82_FR_35774 82 FR 35628 - Airworthiness Directives; The Boeing Company Airplanes

82 FR 35628 - Airworthiness Directives; The Boeing Company Airplanes

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 82, Issue 146 (August 1, 2017)

Page Range35628-35630
FR Document2017-15477

We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the lower skin at the skin lap splice lower fastener row is subject to widespread fatigue damage (WFD). This AD requires repetitive inspections for cracking in the skin lap splice at the lower fastener row, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.

Federal Register, Volume 82 Issue 146 (Tuesday, August 1, 2017) 
[Federal Register Volume 82, Number 146 (Tuesday, August 1, 2017)]
[Rules and Regulations]
[Pages 35628-35630]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2017-15477]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0330; Directorate Identifier 2017-NM-016-AD; 
Amendment 39-18972; AD 2017-15-12]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
The Boeing Company Model 737-300, -400, and -500 series airplanes. This 
AD was prompted by an evaluation by the design approval holder (DAH) 
indicating that the lower skin at the skin lap splice lower fastener 
row is subject to widespread fatigue damage (WFD). This AD requires 
repetitive inspections for cracking in the skin lap splice at the lower 
fastener row, and repair if necessary. We are issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective September 5, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of September 5, 
2017.

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. For information on the availability of this material at the 
FAA, call 425-227-1221. Boeing Alert Service Bulletin 737-53A1365, 
dated January 23, 2017, is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0330.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0330; 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 final rule, 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: James Guo, Aerospace Engineer, 
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification 
Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 
562-627-5357; 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 certain The Boeing Company 
Model 737-300, -400, and -500 series airplanes. The NPRM published in 
the

[[Page 35629]]

Federal Register on May 1, 2017 (82 FR 20288). The NPRM was prompted by 
an evaluation by the DAH indicating that the lower skin at the skin lap 
splice lower fastener row is subject to WFD. The NPRM proposed to 
require repetitive inspections for cracking in the skin lap splice at 
the lower fastener row, and repair if necessary.

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.

Supportive Comment

    Boeing stated that it concurred with the NPRM.

Effect of Winglets on Accomplishment of the Proposed Actions

    Aviation Partners Boeing stated that accomplishing the supplemental 
type certificate (STC) ST01219SE does not affect the actions specified 
in the NPRM.
    We concur with the request. We have redesignated paragraph (c) of 
the proposed AD as paragraph (c)(1) of this AD and added paragraph 
(c)(2) to this AD to state that installation of STC ST01219SE does not 
affect the ability to accomplish the actions required by this AD. 
Therefore, for airplanes on which STC ST01219SE 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.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this final rule with the change 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 NPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this final 
rule.

Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 737-53A1365, dated 
January 23, 2017. The service information describes procedures for eddy 
current inspections for cracking at the skin lap splice in the lower 
fastener row, and repair 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 126 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
----------------------------------------------------------------------------------------------------------------
Inspection.................  84 work-hours x $85                $0  $7,140 per inspection  $899,640 per
                              per hour = $7,140                      cycle.                 inspection cycle.
                              per inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would 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):

2017-15-12 The Boeing Company: Amendment 39-18972; Docket No. FAA-
2017-0330; Directorate Identifier 2017-NM-016-AD.

(a) Effective Date

    This AD is effective September 5, 2017.

(b) Affected ADs

    None.

(c) Applicability

    (1) This AD applies to The Boeing Company Model 737-300, -400, 
and -500 series airplanes, certificated in any category,

[[Page 35630]]

as identified in Boeing Alert Service Bulletin 737-53A1365, dated 
January 23, 2017.
    (2) Installation of Supplemental Type Certificate (STC) 
ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/EBD1CEC7B301293E86257CB30045557A?OpenDocument&Highlight=st01219se) 
does not affect the ability to accomplish the actions required by 
this AD. Therefore, for airplanes on which STC ST01219SE 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 lower skin at the skin lap splice lower 
fastener row is subject to widespread fatigue damage. We are issuing 
this AD to detect and correct cracks in the lower skin, which, if 
not detected, could link up, resulting in reduced structural 
integrity of the airplane and consequent uncontrolled decompression 
of the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Repetitive Inspections

    Except as provided by paragraph (i) of this AD, at the 
applicable time specified in paragraph 1.E., ``Compliance,'' of 
Boeing Alert Service Bulletin 737-53A1365, dated January 23, 2017: 
Do external eddy current inspections at stringer S-14 on the left 
and right sides of the airplane (S-14L and S-14R) for any crack in 
the skin lap splice at the lower fastener row, in accordance with 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
737-53A1365, dated January 23, 2017. Repeat the inspections 
thereafter at the applicable times specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1365, dated 
January 23, 2017.

