81 FR 85113 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 227 (November 25, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 227 (November 25, 2016)
| Page Range | 85113-85116 | |
| FR Document | 2016-27640 |
[Federal Register Volume 81, Number 227 (Friday, November 25, 2016)] [Rules and Regulations] [Pages 85113-85116] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-27640] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-5597; Directorate Identifier 2016-NM-009-AD; Amendment 39-18715; AD 2016-23-08] 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 737-400 series airplanes. This AD was prompted by reports of cracks in the upper chord of the overwing stub beams at body station (STA) 578 emanating from the rivet location common to the crease beam inner chord and the overwing stub beam upper chord. This AD requires repetitive inspections for cracking, and related investigative and corrective actions if necessary. We are issuing this AD to prevent the unsafe condition on these products. DATES: This AD is effective December 30, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 30, 2016. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600; telephone 562-797-1717; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 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- 5597. 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- 5597; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, [[Page 85114]] 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: Galib Abumeri, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5324; 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 737-400 series airplanes. The NPRM published in the Federal Register on April 28, 2016 (81 FR 25360) (``the NPRM''). The NPRM was prompted by reports of cracks in the upper chord of the overwing stub beams at STA 578 emanating from the rivet location common to the crease beam inner chord and the overwing stub beam upper chord. The NPRM proposed to require repetitive inspections for cracking, and related investigative and corrective actions if necessary. Replacement of the overwing stub beam terminates the repetitive inspections for cracking at the replacement location only, and post-replacement inspections are required if the replacement is done. We are issuing this AD to detect and correct cracking in the upper chord of the overwing stub beam caused by high flight-cycle fatigue stresses from both pressurization and maneuver loads. Cracking of the overwing stub beam could adversely affect the fuselage structural integrity and result in possible decompression 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. Request To Clarify Unsafe Condition Statement in the ``Discussion'' Section Boeing requested that, in the ``Discussion'' section of the NPRM, that we clarify the cause of cracking in the overwing stub beams is from high flight-cycle fatigue stresses. Boeing submitted suggested wording. We agree to clarify the unsafe condition. The unsafe condition statement in the SUMMARY section of the NPRM and paragraph (e) of the proposed AD already specified that the cracking in the upper chord of the overwing stub beam is caused by high flight-cycle fatigue stresses from both pressurization and maneuver loads. However, the ``Discussion'' section of the NPRM is not restated in this final rule. Therefore, we have not revised this final rule in this regard. Request To Revise Paragraph (i) of the NPRM Boeing requested that we revise paragraph (i) of the proposed AD to specify that the actions in that paragraph are required on airplanes that have had an overwing stub beam replaced at STA 578 as specified in Part 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1347, Original Issue, dated December 9, 2015 (``ASB 737-53A1347 Original Issue''), and not replaced with any other method. Boeing stated that the post-replacement inspection requirements specified in table 2 of paragraph 1.E., ``Compliance,'' of ASB 737- 53A1347 Original Issue are applicable only to a STA 578 stub beam replacement accomplished as specified in Part 4 of the Accomplishment Instructions of ASB 737-53A1347 Original Issue. We agree with Boeing's request. We have revised paragraph (i) of this AD accordingly. 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 or 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. Related Service Information Under 1 CFR Part 51 We reviewed ASB 737-53A1347 Original Issue. The service information describes procedures for doing a surface high frequency eddy current inspection for cracking in the overwing stub beam upper chord at STA 559, STA 578, and STA 601, and repairs and replacement. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 93 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs -------------------------------------------------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product Cost on U.S. operators -------------------------------------------------------------------------------------------------------------------------------------------------------- Inspection......................... 