected area, operators may request approval of an AMOC as specified in paragraph (j) of this AD. We have not changed this AD regarding this issue. Effect of Winglets on Accomplishment of the Proposed Actions Aviation Partners Boeing stated that accomplishing the supplemental type certificate (STC) ST01518SE does not affect the actions specified in the NPRM. We agree with the commenter. We have redesignated paragraph (c) of the NPRM as (c)(1) and added new paragraph (c)(2) to this final rule to state that installation of STC ST01518SE does not affect the ability to accomplish the actions required by this final rule. Therefore, for airplanes on which STC ST01518SE is installed, a ``change in product'' AMOC approval request is not necessary to comply with the requirements of 14 CFR 39.17. Clarification of Service Information Exception Paragraph (h)(2) of the NPRM describes a standard service information exception; however that exception does not apply to Boeing Alert Service Bulletin 757-53A0102, dated October 8, 2015. Therefore, we have removed paragraph (h)(2) of the NPRM from this AD. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. [[Page 49875]] Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 757-53A0102, dated October 8, 2015. The service information describes procedures for performing repetitive external DFEC or internal HFEC inspections of the lap splice, inner skin fasteners, at stringer 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. Costs of Compliance We estimate that this AD affects 572 airplanes of U.S. registry. We estimate the following costs to comply with this 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 $0................ $340 per $194,480 per inspection. per hour = $340 inspection cycle. inspection cycle. per inspection cycle. Option 2: Internal HFEC 10 work-hours x $0................ $850 per $486,200 per inspection. $85 per hour = inspection cycle. inspection cycle. $850 per inspection cycle. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that will enable us to provide cost estimates for the on-condition actions specified in this 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 This AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under 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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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): 2016-15-04 The Boeing Company: Amendment 39-18595; Docket No. FAA- 2016-3700; Directorate Identifier 2015-NM-171-AD. (a) Effective Date This AD is effective September 2, 2016. (b) Affected ADs None. (c) Applicability (1) This AD applies to all The Boeing Company Model 757-200 and -200CB series airplanes, certificated in any category. (2) Installation of Supplemental Type Certificate (STC) ST01518SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgSTC.nsf/0/38B606833BBD98B386257FAA00602538?OpenDocument&Highlight=st01518se) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01518SE is installed, a ``change in product'' alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. (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 indicating that the lap splices at stringer S-14R, lower fastener row, are subject to widespread fatigue damage. 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) Inspections 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 stringer 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 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. (i) Repair If any crack is found during any inspection required by this AD, before further flight, repair using a method approved in [[Page 49876]] 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 For more information about this AD, contact Eric Schrieber, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627- 5348; fax: 562-627-5210; email: [email protected]. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Boeing Alert Service Bulletin 757-53A0102, dated October 8, 2015. (ii) Reserved. (3) 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. (4) 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on July 21, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-17861 Filed 7-28-16; 8:45 am] BILLING CODE 4910-13-P
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21, 1986), specifically note that seats that established by the existing that may be either a single component
were excluded ‘‘because the recently airworthiness standards. or multiple components in a
adopted standards for flammability of concentrated area in their design.
Applicability
seat cushions will greatly inhibit 2. The applicant may designate up to
involvement of the seats.’’ As discussed above, these special and including 1.5 square feet of non-
Subsequently, the Final Rule at conditions are applicable to the Model traditional, non-metallic panel material
Amendment 25–83 (60 FR 6615, March ATR–42–200/–300/–320/–500 and per seat place that does not have to
6, 1995) clarified the definition of ATR–72–102/–202/–212/–212A comply with special condition 1, above.
minimum panel size: ‘‘It is not possible airplanes. Should ATR apply at a later A triple seat assembly may have a total
to cite a specific size that will apply in date for a change to the type certificate of 4.5 square feet excluded on any
all installations; however, as a general to include another model incorporating portion of the assembly (e.g., outboard
rule, components with exposed surface the same novel or unusual design seat place, 1 sq. ft.; middle, 1 sq. ft.; and
areas of one square foot or less may be feature, these special conditions would inboard, 2.5 sq. ft.)
considered small enough that they do apply to that model as well. These 3. Seats need not meet the test
not have to meet the new standards. special conditions apply to new seat- requirements of 14 CFR part 25
Components with exposed surface areas certification programs. Previously Appendix F, parts IV and V, when
greater than two square feet may be approved seats are not affected by these installed in compartments that are not
considered large enough that they do special conditions. otherwise required to meet these
have to meet the new standards. Those Conclusion requirements. Examples include
with exposed surface areas greater than airplanes:
one square foot, but less than two square This action affects only certain novel
a. With passenger capacities of 19 or
feet, must be considered in conjunction or unusual design features on two
fewer;
with the areas of the cabin in which model series of airplanes. It is not a rule
b. that do not have smoke-emission
they are installed before a determination of general applicability.
