Document ID: FAA-2018-0412-0011
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2018-09-26T04:00Z

[Federal Register Volume 83, Number 187 (Wednesday, September 26, 2018)]
[Rules and Regulations]
[Pages 48527-48530]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-20358]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0412; Product Identifier 2017-NM-180-AD; Amendment 
39-19420; AD 2018-19-20]
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 superseding Airworthiness Directive (AD) 2010-25-06, 
which applied to certain The Boeing Company Model 737-200, -300, -400, 
and -500 series airplanes. AD 2010-25-06 required repetitive 
inspections for cracking of certain fuselage frames and stub beams, and 
corrective actions if necessary. AD 2010-25-06 also provided for an 
optional repair, which terminated the repetitive inspections. For 
airplanes on which a certain repair was done, AD 2010-25-06 also 
required repetitive inspections for cracking of certain fuselage frames 
and stub beams, and corrective actions if necessary. This AD retains 
the actions required by AD 2010-25-06 and expands the inspection area. 
This AD was prompted by additional cracking found in areas not covered 
by the inspections in AD 2010-25-06. We are issuing this AD to address 
the unsafe condition on these products.

DATES: This AD is effective October 31, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of October 31, 
2018.

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 service information at the 
FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. 
For information on the availability of this material at the FAA, call 
206-231-3195. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0412.

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-2018-
0412; or in person at Docket Operations 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 Docket Operations (phone: 800-647-
5527) is 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 Section, Los Angeles ACO Branch, FAA, 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 to supersede AD 2010-25-06, Amendment 39-16539 (75 FR 81409, 
December 28, 2010) (``AD 2010-25-06''). AD 2010-25-06 applied to 
certain Model 737-200, -300, -400, and -500 series airplanes. The NPRM 
published in the Federal Register on May 15, 2018 (83 FR 22422). The 
NPRM was prompted by additional cracking found in areas not covered by 
the inspections in AD 2010-25-06. The NPRM proposed to retain the 
actions required by AD 2010-25-06 and expand the inspection area. We 
are issuing this AD

[[Page 48528]]

to address fatigue cracking of certain fuselage frames and stub beams 
and possible severed frames, which could result in reduced structural 
integrity of the frames. This reduced structural integrity can increase 
loading in the fuselage skin, which will accelerate skin crack growth 
and could result in rapid decompression of the fuselage.

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.

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 agree with the commenter. 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.

Request To Clarify Compliance Language

    Boeing asked that the compliance language in paragraphs (g), (h), 
(i), (j) and (k) of the proposed AD be changed since there are multiple 
conditions and compliance times specified in paragraph 1.E., 
``Compliance'' of the referenced service information. Boeing asked that 
the wording in these paragraphs be changed from ``at the applicable 
time'' specified in tables 1, 2, 3, 4, 5, and 9, respectively, to ``at 
the applicable condition and time'' specified in tables 1, 2, 3, 4, 5, 
and 9, respectively. Boeing stated that these changes would provide 
clarification.
    Although we do not agree to revise this AD as requested by the 
commenter, we agree to clarify the compliance language. The phrase ``at 
the applicable time'' means the compliance time associated with a given 
condition, as specified in the applicable table in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, Revision 
3, dated November 13, 2017. We have not changed this AD in this regard.

Addition of Omitted Word

    We inadvertently omitted the word ``in'' prior to the word 
``table'' in the phrase ``. . . the applicable time specified table . . 
.'' in certain sentences in paragraphs (g), (h), (i), and (j) of the 
proposed AD. We have revised the applicable sentences in paragraphs 
(g), (h), (i), and (j) of this AD to read ``. . . the applicable time 
specified in table. . . .''

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 addressing 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 Boeing Alert Service Bulletin 737-53A1254, Revision 3, 
dated November 13, 2017. This service information describes procedures 
for detailed and eddy current inspections of the fuselage frame and 
over wing stub beam at body station (BS) 616, BS 639, and BS 597 or BS 
601, and buttock line (BL) 45.5 floor beam web at the BS 639 stub beam 
attachment, and related investigative and corrective actions. This 
service information is reasonably available because the interested 
parties have access to it through their normal course of business or by 
the means identified in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 67 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                    Labor cost         Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspections.....................  Up to 67 work-hours              $0   Up to $5,695 per     Up to $381,565 per
                                   x $85 per hour =                      inspection cycle.    inspection cycle.
                                   $5,695 per
                                   inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do certain necessary repairs/
replacements that would be required based on the results of the 
inspections. We have no way of determining the number of aircraft that 
might need these repairs/replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
               Action **                       Labor cost            Parts cost           Cost per product
----------------------------------------------------------------------------------------------------------------
Repairs/replacements..................  Up to 76 work-hours x                  *   Up to $6,460.
                                         $85 per hour = $6,460.
----------------------------------------------------------------------------------------------------------------
* All required parts are supplied by the operator. This cost is minimal, and we have no way to determine what an
  operator would pay for these parts.
** We have received no definitive data that would enable us to provide cost estimates for certain other repairs
  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.