24 work-hours x $85 per $0 $2,040 per inspection $189,720 per inspection cycle. hour = $2,040 per cycle. inspection cycle. -------------------------------------------------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary inspections/ replacements that would be required based on the results of the inspection. We have no way of determining the number of aircraft that might need these inspections/replacements: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Related investigative 9 work-hours x $85 $0........................... $765 per side. inspection. per hour = $765 per side. [[Page 85115]] STA 578 Replacement............ 41 work-hours x $41,500 per side............. $44,985 per side. $85 per hour = $3,485 per side. STA 578 Post[dash]replacement 1 work-hour x $85 $0........................... $85 per side. inspection. per hour = $85 per side. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for the remaining 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): 2016-23-08 The Boeing Company: Amendment 39-18715; Docket No. FAA- 2016-5597; Directorate Identifier 2016-NM-009-AD. (a) Effective Date This AD is effective December 30, 2016. (b) Affected ADs None. (c) Applicability This AD applies to all the Boeing Company Model 737-400 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 reports of cracks in the upper chord of the overwing stub beams at body station (STA) 578 emanating from the rivet location common to the crease beam inner chord and the overwing stub beam upper chord. We are issuing this AD to detect and correct cracking in the upper chord of the overwing stub beam caused by high flight-cycle fatigue stresses from both pressurization and maneuver loads. Cracking of the overwing stub beam could adversely affect the fuselage structural integrity and result in possible decompression of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections, Related Investigative Actions, and Corrective Actions At the applicable time specified in table 1 in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1347, Original Issue, dated December 9, 2015 (``ASB 737-53A1347 Original Issue''), except as required by paragraphs (j)(1) and (j)(2) of this AD: Do a surface high frequency eddy current (HFEC) inspection for any cracking in the overwing stub beam upper chord at STA 559, STA 578, and STA 601; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of ASB 737-53A1347 Original Issue, except as specified in paragraph (j)(3) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the HFEC inspection thereafter at the applicable intervals specified in ASB 737-53A1347 Original Issue. Note 1 to paragraph (g) of this AD: Deviation from the actions specified in ASB 737-53A1347 Original Issue may affect compliance with the fuel tank ignition prevention requirements specified in Critical Design Configuration Control Limitation 28-AWL-11 of Document D6-38278-CMR. (h) Terminating Action Replacement of the overwing stub beam, in accordance with Part 4 of the Accomplishment Instructions of ASB 737-53A1347 Original Issue, terminates the repetitive inspections required by paragraph (g) of this AD at the STA 578 replacement location only. The post- replacement inspections required by paragraph (i) of this AD are still required at the STA 578 replacement location. (i) Post-Replacement Inspections and Corrective Action For airplanes on which an overwing stub beam has been replaced at STA 578, in accordance with Part 4 of the Accomplishment Instructions of ASB 737-53A1347 Original Issue: At the applicable time specified in table 2 in paragraph 1.E., ``Compliance,'' of ASB 737-53A1347 Original Issue, do a surface HFEC inspection for any cracking in the overwing stub beam upper chord at STA 578, in accordance with the Accomplishment Instructions of ASB 737-53A1347 Original Issue. Repeat the HFEC inspection thereafter at the applicable intervals specified in ASB 737-53A1347 Original Issue. If any cracking is found during any inspection required by this paragraph, before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (j)(3) of this AD. (j) Exceptions to Service Information (1) Where ASB 737-53A1347 Original Issue, 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 ASB 737-53A1347 [[Page 85116]] Original Issue, refers to airplanes with specified total flight- cycles ``at the original issue date of this service bulletin.'' This AD, however, applies to the airplanes with the specified total flight-cycles as of the effective date of this AD. (3) If any cracking is found during any inspection required by this AD, and ASB 737-53A1347 Original Issue specifies to contact Boeing for appropriate action: Before further flight, repair the cracking or replace the stub beam, using a method approved in accordance with the procedures specified in paragraph (l) of this AD. (k) No Economic Inspection Required This AD does not require the ``Recommended Economic Inspection'' specified in paragraph 3.B.3. of the Accomplishment Instructions of ASB 737-53A1347 Original Issue. (l) 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 (m) of this AD. Information may be emailed to: [email protected]. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, 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 (j)(3) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (l)(4)(i) and (l)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or substep is labeled ``RC Exempt,'' then the RC requirement is removed from that step or substep. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (m) Related Information For more information about this AD, contact Galib Abumeri, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5324; fax: 562-627-5210; email: [email protected]. (n) 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 737-53A1347, Original Issue, dated December 9, 2015. (ii) Reserved. (3) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-5600; telephone 562-797-1717; Internet https://www.myboeingfleet.com. (4) You may view this 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 November 8, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-27640 Filed 11-23-16; 8:45 am] BILLING CODE 4910-13-P
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concurrence before applying for a loan. Participating Credit Union’s members DEPARTMENT OF TRANSPORTATION
NCUA will obtain the concurrence once a year, either at the annual meeting
directly from the state supervisory or in a written report sent to all Federal Aviation Administration
authority rather than through the members. The Participating Credit
qualifying state-chartered credit union. Union must also submit to NCUA the 14 CFR Part 39
Additionally, before NCUA will provide written report or a summary of the [Docket No. FAA–2016–5597; Directorate
a loan to a qualifying state-charted report provided to members. Identifier 2016–NM–009–AD; Amendment
credit union the credit union must make (ii) Technical Assistance Grants. A 39–18715; AD 2016–23–08]
copies of its state examination reports Participating Credit Union that receives RIN 2120–AA64
available to NCUA and agree to a technical assistance grant under this
examination by NCUA. part should report on the progress of Airworthiness Directives; The Boeing
* * * * * providing needed community services Company Airplanes
(f) Notice of Award. NCUA will to the Participating Credit Union’s
determine whether an application meets AGENCY: Federal Aviation
members once a year, either at the
NCUA’s standards established by this Administration (FAA), DOT.
annual meeting or in a written report
part and the related Notice of Funding sent to all members. ACTION: Final rule.
Opportunity. NCUA will provide
* * * * * SUMMARY: We are adopting a new
written notice to a Qualifying Credit
Union as to whether or not it has ■ 10. Revise § 705.10 to read as follows: airworthiness directive (AD) for all The
qualified for a loan or technical Boeing Company Model 737–400 series
assistance grant under this part. A § 705.10 Appeals. airplanes. This AD was prompted by
Qualifying Credit Union whose reports of cracks in the upper chord of
(a) Appeals of non-qualification. A the overwing stub beams at body station
application has been denied for failure Qualifying Credit Union whose
of a qualification may appeal that (STA) 578 emanating from the rivet
application for a loan or technical location common to the crease beam
decision in accordance with § 705.10 of assistance grant has been denied, under
this part. inner chord and the overwing stub beam
§ 705.7(f), for failure of a qualification upper chord. This AD requires
(g) Disbursement—(1) Loans. Before may appeal that decision to the NCUA
NCUA will disburse a loan, the repetitive inspections for cracking, and
Board in accordance with the following: related investigative and corrective
Participating Credit Union must sign the
loan agreement, promissory note, and (1) Within thirty days of its receipt of actions if necessary. We are issuing this
any other loan related documents. a notice of non-qualification, a credit AD to prevent the unsafe condition on
NCUA may, in its discretion, choose not union may appeal the decision to the these products.
to disburse the entire amount of the loan NCUA Board. The scope of the NCUA DATES: This AD is effective December
at once. Board’s review is limited to the 30, 2016.
(2) Technical Assistance Grants. threshold question of qualification and The Director of the Federal Register
NCUA will disburse technical assistance not the issue of whether, among approved the incorporation by reference
grants in such amounts, and in qualified applicants, a particular loan or of a certain publication listed in this AD
accordance with such terms and technical assistance grant is funded. as of December 30, 2016.