The substance of these special and heat-release test requirements in
could be made.’’ their certification basis, and that are not
In the late 1990s, the FAA issued conditions has been subjected to the
notice and comment period in several required by 14 CFR 121.312 to conduct
Policy Memorandum 97–112–39, such tests; or
‘‘Guidance for Flammability Testing of prior instances and has been derived
without substantive change from those c. that are exempted from smoke-
Seat/Console Installations,’’ October 17, emission and heat-release testing.
1997 (http://rgl.faa.gov). That memo previously issued. It is unlikely that
was issued when it became clear that prior public comment would result in a Issued in Renton, Washington, on July 21,
seat designs were evolving to include significant change from the substance 2016.
large, non-metallic panels with surface contained herein. Therefore, because a Michael Kaszycki,
areas that would impact survivability delay would significantly affect the Assistant Manager, Transport Airplane
during a cabin-fire event, comparable to certification of the airplane, which is Directorate, Aircraft Certification Service.
partitions or galleys. The memo noted imminent, the FAA has determined that [FR Doc. 2016–17846 Filed 7–28–16; 8:45 am]
that large-surface-area panels must prior public notice and comment are BILLING CODE 4910–13–P
comply with heat-release and smoke- unnecessary and impracticable, and
emission requirements, even if they good cause exists for adopting these
were attached to a seat. If the FAA had special conditions upon publication in DEPARTMENT OF TRANSPORTATION
not issued such policy, seat designs the Federal Register. The FAA is
could have been viewed as a loophole requesting comments to allow interested Federal Aviation Administration
to the airworthiness standards that persons to submit views that may not
would result in an unacceptable have been submitted in response to the 14 CFR Part 39
decrease in survivability during a cabin- prior opportunities for comment [Docket No. FAA–2016–3700; Directorate
fire event. described above. Identifier 2015–NM–171–AD; Amendment
In October of 2004, an issue was 39–18595; AD 2016–15–04]
raised regarding the appropriate List of Subjects in 14 CFR Part 25
Aircraft, Aviation safety, Reporting RIN 2120–AA64
flammability standards for passenger
seats that incorporated non-traditional, and recordkeeping requirements.
Airworthiness Directives; The Boeing
large, non-metallic panels in lieu of the The authority citation for these Company Airplanes
traditional metal covered by fabric. The special conditions is as follows:
FAA Seattle Aircraft Certification Office Authority: 49 U.S.C. 106(g), 40113, 44701, AGENCY: Federal Aviation
and Transport Standards Staff reviewed 44702, 44704. Administration (FAA), DOT.
this design, and determined that it ACTION: Final rule.
represented the kind and quantity of The Special Conditions
material that should be required to pass Accordingly, pursuant to the SUMMARY: We are adopting a new
the heat-release and smoke-emissions authority delegated to me by the airworthiness directive (AD) for all The
requirements. The FAA has determined Administrator, the following special Boeing Company Model 757–200 and
that special conditions would be issued conditions are issued as part of the type –200CB series airplanes. This AD was
to apply the standards defined in 14 certification basis for ATR Model ATR– prompted by an evaluation by the
asabaliauskas on DSK3SPTVN1PROD with RULES
CFR 25.853(d) to seats with large, non- 42–200/–300/–320/–500 and ATR–72– design approval holder (DAH)
metallic panels in their design. 102/–202/–212/–212A airplanes for new indicating that the lap splices at stringer
Traditional seat panels would not be seat-certification programs. S–14R, lower fastener row, are subject to
covered by the special conditions. 1. Compliance with 14 CFR part 25 widespread fatigue damage (WFD). This
These special conditions contain the Appendix F, parts IV and V, ‘‘Heat AD requires external dual frequency
additional safety standards that the release and smoke emission,’’ is eddy current (DFEC) or internal high
Administrator considers necessary to required for seats that incorporate non- frequency eddy current (HFEC)
establish a level of safety equivalent to traditional, large, non-metallic panels inspections of the lap splice, inner skin
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Related Service Information Under 1 inspections of the lap splice, inner skin or by the means identified in the
CFR Part 51 fasteners, at stringer S–14R, STA 440— ADDRESSES section.