(h) Repair

    If any crack is found during any inspection required by 
paragraph (g) of this AD, repair before further flight using a 
method approved in accordance with the procedures specified in 
paragraph (j) of this AD. Although Boeing Alert Service Bulletin 
737-53A1365, dated January 23, 2017, specifies to contact Boeing for 
appropriate action and specifies that action as ``RC'' (Required for 
Compliance), this AD requires repair as specified in this paragraph.

(i) Exceptions to Service Information Specifications

    (1) Where Boeing Alert Service Bulletin 737-53A1365, dated 
January 23, 2017, 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 Table 1 and Table 2 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1365, 
dated January 23, 2017, refers to 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.

(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 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 (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. 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.

(k) Related Information

    For more information about this AD, contact James Guo, Aerospace 
Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 3960 
Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5357; 
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 737-53A1365, dated January 23, 
2017.
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Contractual & Data Services 
(C&DS), 2600 Westminster Blvd., MC 110-SK57, Seal Beach, CA 90740-
5600; telephone 562-797-1717; Internet https://www.myboeingfleet.com.
    (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 July 14, 2017.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-15477 Filed 7-31-17; 8:45 am]
 BILLING CODE 4910-13-P

35628 Federal Register / Vol. 82, No. 146 / Tuesday, August 1, 2017 / Rules and Regulations the clothing should be in contrast to the Class 600 as defined in SAE J211, This AD requires repetitive inspections color of the restraint system. The ES–2re ‘‘Instrumentation for Impact Test—Part for cracking in the skin lap splice at the jacket is sufficient for torso clothing, 1—Electronic Instrumentation.’’ lower fastener row, and repair if although a form-fitting shirt may be (1) The upper-neck tension force at necessary. We are issuing this AD to used in addition if desired. the occipital condyle (O.C.) location address the unsafe condition on these (3) ES–2re ATD lateral must be less than 405 lb (1,800 N). products. instrumentation: The rib-module linear (2) The upper-neck compression force DATES: This AD is effective September 5, slides are directional, i.e., deflection at the O.C. location must be less than 2017. occurs in either a positive or negative 405 lb (1,800 N). The Director of the Federal Register ATD y-axis direction. The modules (3) The upper-neck bending torque approved the incorporation by reference must be installed such that the moving about the ATD x-axis at the O.C. of a certain publication listed in this AD end of the rib module is toward the location must be less than 1,018 in-lb as of September 5, 2017. front of the airplane. The three (115 Nm). ADDRESSES: For service information abdominal-force sensors must be (4) The upper-neck resultant shear identified in this final rule, contact installed such that they are on the side force at the O.C. location must be less Boeing Commercial Airplanes, of the ATD toward the front of the than 186 lb (825 N). Attention: Contractual & Data Services airplane. g. Occupant (ES–2re ATD) retention: (C&DS), 2600 Westminster Blvd., MC f. The combined horizontal/vertical The pelvic restraint must remain on the 110 SK57, Seal Beach, CA 90740–5600; test, required by § 25.562(b)(1) and these ES–2re ATD’s pelvis during the impact telephone 562–797–1717; Internet special conditions, must be conducted and rebound phases of the test. The https://www.myboeingfleet.com. You with a Hybrid II ATD (49 CFR part 572, upper-torso restraint straps (if present) may view this referenced service subpart B, as specified in § 25.562), or must remain on the ATD’s shoulder information at the FAA, Transport equivalent, occupying each seat during the impact. Airplane Directorate, 1601 Lind Avenue position. h. Occupant (ES–2re ATD) support: g. Restraint systems: SW., Renton, WA. For information on (1) Pelvis excursion: The load-bearing the availability of this material at the (1) If inflatable restraint systems are portion of the bottom of the ATD pelvis used, they must be active during all FAA, call 425–227–1221. Boeing Alert must not translate beyond the edges of Service Bulletin 737–53A1365, dated dynamic tests conducted to show its seat’s bottom seat-cushion compliance with § 25.562. January 23, 2017, is also available on the supporting structure. Internet at http://www.regulations.gov (2) The design and installation of (2) Upper-torso support: The lateral seatbelt buckles must prevent by searching for and locating Docket No. flexion of the ATD torso must not FAA–2017–0330. unbuckling due to applied inertial exceed 40 degrees from the normal forces, or impact of the hands or arms upright position during the impact. Examining the AD Docket of the occupant during an emergency Issued in Renton, Washington, on July 13, You may examine the AD docket on landing. 2. Additional performance measures 2017. the Internet at http:// applicable to tests and rational analysis Dionne Palermo, www.regulations.gov by searching for conducted to show compliance with Acting Manager, Transport Airplane and locating Docket No. FAA–2017– §§ 25.562 and 25.785 for side-facing Directorate, Aircraft Certification Service. 0330; or in person at the Docket seats: [FR Doc. 2017–16099 Filed 7–31–17; 8:45 am] Management Facility between 9 a.m. a. Body-to-body contact: Contact BILLING CODE 4910–13–P and 5 p.m., Monday through Friday, between the head, pelvis, torso, or except Federal holidays. The AD docket shoulder area of one ATD with the contains this final rule, the regulatory adjacent-seated ATD’s head, pelvis, DEPARTMENT OF TRANSPORTATION evaluation, any comments received, and torso, or shoulder area is not allowed. other information. The address for the Contact during rebound is allowed. Federal Aviation Administration Docket Office (phone: 800–647–5527) is b. Thoracic: The deflection of any of Docket Management Facility, U.S. the ES–2re ATD upper, middle, and 14 CFR Part 39 Department of Transportation, Docket lower ribs must not exceed 1.73 in. (44 [Docket No. FAA–2017–0330; Directorate Operations, M–30, West Building mm). Data must be processed as defined Identifier 2017–NM–016–AD; Amendment Ground Floor, Room W12–140, 1200 in Federal Motor Vehicle Safety 39–18972; AD 2017–15–12] New Jersey Avenue SE., Washington, Standards (FMVSS) 571.214. DC 20590. RIN 2120–AA64 c. Abdominal: The sum of the FOR FURTHER INFORMATION CONTACT: measured ES–2re ATD front, middle, Airworthiness Directives; The Boeing James Guo, Aerospace Engineer, and rear abdominal forces must not Company Airplanes Airframe Branch, ANM–120L, FAA, Los exceed 562 lb (2,500 N). Data must be Angeles Aircraft Certification Office processed as defined in FMVSS AGENCY: Federal Aviation (ACO), 3960 Paramount Boulevard, 571.214. Administration (FAA), DOT. Lakewood, CA 90712–4137; phone: d. Pelvic: The pubic symphysis force ACTION: Final rule. 562–627–5357; fax: 562–627–5210; measured by the ES–2re ATD must not email: james.guo@faa.gov. exceed 1,350 lb (6,000 N). Data must be SUMMARY: We are adopting a new SUPPLEMENTARY INFORMATION: processed as defined in FMVSS airworthiness directive (AD) for certain Discussion mstockstill on DSK30JT082PROD with RULES 571.214. The Boeing Company Model 737–300, e. Leg: Axial rotation of the upper-leg –400, and –500 series airplanes. This We issued a notice of proposed (femur) must be limited to 35 degrees in AD was prompted by an evaluation by rulemaking (NPRM) to amend 14 CFR either direction from the nominal seated the design approval holder (DAH) part 39 by adding an AD that would position. indicating that the lower skin at the skin apply to certain The Boeing Company f. Neck: As measured by the ES–2re lap splice lower fastener row is subject Model 737–300, –400, and –500 series ATD and filtered at Channel Frequency to widespread fatigue damage (WFD). airplanes. The NPRM published in the VerDate Sep<11>2014 17:30 Jul 31, 2017 Jkt 241001 PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 E:\FR\FM\01AUR1.SGM 01AUR1