conditions, as NCUA may establish. In (2) The foregoing procedure shall ADDRESSES: For service information
general, technical assistance grants are apply only with respect to Applications identified in this final rule, contact
provided on a reimbursement basis, to received by NCUA during an open Boeing Commercial Airplanes,
cover expenditures approved in advance period in which funds are available and Attention: Contractual & Data Services
by NCUA and supported by receipts NCUA has called for Applications. Any (C&DS), 2600 Westminster Blvd., MC
evidencing payment by the Participating Application submitted by an applicant 110–SK57, Seal Beach, CA 90740–5600;
Credit Union. during a period in which NCUA has not telephone 562–797–1717; Internet
■ 9. Revise § 705.9(b) to read as follows: called for Applications will be rejected, https://www.myboeingfleet.com. You
except for those Applications submitted may view this referenced service
§ 705.9 Reporting and monitoring. under § 705.8. Any such rejection shall information at the FAA, Transport
* * * * * not be subject to appeal or review by the Airplane Directorate, 1601 Lind Avenue
(b) Reporting—(1) Reporting to NCUA. NCUA Board. SW., Renton, WA. You may view this
A Participating Credit Union must referenced service information at the
(b) Appeals of technical assistance
complete and submit to NCUA all FAA, Transport Airplane Directorate,
grant reimbursement denials. Pursuant
required reports, at such times and in 1601 Lind Avenue SW., Renton, WA.
to NCUA Interpretative Ruling and
such formats as NCUA will direct. Such For information on the availability of
Policy Statement 11–1, any Participating
reports must describe how the this material at the FAA, call 425–227–
Credit Union may appeal a denial of a
Participating Credit Union has used the 1221. It is also available on the Internet
technical assistance grant
loan or technical assistance grant at http://www.regulations.gov by
reimbursement to NCUA’s Supervisory
proceeds and the results it has obtained, searching for and locating Docket No.
Review Committee. All appeals of
in relation to the programs, policies, or FAA–2016–5597.
initiatives identified by the Participating technical assistance grant
Credit Union in its application. NCUA reimbursements must be submitted to Examining the AD Docket
may request additional information as it the Supervisory Review Committee You may examine the AD docket on
ehiers on DSK5VPTVN1PROD with RULES
determines appropriate. within 30 days from the date of the the Internet at http://
(2) Reporting to Members—(i) Loans. denial. The decisions of the Supervisory www.regulations.gov by searching for
A Participating Credit Union that Review Committee are final and may and locating Docket No. FAA–2016–
receives a loan under this part must not be appealed to the NCUA Board. 5597; or in person at the Docket
report on the progress of providing [FR Doc. 2016–28229 Filed 11–23–16; 8:45 am] Management Facility between 9 a.m.
needed community services to the BILLING CODE 7535–01–P and 5 p.m., Monday through Friday,
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ON-CONDITION COSTS—Continued
Action Labor cost Parts cost Cost per product
STA 578 Replacement ..................................... 41 work-hours × $85 per hour = $3,485 per $41,500 per side ....... $44,985 per side.
side.
STA 578 Post-replacement inspection ............. 1 work-hour × $85 per hour = $85 per side ..... $0 .............................. $85 per side.
We have received no definitive data Adoption of the Amendment by paragraphs (j)(1) and (j)(2) of this AD: Do
that would enable us to provide cost a surface high frequency eddy current (HFEC)
Accordingly, under the authority inspection for any cracking in the overwing
estimates for the remaining on- delegated to me by the Administrator, stub beam upper chord at STA 559, STA 578,
condition actions specified in this AD. the FAA amends 14 CFR part 39 as and STA 601; and do all applicable related
Authority for This Rulemaking follows: investigative and corrective actions; in
accordance with the Accomplishment
Title 49 of the United States Code PART 39—AIRWORTHINESS Instructions of ASB 737–53A1347 Original
specifies the FAA’s authority to issue DIRECTIVES Issue, except as specified in paragraph (j)(3)
rules on aviation safety. Subtitle I, of this AD. Do all applicable related
section 106, describes the authority of ■ 1. The authority citation for part 39 investigative and corrective actions before
the FAA Administrator. Subtitle VII: continues to read as follows: further flight. Repeat the HFEC inspection
thereafter at the applicable intervals specified
Aviation Programs, describes in more Authority: 49 U.S.C. 106(g), 40113, 44701. in ASB 737–53A1347 Original Issue.
detail the scope of the Agency’s
§ 39.13 [Amended] Note 1 to paragraph (g) of this AD:
authority.