STA 540, and corrective action if Costs of Compliance
We reviewed Boeing Alert Service necessary. This service information is
Bulletin 757–53A0102, dated October 8, reasonably available because the We estimate that this AD affects 572
2015. The service information describes interested parties have access to it airplanes of U.S. registry.
procedures for performing repetitive through their normal course of business We estimate the following costs to
external DFEC or internal HFEC comply with this AD:
ESTIMATED COSTS
Parts
Action Labor cost Cost per product Cost on U.S. operators
cost
Option 1: External DFEC in- 4 work-hours × $85 per hour = $0 ......... $340 per inspection cycle ........ $194,480 per inspection cycle.
spection. $340 per inspection cycle.
Option 2: Internal HFEC inspec- 10 work-hours × $85 per hour $0 ......... $850 per inspection cycle ........ $486,200 per inspection cycle.
tion. = $850 per inspection cycle.
We have received no definitive data (4) Will not have a significant ‘‘change in product’’ alternative method of
that will enable us to provide cost economic impact, positive or negative, compliance (AMOC) approval request is not
estimates for the on-condition actions on a substantial number of small entities necessary to comply with the requirements of
specified in this AD. under the criteria of the Regulatory 14 CFR 39.17.
Flexibility Act. (d) Subject
Authority for This Rulemaking
List of Subjects in 14 CFR Part 39 Air Transport Association (ATA) of
Title 49 of the United States Code America Code 53, Fuselage.
specifies the FAA’s authority to issue Air transportation, Aircraft, Aviation
rules on aviation safety. Subtitle I, safety, Incorporation by reference, (e) Unsafe Condition
section 106, describes the authority of Safety. This AD was prompted by an evaluation by
the FAA Administrator. Subtitle VII: the design approval holder indicating that
Adoption of the Amendment the lap splices at stringer S–14R, lower
Aviation Programs, describes in more
Accordingly, under the authority fastener row, are subject to widespread
detail the scope of the Agency’s
delegated to me by the Administrator, fatigue damage. We are issuing this AD to
authority. detect and correct cracking of the fuselage
We are issuing this rulemaking under the FAA amends 14 CFR part 39 as
skin lap splice. Such cracking could result in
the authority described in Subtitle VII, follows:
reduced structural integrity of the airplane.
Part A, Subpart III, Section 44701:
PART 39—AIRWORTHINESS (f) Compliance
‘‘General requirements.’’ Under that
DIRECTIVES Comply with this AD within the
section, Congress charges the FAA with
promoting safe flight of civil aircraft in compliance times specified, unless already
■ 1. The authority citation for part 39 done.
air commerce by prescribing regulations continues to read as follows:
for practices, methods, and procedures (g) Inspections
Authority: 49 U.S.C. 106(g), 40113, 44701.
the Administrator finds necessary for At the applicable time specified in
safety in air commerce. This regulation § 39.13 [Amended] paragraph 1.E., ‘‘Compliance,’’ of Boeing
is within the scope of that authority ■ 2. The FAA amends § 39.13 by adding Alert Service Bulletin 757–53A0102, dated
because it addresses an unsafe condition October 8, 2015, except as required by
the following new airworthiness paragraph (h) of this AD: Do an external dual
that is likely to exist or develop on directive (AD):
products identified in this rulemaking frequency eddy current inspection or internal
2016–15–04 The Boeing Company: high frequency eddy current inspection for
action.
Amendment 39–18595; Docket No. cracking of the lap splice, inner skin lower
Regulatory Findings FAA–2016–3700; Directorate Identifier fastener row, at stringer S–14R, station (STA)
2015–NM–171–AD. 440 through STA 540, in accordance with the
This AD will not have federalism Accomplishment Instructions of Boeing Alert
implications under Executive Order (a) Effective Date Service Bulletin 757–53A0102, dated October
13132. This AD will not have a This AD is effective September 2, 2016. 8, 2015. Repeat either inspection thereafter at
substantial direct effect on the States, on the time specified in paragraph 1.E.,
(b) Affected ADs ‘‘Compliance,’’ of Boeing Alert Service
the relationship between the national
government and the States, or on the None. Bulletin 757–53A0102, dated October 8,
distribution of power and 2015.