Federal Register / Vol. 82, No. 146 / Tuesday, August 1, 2017 / Rules and Regulations 35629 Federal Register on May 1, 2017 (82 FR We concur with the request. We have • Do not add any additional burden 20288). The NPRM was prompted by an redesignated paragraph (c) of the upon the public than was already evaluation by the DAH indicating that proposed AD as paragraph (c)(1) of this proposed in NPRM. the lower skin at the skin lap splice AD and added paragraph (c)(2) to this We also determined that these lower fastener row is subject to WFD. AD to state that installation of STC changes will not increase the economic The NPRM proposed to require ST01219SE does not affect the ability to burden on any operator or increase the repetitive inspections for cracking in the accomplish the actions required by this scope of this final rule. skin lap splice at the lower fastener row, AD. Therefore, for airplanes on which Related Service Information Under 1 and repair if necessary. STC ST01219SE is installed, a ‘‘change CFR Part 51 Comments in product’’ alternative method of We reviewed Boeing Alert Service compliance (AMOC) approval request is We gave the public the opportunity to Bulletin 737–53A1365, dated January not necessary to comply with the participate in developing this AD. The 23, 2017. The service information requirements of 14 CFR 39.17. describes procedures for eddy current following presents the comments received on the NPRM and the FAA’s Conclusion inspections for cracking at the skin lap response to each comment. splice in the lower fastener row, and We reviewed the relevant data, repair if necessary. This service Supportive Comment considered the comments received, and information is reasonably available Boeing stated that it concurred with determined that air safety and the because the interested parties have the NPRM. public interest require adopting this access to it through their normal course final rule with the change described of business or by the means identified Effect of Winglets on Accomplishment previously and minor editorial changes. in the ADDRESSES section. of the Proposed Actions We have determined that these minor Costs of Compliance Aviation Partners Boeing stated that changes: accomplishing the supplemental type We estimate that this AD affects 126 certificate (STC) ST01219SE does not • Are consistent with the intent that airplanes of U.S. registry. We estimate affect the actions specified in the was proposed in the NPRM for the following costs to comply with this NPRM. correcting the unsafe condition; and AD: ESTIMATED COSTS Action Labor cost Parts cost Cost per product Cost on U.S. operators Inspection ......... 84 work-hours × $85 per hour = $0 $7,140 per inspection cycle .......... $899,640 per inspection cycle. $7,140 per inspection cycle. We have received no definitive data Regulatory Findings Adoption of the Amendment that would enable us to provide cost estimates for the on-condition actions This AD will not have federalism Accordingly, under the authority specified in this AD. implications under Executive Order delegated to me by the Administrator, 13132. This AD will not have a the FAA amends 14 CFR part 39 as Authority for This Rulemaking substantial direct effect on the States, on follows: the relationship between the national Title 49 of the United States Code government and the States, or on the PART 39—AIRWORTHINESS specifies the FAA’s authority to issue distribution of power and DIRECTIVES rules on aviation safety. Subtitle I, responsibilities among the various section 106, describes the authority of levels of government. ■ 1. The authority citation for part 39 the FAA Administrator. Subtitle VII: continues to read as follows: For the reasons discussed above, I Aviation Programs, describes in more Authority: 49 U.S.C. 106(g), 40113, 44701. certify that this AD: detail the scope of the Agency’s authority. (1) Is not a ‘‘significant regulatory § 39.13 [Amended] action’’ under Executive Order 12866, We are issuing this rulemaking under ■ 2. The FAA amends § 39.13 by adding the authority described in Subtitle VII, (2) Is not a ‘‘significant rule’’ under the following new airworthiness Part A, Subpart III, Section 44701: DOT Regulatory Policies and Procedures directive (AD): ‘‘General requirements.’’ Under that (44 FR 11034, February 26, 1979), 2017–15–12 The Boeing Company: section, Congress charges the FAA with (3) Will not affect intrastate aviation Amendment 39–18972; Docket No. promoting safe flight of civil aircraft in in Alaska, and FAA–2017–0330; Directorate Identifier air commerce by prescribing regulations (4) Will not have a significant 2017–NM–016–AD. for practices, methods, and procedures economic impact, positive or negative, (a) Effective Date the Administrator finds necessary for on a substantial number of small entities This AD is effective September 5, 2017. safety in air commerce. This regulation under the criteria of the Regulatory mstockstill on DSK30JT082PROD with RULES is within the scope of that authority Flexibility Act. (b) Affected ADs because it addresses an unsafe condition None. that is likely to exist or develop on List of Subjects in 14 CFR Part 39 (c) Applicability products identified in this rulemaking Air transportation, Aircraft, Aviation (1) This AD applies to The Boeing action. safety, Incorporation by reference, Company Model 737–300, –400, and –500 Safety. series airplanes, certificated in any category, VerDate Sep<11>2014 17:30 Jul 31, 2017 Jkt 241001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 E:\FR\FM\01AUR1.SGM 01AUR1