Deviation from the actions specified in ASB
We are issuing this rulemaking under ■ 2. The FAA amends § 39.13 by adding 737–53A1347 Original Issue may affect
the authority described in Subtitle VII, the following new airworthiness compliance with the fuel tank ignition
Part A, Subpart III, Section 44701: directive (AD): prevention requirements specified in Critical
‘‘General requirements.’’ Under that 2016–23–08 The Boeing Company: Design Configuration Control Limitation 28–
section, Congress charges the FAA with Amendment 39–18715; Docket No. AWL–11 of Document D6–38278–CMR.
promoting safe flight of civil aircraft in FAA–2016–5597; Directorate Identifier
2016–NM–009–AD. (h) Terminating Action
air commerce by prescribing regulations
for practices, methods, and procedures Replacement of the overwing stub beam, in
(a) Effective Date accordance with Part 4 of the
the Administrator finds necessary for This AD is effective December 30, 2016. Accomplishment Instructions of ASB 737–
safety in air commerce. This regulation 53A1347 Original Issue, terminates the
is within the scope of that authority (b) Affected ADs
repetitive inspections required by paragraph
because it addresses an unsafe condition None. (g) of this AD at the STA 578 replacement
that is likely to exist or develop on (c) Applicability location only. The post-replacement
products identified in this rulemaking inspections required by paragraph (i) of this
This AD applies to all the Boeing Company AD are still required at the STA 578
action. Model 737–400 series airplanes, certificated replacement location.
Regulatory Findings in any category.
(i) Post-Replacement Inspections and
This AD will not have federalism (d) Subject
Corrective Action
implications under Executive Order Air Transport Association (ATA) of
For airplanes on which an overwing stub
13132. This AD will not have a America Code 53, Fuselage.
beam has been replaced at STA 578, in
substantial direct effect on the States, on (e) Unsafe Condition accordance with Part 4 of the
the relationship between the national This AD was prompted by reports of cracks Accomplishment Instructions of ASB 737–
government and the States, or on the in the upper chord of the overwing stub 53A1347 Original Issue: At the applicable
distribution of power and beams at body station (STA) 578 emanating time specified in table 2 in paragraph 1.E.,
responsibilities among the various from the rivet location common to the crease ‘‘Compliance,’’ of ASB 737–53A1347
levels of government. beam inner chord and the overwing stub Original Issue, do a surface HFEC inspection
beam upper chord. We are issuing this AD to for any cracking in the overwing stub beam
For the reasons discussed above, I upper chord at STA 578, in accordance with
certify that this AD: detect and correct cracking in the upper
chord of the overwing stub beam caused by the Accomplishment Instructions of ASB
(1) Is not a ‘‘significant regulatory high flight-cycle fatigue stresses from both 737–53A1347 Original Issue. Repeat the
action’’ under Executive Order 12866, pressurization and maneuver loads. Cracking HFEC inspection thereafter at the applicable
(2) Is not a ‘‘significant rule’’ under of the overwing stub beam could adversely intervals specified in ASB 737–53A1347
DOT Regulatory Policies and Procedures affect the fuselage structural integrity and Original Issue. If any cracking is found
result in possible decompression of the during any inspection required by this
(44 FR 11034, February 26, 1979),
airplane. paragraph, before further flight, repair the
(3) Will not affect intrastate aviation cracking using a method approved in
in Alaska, and (f) Compliance accordance with the procedures specified in
(4) Will not have a significant Comply with this AD within the paragraph (j)(3) of this AD.
economic impact, positive or negative, compliance times specified, unless already
(j) Exceptions to Service Information
on a substantial number of small entities done.
under the criteria of the Regulatory (1) Where ASB 737–53A1347 Original
(g) Inspections, Related Investigative
ehiers on DSK5VPTVN1PROD with RULES
Issue, specifies a compliance time after the
Flexibility Act. Actions, and Corrective Actions ‘‘original issue date of this service bulletin,’’
List of Subjects in 14 CFR Part 39 At the applicable time specified in table 1 this AD requires compliance within the
in paragraph 1.E., ‘‘Compliance,’’ of Boeing specified compliance time after the effective
Air transportation, Aircraft, Aviation Alert Service Bulletin 737–53A1347, Original date of this AD.
