Airworthiness Directives; the Boeing Company Airplanes, 5893-5896 [2016-01827]

Agencies

[Federal Register Volume 81, Number 23 (Thursday, February 4, 2016)]
[Rules and Regulations]
[Pages 5893-5896]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-01827]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-1983; Directorate Identifier 2015-NM-020-AD;
Amendment 39-18388; AD 2016-03-01]
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 all The
Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series
airplanes. This AD was prompted by a report of a crack of the forward
leg of the left front spar lower chord and cracks on the lower wing
skin at three fastener holes common to the nacelle outboard side load
fitting. This AD requires repetitive inspections for cracks on the
front spar lower chord, inspar skin, and wing skin, and corrective
action if necessary. We are issuing this AD to detect and correct
fatigue cracking of the forward leg of the front spar lower chord,
inspar skin, and wing skin common to the nacelle outboard side load
fitting, which could adversely affect the structural integrity of the
wing.

DATES: This AD is effective March 10, 2016.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of March 10,
2016.

ADDRESSES: For service information identified in this final rule,
contact Boeing Commercial Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone
206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the availability of this material at the
FAA, call 425-227-1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
1983.

Examining the AD Docket

You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-

[[Page 5894]]

1983; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation,
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200
New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Jennifer Tsakoumakis, Aerospace
Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft
Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA
90712-4137; phone: 562-627-5264; fax: 562-627-5210; email:
jennifer.tsakoumakis@faa.gov.

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 737-100, -200, -200C, -300, -400, and -500 series airplanes. The
NPRM published in the Federal Register on June 24, 2015 (80 FR 36258)
(``the NPRM''). The NPRM was prompted by a report of a crack of the
forward leg of the left front spar lower chord and cracks on the lower
wing skin at three fastener holes common to the nacelle outboard side
load fitting. The NPRM proposed to require repetitive inspections for
cracks on the front spar lower chord, inspar skin, and wing skin, and
corrective action if necessary. We are issuing this AD to correct the
unsafe condition on these products.

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.

Support for the NPRM

Boeing stated that it concurs with the NPRM.

Effect of Winglets on Accomplishment of the NPRM

Southwest Airlines (SWA) requested clarification whether the
installation of Aviation Partners Boeing (APB) Supplemental Type
Certificate (STC) ST01219SE (https://rgl.faa.gov/
Regulatory_and_Guidance_Library/rgstc.nsf/0/
ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf) has any affect to
the ability of accomplishment of the action of this proposed AD (80 FR
36258, June 24, 2015). APB stated that the installation of winglets per
STC ST01219SE does not affect the accomplishment of the manufacturer's
service instructions.
We concur with APB's comment and agree to clarify. We have
redesignated paragraph (c) of the proposed AD (80 FR 36258, June 24,
2015) as paragraph (c)(1) and added new paragraph (c)(2) to this AD to
state that installation of STC ST01219SE (https://rgl.faa.gov/
Regulatory_and_Guidance_Library/rgstc.nsf/0/
ebd1cec7b301293e86257cb30045557a/$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.

Request for Critical Design Configuration Control Limitation (CDCCL)
Instructions

SWA requested that we add instructions to paragraph (i) of the
proposed AD (80 FR 36258, June 24, 2015) to specify that important
CDCCL information must be observed during access and close-up while
performing the actions specified in paragraph (i) of the proposed AD.
SWA explained that Boeing Alert Service Bulletin 737-57A1323, dated
December 5, 2014, does not contain any references to CDCCLs, despite
the required access to the fuel tank, in order to perform either option
1 or option 2 non-destructive test inspection requirements. SWA stated
that the access and close-up steps indicate, as a reference, the
maintenance planning document (section 4), which does not provide a
clear path to the airplane maintenance manual section that addresses
CDCCL requirements.
We agree with the commenter's request. Boeing Alert Service
Bulletin 737-57A1323, dated December 5, 2014, does not contain any
references to CDCCLs that are part of the airworthiness limitations
(AWLs). All applicable AWLs must still be observed while performing the
actions mandated by this AD. We have revised paragraph (i) of this AD
to state that while accomplishing the actions required by paragraph (i)
of this AD, operators must ensure that all applicable CDCCLs are
complied with.