35630 Federal Register / Vol. 82, No. 146 / Tuesday, August 1, 2017 / Rules and Regulations as identified in Boeing Alert Service Bulletin (2) The Condition column of Table 1 and (IBR) of the service information listed in this 737–53A1365, dated January 23, 2017. Table 2 of paragraph 1.E., ‘‘Compliance,’’ of paragraph under 5 U.S.C. 552(a) and 1 CFR (2) Installation of Supplemental Type Boeing Alert Service Bulletin 737–53A1365, part 51. Certificate (STC) ST01219SE (http:// dated January 23, 2017, refers to total flight (2) You must use this service information rgl.faa.gov/Regulatory_and_Guidance_ cycles ‘‘at the original issue date of this as applicable to do the actions required by Library/rgstc.nsf/0/EBD1CEC7B301293 service bulletin.’’ This AD, however, applies this AD, unless the AD specifies otherwise. E86257CB30045557A?OpenDocument& to the airplanes with the specified total flight (i) Boeing Alert Service Bulletin 737– Highlight=st01219se) does not affect the cycles as of the effective date of this AD. 53A1365, dated January 23, 2017. ability to accomplish the actions required by (ii) Reserved. (j) Alternative Methods of Compliance (3) For service information identified in this AD. Therefore, for airplanes on which (AMOCs) this AD, contact Boeing Commercial STC ST01219SE is installed, a ‘‘change in product’’ alternative method of compliance (1) The Manager, Los Angeles Aircraft Airplanes, Attention: Contractual & Data (AMOC) approval request is not necessary to Certification Office (ACO), FAA, has the Services (C&DS), 2600 Westminster Blvd., comply with the requirements of 14 CFR authority to approve AMOCs for this AD, if MC 110–SK57, Seal Beach, CA 90740–5600; 39.17. requested using the procedures found in 14 telephone 562–797–1717; Internet https:// CFR 39.19. In accordance with 14 CFR 39.19, www.myboeingfleet.com. (d) Subject send your request to your principal inspector (4) You may view this service information Air Transport Association (ATA) of or local Flight Standards District Office, as at the FAA, Transport Airplane Directorate, America Code 53; Fuselage. appropriate. If sending information directly 1601 Lind Avenue SW., Renton, WA. For to the manager of the ACO, send it to the information on the availability of this (e) Unsafe Condition attention of the person identified in material at the FAA, call 425–227–1221. This AD was prompted by an evaluation by paragraph (k) of this AD. Information may be (5) You may view this service information the design approval holder indicating that emailed to: 9-ANM-LAACO-AMOC- that is incorporated by reference at the the lower skin at the skin lap splice lower Requests@faa.gov. National Archives and Records fastener row is subject to widespread fatigue (2) Before using any approved AMOC, Administration (NARA). For information on damage. We are issuing this AD to detect and notify your appropriate principal inspector, the availability of this material at NARA, call correct cracks in the lower skin, which, if not or lacking a principal inspector, the manager 202–741–6030, or go to: http:// detected, could link up, resulting in reduced of the local flight standards district office/ www.archives.gov/federal-register/cfr/ibr- structural integrity of the airplane and certificate holding district office. locations.html. consequent uncontrolled decompression of (3) An AMOC that provides an acceptable Issued in Renton, Washington, on July 14, the airplane. level of safety may be used for any repair, 2017. modification, or alteration required by this (f) Compliance Dionne Palermo, AD if it is approved by the Boeing Comply with this AD within the Commercial Airplanes Organization Acting Manager, Transport Airplane compliance times specified, unless already Designation Authorization (ODA) that has Directorate, Aircraft Certification Service. done. been authorized by the Manager, Los Angeles [FR Doc. 2017–15477 Filed 7–31–17; 8:45 am] ACO, to make those findings. To be BILLING CODE 4910–13–P (g) Repetitive Inspections approved, the repair method, modification Except as provided by paragraph (i) of this deviation, or alteration deviation must meet AD, at the applicable time specified in the certification basis of the airplane, and the paragraph 1.E., ‘‘Compliance,’’ of Boeing DEPARTMENT OF TRANSPORTATION approval must specifically