safety, Incorporation by reference, Issue, dated December 9, 2015 (‘‘ASB 737– (2) The Condition column of paragraph
Safety. 53A1347 Original Issue’’), except as required 1.E., ‘‘Compliance,’’ of ASB 737–53A1347
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Original Issue, refers to airplanes with (m) Related Information Bombardier, Inc. Model DHC–8–102,
specified total flight-cycles ‘‘at the original For more information about this AD, –103, and –106 airplanes; and Model
issue date of this service bulletin.’’ This AD, contact Galib Abumeri, Aerospace Engineer, DHC–8–200 and –300 series airplanes.
however, applies to the airplanes with the Airframe Branch, ANM–120L, FAA, Los This AD was prompted by a report of
specified total flight-cycles as of the effective Angeles Aircraft Certification Office (ACO),
date of this AD. heat damage found on a nacelle firewall
3960 Paramount Boulevard, Lakewood, CA after an unsuccessful engine ground
(3) If any cracking is found during any 90712–4137; phone: 562–627–5324; fax: 562–
inspection required by this AD, and ASB start and several events of heat damage
627–5210; email: galib.abumeri@faa.gov.
737–53A1347 Original Issue specifies to found on direct current starter/generator
contact Boeing for appropriate action: Before (n) Material Incorporated by Reference terminal block assemblies. This AD
further flight, repair the cracking or replace (1) The Director of the Federal Register requires an inspection to detect damage
the stub beam, using a method approved in approved the incorporation by reference on the nacelle firewalls and the terminal
accordance with the procedures specified in
paragraph (l) of this AD.
(IBR) of the service information listed in this block assemblies and to make sure the
paragraph under 5 U.S.C. 552(a) and 1 CFR insulating sleeves are installed and have
(k) No Economic Inspection Required part 51. no damage, and corrective action if
This AD does not require the (2) You must use this service information necessary. We are issuing this AD to
‘‘Recommended Economic Inspection’’ as applicable to do the actions required by
address the unsafe condition on these
specified in paragraph 3.B.3. of the this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 737– products.
Accomplishment Instructions of ASB 737–
53A1347 Original Issue. 53A1347, Original Issue, dated December 9, DATES: This AD is effective December
2015. 30, 2016.
(l) Alternative Methods of Compliance (ii) Reserved. The Director of the Federal Register
(AMOCs) (3) For Boeing service information approved the incorporation by reference
(1) The Manager, Los Angeles Aircraft identified in this AD, contact Boeing of a certain publication listed in this AD
Certification Office (ACO), FAA, has the Commercial Airplanes, Attention:
Contractual & Data Services (C&DS), 2600
as of December 30, 2016.
authority to approve AMOCs for this AD, if
requested using the procedures found in 14 Westminster Blvd., MC 110–SK57, Seal ADDRESSES: For service information
CFR 39.19. In accordance with 14 CFR 39.19, Beach, CA 90740–5600; telephone 562–797– identified in this final rule, contact
send your request to your principal inspector 1717; Internet https:// Bombardier, Inc., Q-Series Technical
or local Flight Standards District Office, as www.myboeingfleet.com. Help Desk, 123 Garratt Boulevard,
appropriate. If sending information directly (4) You may view this service information Toronto, Ontario M3K 1Y5, Canada;
to the manager of the ACO, send it to the at the FAA, Transport Airplane Directorate, telephone 416–375–4000; fax 416–375–
attention of the person identified in 1601 Lind Avenue SW., Renton, WA. For
4539; email thd.qseries@
paragraph (m) of this AD. Information may be information on the availability of this
emailed to: 9-ANM-LAACO-ACO-AMOC- material at the FAA, call 425–227–1221. aero.bombardier.com; Internet http://
Requests@faa.gov. (5) You may view this service information www.bombardier.com. You may view
(2) Before using any approved AMOC, that is incorporated by reference at the this referenced service information at
notify your appropriate principal inspector, National Archives and Records the FAA, Transport Airplane
or lacking a principal inspector, the manager Administration (NARA). For information on Directorate, 1601 Lind Avenue SW.,
of the local flight standards district office/ the availability of this material at NARA, call Renton, WA. For information on the
certificate holding district office. 202–741–6030, or go to: http:// availability of this material at the FAA,
(3) An AMOC that provides an acceptable www.archives.gov/federal-register/cfr/ibr- call 425–227–1221. It is also available
level of safety may be used for any repair, locations.html.