(c) Applicability
responsibilities among the various (1) This AD applies to all The Boeing (h) Service Information Exceptions
levels of government. Company Model 757–200 and –200CB series Where Boeing Alert Service Bulletin 757–
For the reasons discussed above, I airplanes, certificated in any category. 53A0102, dated October 8, 2015, specifies a
asabaliauskas on DSK3SPTVN1PROD with RULES
certify that this AD: (2) Installation of Supplemental Type compliance time ‘‘after the original issue date
(1) Is not a ‘‘significant regulatory Certificate (STC) ST01518SE (http:// of this service bulletin,’’ this AD requires
action’’ under Executive Order 12866, rgl.faa.gov/Regulatory_and_Guidance compliance within the specified compliance
_Library/rgSTC.nsf/0/38B6068 time after the effective date of this AD.
(2) Is not a ‘‘significant rule’’ under 33BBD98B386257FAA00602538?Open
DOT Regulatory Policies and Procedures Document&Highlight=st01518se) does not (i) Repair
(44 FR 11034, February 26, 1979), affect the ability to accomplish the actions If any crack is found during any inspection
(3) Will not affect intrastate aviation required by this AD. Therefore, for airplanes required by this AD, before further flight,
in Alaska, and on which STC ST01518SE is installed, a repair using a method approved in
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accordance with the procedures specified in (3) For service information identified in consequent reduced controllability of
paragraph (j) of this AD. this AD, contact Boeing Commercial the airplane.
Airplanes, Attention: Data & Services
(j) Alternative Methods of Compliance DATES: This AD is effective September 2,
Management, P. O. Box 3707, MC 2H–65,
(AMOCs) Seattle, WA 98124–2207; telephone: 206– 2016.
(1) The Manager, Los Angeles Aircraft 544–5000, extension 1; fax: 206–766–5680; The Director of the Federal Register
Certification Office (ACO), FAA, has the Internet: https://www.myboeingfleet.com. approved the incorporation by reference
authority to approve AMOCs for this AD, if You may view this referenced service of a certain publication listed in this AD
requested using the procedures found in 14 information at the FAA, Transport Airplane as of September 2, 2016.
CFR 39.19. In accordance with 14 CFR 39.19, Directorate, 1601 Lind Avenue SW., Renton, ADDRESSES: For service information
send your request to your principal inspector WA. For information on the availability of identified in this final rule, contact
or local Flight Standards District Office, as this material at the FAA, call 425–227–1221.
Bombardier, Inc., 400 Côte-Vertu Road
appropriate. If sending information directly (4) You may view this referenced service
to the manager of the ACO, send it to the information at the FAA, Transport Airplane West, Dorval, Québec H4S 1Y9, Canada;
attention of the person identified in Directorate, 1601 Lind Avenue SW., Renton, Widebody Customer Response Center
paragraph (k) of this AD. Information may be WA. For information on the availability of North America toll-free telephone: 1–
emailed to: 9-ANM-LAACO-AMOC- this material at the FAA, call 425–227–1221. 866–538–1247 or direct-dial telephone:
Requests@faa.gov. (5) You may view this service information 1–514–855–2999; fax: 514–855–7401;
(2) Before using any approved AMOC, that is incorporated by reference at the email: ac.yul@aero.bombardier.com;
notify your appropriate principal inspector, National Archives and Records Internet http://www.bombardier.com.
or lacking a principal inspector, the manager Administration (NARA). For information on You may view this referenced service
of the local flight standards district office/ the availability of this material at NARA, call
information at the FAA, Transport
certificate holding district office. 202–741–6030, or go to: http://
(3) An AMOC that provides an acceptable www.archives.gov/federal-register/cfr/ibr- Airplane Directorate, 1601 Lind Avenue
level of safety may be used for any repair, locations.html. SW., Renton, WA. For information on
modification, or alteration required by this the availability of this material at the
Issued in Renton, Washington, on July 21,
AD if it is approved by the Boeing FAA, call 425–227–1221. It is also
2016.
Commercial Airplanes ODA that has been available on the Internet at http://
authorized by the Manager, Los Angeles Michael Kaszycki,
www.regulations.gov by searching for
ACO, to make those findings. To be Acting Manager, Transport Airplane and locating Docket No. FAA–2016–
approved, the repair method, modification Directorate, Aircraft Certification Service.
5463.
deviation, or alteration deviation must meet [FR Doc. 2016–17861 Filed 7–28–16; 8:45 am]
the certification basis of the airplane, and the BILLING CODE 4910–13–P Examining the AD Docket
approval must specifically refer to this AD.