[[Page 48529]]

    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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes and 
associated appliances to the Director of the System Oversight Division.

Regulatory Findings

    We have determined that 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 removing Airworthiness Directive (AD) 
2010-25-06, Amendment 39-16539 (75 FR 81409, December 28, 2010), and 
adding the following new AD:

2018-19-20 The Boeing Company: Amendment 39-19420; Docket No. FAA-
2018-0412; Product Identifier 2017-NM-180-AD.

(a) Effective Date

    This AD is effective October 31, 2018.

(b) Affected ADs

    This AD replaces AD 2010-25-06, Amendment 39-16539 (75 FR 81409, 
December 28, 2010) (``AD 2010-25-06'').

(c) Applicability

    (1) This AD applies to The Boeing Company Model 737-200, -300, -
400, and -500 series airplanes, certificated in any category, as 
identified in Boeing Alert Service Bulletin 737-53A1254, Revision 3, 
dated November 13, 2017.
    (2) Installation of Supplemental Type Certificate (STC) 
ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/
rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf) 
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 the detection of fatigue cracks at 
certain frame sections, in addition to stub beam cracking, caused by 
high flight cycle stresses from both pressurization and maneuver 
loads and additional cracking found in areas not covered by the 
inspections in AD 2010-25-06. We are issuing this AD to address 
fatigue cracking of certain fuselage frames and stub beams and 
possible severed frames, which could result in reduced structural 
integrity of the frames. This reduced structural integrity can 
increase loading in the fuselage skin, which will accelerate skin 
crack growth and could result in rapid decompression of the 
fuselage.

(f) Compliance

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

(g) Repetitive Inspections of Body Stations 616 and 639 Frames and Stub 
Beams and Corrective Actions

    At the applicable time specified in table 1 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, 
Revision 3, dated November 13, 2017: Do a detailed or high frequency 
eddy current (HFEC) inspection for cracking of the body station (BS) 
616 and 639 frames and stub beams and do all applicable related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1254, Revision 3, dated November 13, 2017, except as required by 
paragraph (m)(1) of this AD. Do all applicable related investigative 
and corrective actions before further flight. Thereafter, repeat the 
inspection at the applicable time specified in table 1 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, 
Revision 3, dated November 13, 2017.

(h) Repetitive Post-Repair Inspections of Body Stations 616 and 639 
Frames and Integral Stub Beams and Corrective Actions

    At the applicable time specified in table 2 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, 
Revision 3, dated November 13, 2017: Do the inspections required by 
paragraphs (h)(1) and (h)(2) of this AD; or the inspection required 
by paragraph (h)(3) of this AD; as applicable, in accordance with 
the Accomplishment Instructions of Boeing Alert Service Bulletin 
737-53A1254, Revision 3, dated November 13, 2017, except as required 
by paragraph (m)(1) of this AD. Do all applicable related 
investigative and corrective actions before further flight. 
Thereafter, repeat the inspection at the applicable time specified 
in table 2 of paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017.
    (1) Do a low frequency eddy current (LFEC) inspection of the 
web, and an HFEC inspection of the inner and outer chord common to 
the upper end fastener rows of the web splice doubler for cracking.
    (2) Do the inspection specified in paragraph (h)(2)(i) or 
(h)(2)(ii) of this AD.
    (i) Do a detailed inspection of the replacement frame section 
for cracking.
    (ii) Do an HFEC and LFEC inspection of the replacement frame 
section for cracking.
    (3) Do a detailed or HFEC inspection of the replacement stub 
beam for cracking.

(i) Repetitive Inspections of Buttock Line 45.5 Longitudinal Floor Beam 
Web at Body Station 639 Stub Beam Attachment and Corrective Actions

    For Group 1 and Group 2 airplanes as identified in Boeing Alert 
Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, 
at the time specified in table 3 or table 4, as applicable, of 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
737-53A1254, Revision 3, dated November 13, 2017, except as required 
by paragraph (m)(2) of this AD: Do the inspections required by 
paragraph (i)(1) and (i)(2) of this AD and all applicable corrective 
actions, in accordance with the Accomplishment Instructions of 
Boeing Alert

[[Page 48530]]

Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, 
except as required by paragraph (m)(1) of this AD. Do all applicable 
corrective actions before further flight. Thereafter, repeat the 
inspections at the time specified in table 3 or table 4, as 
applicable, of paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017.
    (1) Do an open-hole HFEC inspection for cracking of the buttock 
line (BL) 45.5 longitudinal floor beam web at each fastener hole 
common to the stub beam attachment angle.
    (2) Do an HFEC surface inspection for cracking of the BL 45.5 
longitudinal floor beam web around the fastener head/tail at each 
fastener location common to the backup strap.