modification, or alteration required by this
on the Internet at http://
Issued in Renton, Washington, on www.regulations.gov by searching for
AD if it is approved by the Boeing
November 8, 2016. and locating Docket No. FAA–2016–
Commercial Airplanes Organization
Designation Authorization (ODA) that has Michael Kaszycki, 5044.
been authorized by the Manager, Los Angeles Acting Manager, Transport Airplane
ACO, to make those findings. To be Directorate, Aircraft Certification Service.
Examining the AD Docket
approved, the repair method, modification [FR Doc. 2016–27640 Filed 11–23–16; 8:45 am] You may examine the AD docket on
deviation, or alteration deviation must meet the Internet at http://
BILLING CODE 4910–13–P
the certification basis of the airplane, and the www.regulations.gov by searching for
approval must specifically refer to this AD. and locating Docket No. FAA–2016–
(4) Except as required by paragraph (j)(3)
of this AD: For service information that DEPARTMENT OF TRANSPORTATION 5044; or in person at the Docket
contains steps that are labeled as Required Management Facility between 9 a.m.
for Compliance (RC), the provisions of Federal Aviation Administration and 5 p.m., Monday through Friday,
paragraphs (l)(4)(i) and (l)(4)(ii) of this AD except Federal holidays. The AD docket
apply. 14 CFR Part 39 contains this AD, the regulatory
(i) The steps labeled as RC, including evaluation, any comments received, and
substeps under an RC step and any figures [Docket No. FAA–2016–5044; Directorate
Identifier 2014–NM–166–AD; Amendment other information. The street address for
identified in an RC step, must be done to the Docket Office (telephone 800–647–
comply with the AD. If a step or substep is 39–18718; AD 2016–24–01]
labeled ‘‘RC Exempt,’’ then the RC
5527) is Docket Management Facility,
RIN 2120–AA64 U.S. Department of Transportation,
requirement is removed from that step or
substep. An AMOC is required for any Docket Operations, M–30, West
Airworthiness Directives; Bombardier, Building Ground Floor, Room W12–140,
deviations to RC steps, including substeps
and identified figures. Inc. Airplanes 1200 New Jersey Avenue SE.,
(ii) Steps not labeled as RC may be AGENCY: Federal Aviation Washington, DC 20590.
ehiers on DSK5VPTVN1PROD with RULES
deviated from using accepted methods in FOR FURTHER INFORMATION CONTACT:
Administration (FAA), Department of
accordance with the operator’s maintenance
or inspection program without obtaining Transportation (DOT). Assata Dessaline, Aerospace Engineer,
approval of an AMOC, provided the RC steps, ACTION: Final rule. Avionics and Flight Test Branch, ANE–
including substeps and identified figures, can 172, FAA, New York Aircraft
still be done as specified, and the airplane SUMMARY: We are adopting a new Certification Office, 1600 Stewart
can be put back in an airworthy condition. airworthiness directive (AD) for certain Avenue, Suite 410, Westbury, NY
VerDate Sep<11>2014 14:00 Nov 23, 2016 Jkt 241001 PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 E:\FR\FM\25NOR1.SGM 25NOR1](https://thefederalregister.org/doc/81_FR_85340/page/4.svg)
Document Created: 2016-11-23 23:17:25
Document Modified: 2016-11-23 23:17:25
| 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 December 30, 2016. | |
| Contact | Galib Abumeri, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5324; fax: 562-627-5210; email: [email protected] | |
| FR Citation | 81 FR 85113 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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