refer to this AD. Alert Service Bulletin 737–53A1365, dated (4) Except as required by paragraph (h) of January 23, 2017: Do external eddy current Federal Aviation Administration this AD: For service information that inspections at stringer S–14 on the left and contains steps that are labeled as Required right sides of the airplane (S–14L and S–14R) for Compliance (RC), the provisions of 14 CFR Part 39 for any crack in the skin lap splice at the paragraphs (j)(4)(i) and (j)(4)(ii) of this AD [Docket No. FAA–2017–0640; Directorate lower fastener row, in accordance with the apply. Identifier 2017–CE–020–AD; Amendment Accomplishment Instructions of Boeing Alert (i) The steps labeled as RC, including 39–18969; AD 2017–15–09] Service Bulletin 737–53A1365, dated January substeps under an RC step and any figures 23, 2017. Repeat the inspections thereafter at identified in an RC step, must be done to RIN 2120–AA64 the applicable times specified in paragraph comply with the AD. If a step or substep is 1.E., ‘‘Compliance,’’ of Boeing Alert Service labeled ‘‘RC Exempt,’’ then the RC Airworthiness Directives; Diamond Bulletin 737–53A1365, dated January 23, requirement is removed from that step or Aircraft Industries GmbH Airplanes 2017. substep. An AMOC is required for any deviations to RC steps, including substeps AGENCY: Federal Aviation (h) Repair Administration (FAA), DOT. and identified figures. If any crack is found during any inspection (ii) Steps not labeled as RC may be ACTION: Final rule; request for required by paragraph (g) of this AD, repair deviated from using accepted methods in comments. before further flight using a method approved accordance with the operator’s maintenance in accordance with the procedures specified or inspection program without obtaining SUMMARY: We are adopting a new in paragraph (j) of this AD. Although Boeing approval of an AMOC, provided the RC steps, airworthiness directive (AD) for certain Alert Service Bulletin 737–53A1365, dated including substeps and identified figures, can Diamond Aircraft Industries GmbH January 23, 2017, specifies to contact Boeing still be done as specified, and the airplane for appropriate action and specifies that Model DA 42 airplanes. This AD can be put back in an airworthy condition. action as ‘‘RC’’ (Required for Compliance), requires installing engine exhaust pipe this AD requires repair as specified in this (k) Related Information clamps with spring washers, repetitively paragraph. For more information about this AD, inspecting the engine exhaust pipe contact James Guo, Aerospace Engineer, clamps for cracks, and replacing the (i) Exceptions to Service Information Specifications Airframe Branch, ANM–120L, FAA, Los clamps if found cracked. This AD was mstockstill on DSK30JT082PROD with RULES Angeles ACO, 3960 Paramount Boulevard, prompted by cracks in the affected (1) Where Boeing Alert Service Bulletin Lakewood, CA 90712–4137; phone: 562–627– engine exhaust pipes, which could 737–53A1365, dated January 23, 2017, 5357; fax: 562–627–5210; email: james.guo@ specifies a compliance time ‘‘after the cause failure of the propeller regulating faa.gov. original issue date of this service bulletin,’’ valve because of hot exhaust gases this AD requires compliance within the (l) Material Incorporated by Reference coming from the fractured pipes. We are specified compliance time after the effective (1) The Director of the Federal Register issuing this AD to correct the unsafe date of this AD. approved the incorporation by reference condition on these products. VerDate Sep<11>2014 17:30 Jul 31, 2017 Jkt 241001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 E:\FR\FM\01AUR1.SGM 01AUR1


Document Created: 2018-10-24 11:44:28
Document Modified: 2018-10-24 11:44:28
CategoryRegulatory Information
CollectionFederal Register
sudoc ClassAE 2.7:
GS 4.107:
AE 2.106:
PublisherOffice of the Federal Register, National Archives and Records Administration
SectionRules and Regulations
ActionFinal rule.
DatesThis AD is effective September 5, 2017.
ContactJames Guo, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5357; fax: 562-627-5210; email: [email protected]
FR Citation82 FR 35628 
RIN Number2120-AA64
CFR AssociatedAir Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety
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