(j) Repetitive Post-Repair Inspections of Buttock Line 45.5 
Longitudinal Floor Beam Web at Body Station 639 and Corrective Actions

    For Group 2 airplanes as identified in Boeing Alert Service 
Bulletin 737-53A1254, Revision 3, dated November 13, 2017, at the 
applicable time specified in table 5 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, 
Revision 3, dated November 13, 2017, except as required by paragraph 
(m)(2) of this AD: Do the inspections required by paragraphs (j)(1) 
and (j)(2) of this AD and all applicable corrective actions, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, 
except as required by paragraph (m)(1) of this AD. Do all applicable 
corrective actions before further flight. Thereafter, repeat the 
inspections at the applicable time specified in table 5 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, 
Revision 3, dated November 13, 2017.
    (1) Do an open-hole HFEC inspection for cracking of the BL 45.5 
longitudinal floor beam web filler at each fastener hole common to 
the stub beam attachment angle.
    (2) Do an HFEC surface inspection for cracking of the BL 45.5 
longitudinal floor beam web filler around the fastener head/tail at 
each fastener location common to the backup strap.

(k) Repetitive Inspections for Cracking of BS 616 Machined Stub Beam 
Upper Chord and Corrective Actions

    For Group 2 and Group 3 airplanes as identified in Boeing Alert 
Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, 
at the applicable time specified in table 9 of paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, 
Revision 3, dated November 13, 2017, except as required by paragraph 
(m)(2) of this AD; do detailed and medium frequency eddy current 
subsurface inspections for cracking of the BS 616 machined stub beam 
upper chord, and all applicable corrective actions, except as 
required by paragraph (m)(1) of this AD. Do all applicable 
corrective actions before further flight. Thereafter, repeat the 
inspections at the applicable time specified in table 9 of paragraph 
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1254, 
Revision 3, dated November 13, 2017.

(l) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD, using Boeing Alert Service Bulletin 737-
53A1254, Revision 1, dated July 9, 2009; or Boeing Alert Service 
Bulletin 737-53A1254, Revision 2, dated February 22, 2012.
    (2) This paragraph provides credit for actions required by 
paragraph (h) of this AD, if those actions were performed before the 
effective date of this AD, using Boeing Alert Service Bulletin 737-
53A1254, Revision 2, dated February 22, 2012.

(m) Exceptions to Service Information Specifications

    (1) Where Boeing Alert Service Bulletin 737-53A1254, Revision 3, 
dated November 13, 2017, specifies to contact Boeing for repair 
instructions: Before further flight, do the repair using a method 
approved in accordance with the procedures specified in paragraph 
(n) of this AD.
    (2) Where Paragraph 1.E., ``Compliance,'' of Boeing Alert 
Service Bulletin 737-53A1254, Revision 3, dated November 13, 2017, 
specifies a compliance time ``after the Revision 3 date of this 
service bulletin,'' this AD requires compliance within the specified 
compliance time after the effective date of this AD.

(n) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles ACO Branch, 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 certification office, send it to the attention of 
the person identified in paragraph (o)(1) of this AD. Information 
may be emailed to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair, 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 Branch, 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) AMOCs approved previously for AD 2010-25-06 are approved as 
AMOCs for the corresponding provisions of Boeing Alert Service 
Bulletin 737-53A1254, Revision 3, dated November 13, 2017, that are 
required by paragraphs (g) and (h) of this AD.

(o) Related Information

    (1) For information about this AD, contact Galib Abumeri, 
Aerospace Engineer, Airframe Section, Los Angeles ACO Branch, FAA, 
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5324; fax: 562-627-5210; email: [email protected].
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (p)(3) and (p)(4) of this AD.

(p) 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 737-53A1254, Revision 3, dated 
November 13, 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 
Standards Branch, 2200 South 216th St., Des Moines, WA. For 
information on the availability of this material at the FAA, call 
206-231-3195.
    (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 Des Moines, Washington, on September 10, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-20358 Filed 9-25-18; 8:45 am]
 BILLING CODE 4910-13-P