(4) Except as required by paragraph (h) of
You may examine the AD docket on
this AD: For service information that the Internet at http://
DEPARTMENT OF TRANSPORTATION www.regulations.gov by searching for
contains steps that are labeled as Required
for Compliance (RC), the provisions of and locating Docket No. FAA–2016–
Federal Aviation Administration 5463; or in person at the Docket
paragraphs (j)(4)(i) and (j)(4)(ii) of this AD
apply. Management Facility between 9 a.m.
(i) The steps labeled as RC, including 14 CFR Part 39 and 5 p.m., Monday through Friday,
substeps under an RC step and any figures except Federal holidays. The AD docket
identified in an RC step, must be done to [Docket No. FAA–2016–5463; Directorate
Identifier 2016–NM–013–AD; Amendment contains this AD, the regulatory
comply with the AD. An AMOC is required
for any deviations to RC steps, including 39–18598; AD 2016–15–07] evaluation, any comments received, and
substeps and identified figures. other information. The street address for
RIN 2120–AA64 the Docket Office (telephone: 800–647–
(ii) Steps not labeled as RC may be
deviated from using accepted methods in 5527) is Docket Management Facility,
accordance with the operator’s maintenance
Airworthiness Directives; Bombardier, U.S. Department of Transportation,
or inspection program without obtaining Inc. Airplanes Docket Operations, M–30, West
approval of an AMOC, provided the RC steps, AGENCY: Federal Aviation Building Ground Floor, Room W12–140,
including substeps and identified figures, can 1200 New Jersey Avenue SE.,
still be done as specified, and the airplane
Administration (FAA), Department of
Transportation (DOT). Washington, DC 20590.
can be put back in an airworthy condition.
ACTION: Final rule. FOR FURTHER INFORMATION CONTACT:
(k) Related Information Cesar Gomez, Aerospace Engineer,
For more information about this AD, SUMMARY: We are adopting a new Airframe and Mechanical Systems
contact Eric Schrieber, Aerospace Engineer, airworthiness directive (AD) for certain Branch, ANE–171, FAA, New York
Airframe Branch, ANM–120L, FAA, Los Bombardier, Inc. Model CL–600–2C10 Aircraft Certification Office (ACO), 1600
Angeles ACO, 3960 Paramount Boulevard, (Regional Jet Series 700, 701, & 702), Stewart Avenue, Suite 410, Westbury,
Lakewood, CA 90712–4137; phone: 562–627–
Model CL–600–2D15 (Regional Jet NY 11590; telephone: 516–228–7318;
5348; fax: 562–627–5210; email:
eric.schrieber@faa.gov. Series 705), Model CL–600–2D24 fax: 516–794–5531.
(Regional Jet Series 900), and Model SUPPLEMENTARY INFORMATION:
(l) Material Incorporated by Reference CL–600–2E25 (Regional Jet Series 1000)
(1) The Director of the Federal Register airplanes. This AD was prompted by Discussion
approved the incorporation by reference reports of corrosion found on the slat We issued a notice of proposed
asabaliauskas on DSK3SPTVN1PROD with RULES
(IBR) of the service information listed in this and flap torque tubes in the slat and flap rulemaking (NPRM) to amend 14 CFR
paragraph under 5 U.S.C. 552(a) and 1 CFR control system. This AD requires part 39 by adding an AD that would
part 51.
replacement of the slat and flap torque apply to certain Bombardier, Inc. Model
(2) You must use this service information
as applicable to do the actions required by tubes in the slat and flap control system. CL–600–2C10 (Regional Jet Series 700,
this AD, unless the AD specifies otherwise. We are issuing this AD to prevent 701, & 702), Model CL–600–2D15
(i) Boeing Alert Service Bulletin 757– rupture of a corroded slat or flap torque (Regional Jet Series 705), Model CL–
53A0102, dated October 8, 2015. tube. This condition could result in an 600–2D24 (Regional Jet Series 900), and
(ii) Reserved. inoperative slat or flap system and Model CL–600–2E25 (Regional Jet Series
VerDate Sep<11>2014 17:04 Jul 28, 2016 Jkt 238001 PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 E:\FR\FM\29JYR1.SGM 29JYR1](https://thefederalregister.org/doc/81_FR_50019/page/4.svg)
Document Created: 2018-02-08 07:51:26
Document Modified: 2018-02-08 07:51:26
| 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 | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective September 2, 2016. | |
| Contact | Eric Schrieber, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5348; fax: 562-627-5210; email: [email protected] | |
| FR Citation | 81 FR 49873 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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