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:
[Agr]re consistent with the intent that was proposed in
the NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

We reviewed Boeing Alert Service Bulletin 737-57A1323, dated
December 5, 2014. The service information describes procedures for
repetitive inspections for cracks on the left and right wing front spar
lower chord, inspar skin, and wing skin, and corrective action. The
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 331 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 (28 Group 2 7 work[dash]hours $0................ $595 per $16,660 per
airplanes). x $85 per hour = inspection cycle. inspection cycle.
$595 per
inspection cycle.
Inspection and fastener Up to 94 0................. Up to $7,990 per Up to $2,412,980
installation (302 Group 3 work[dash]hours x inspection cycle. per inspection
airplanes). $85 per hour = cycle.
$7,990 per
inspection cycle.
----------------------------------------------------------------------------------------------------------------

[[Page 5895]]

We have received no definitive data that will enable us to provide
cost estimates for the actions specified for the Group 1 airplane in
this AD.
We also have received no definitive data that will enable us to
provide cost estimates for the on-condition actions specified in this
AD.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.

Regulatory Findings

This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

Adoption of the Amendment

Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec. 39.13 [Amended]

0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):

2016-03-01 the Boeing Company: Amendment 39-18388; Docket No. FAA-
2015-1983; Directorate Identifier 2015-NM-020-AD.

(a) Effective Date

This AD is effective March 10, 2016.

(b) Affected ADs

None.

(1) This AD applies to all The Boeing Company Model 737-100, -
200, -200C, -300, -400, and -500 series airplanes, certificated in
any category.
(2) Installation of Supplemental Type Certificate (STC)
ST01219SE (https://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 57, Wings.

(e) Unsafe Condition

This AD was prompted by a report of a crack in the forward leg
of the left front spar lower chord and cracks on the lower wing skin
at three fastener holes common to the nacelle outboard side load
fitting. We are issuing this AD to detect and correct fatigue
cracking of the forward leg of the front spar lower chord, inspar
skin, and wing skin common to the nacelle outboard side load
fitting, which could adversely affect the structural integrity of
the wing.

(f) Compliance

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

(g) Inspections and Corrective Actions for Group 1 Airplanes

For Group 1 airplanes identified in Boeing Alert Service
Bulletin 737-57A1323, dated December 5, 2014: Within 120 days after
the effective date of this AD, do inspections of the left and right
wing front spar lower chord and inspar skin, and the left and right
wing nacelle outboard side load fitting fastener holes common to the
front spar lower chord and skin, and do all applicable corrective
actions, using a method approved in accordance with the procedures
specified in paragraph (k) of this AD.

(h) Repetitive Detailed Inspections and Corrective Actions

For Group 2 and 3 airplanes identified in Boeing Alert Service
Bulletin 737-57A1323, dated December 5, 2014: Except as provided by
paragraph (j)(1) of this AD, at the applicable time specified in
Table 1 of paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-57A1323, dated December 5, 2014, do a detailed
inspection for cracks on the left and right wing front spar lower
chord and inspar skin, and do all applicable corrective actions, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-57A1323, dated December 5, 2014, except as
specified in paragraph (j)(2) of this AD. Do all applicable
corrective actions before further flight. Repeat the inspection
thereafter at the applicable interval specified in Table 1 of
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-57A1323, dated December 5, 2014, except in areas repaired in
accordance with the procedures specified in paragraph (k) of this
AD.

(i) Repetitive High Frequency Eddy Current (HFEC) Inspections and
Corrective Actions

For Group 3 airplanes identified in Boeing Alert Service
Bulletin 737-57A1323, dated December 5, 2014: Except as provided by
paragraph (j)(1) of this AD, at the applicable time specified in
Table 2 or Table 3 of paragraph 1.E., ``Compliance,'' of Boeing
Alert Service Bulletin 737-57A1323, dated December 5, 2014, do the
actions specified in paragraphs (i)(1) or (i)(2) of this AD. Repeat
the inspection specified in either paragraph (i)(1) or (i)(2) of
this AD thereafter at the applicable interval specified in Table 2
or Table 3 of paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin737-57A1323, dated December 5, 2014. While
accomplishing the actions required by this paragraph, ensure that
all applicable critical design configuration control limitations are
complied with.
(1) Do an HFEC open hole probe inspection for cracks of the left
and right wing nacelle outboard side load fitting fastener holes
common to the front spar lower chord and skin, and perform all
applicable corrective actions, in accordance with Part 2, Option 1
of the Accomplishment Instructions of Boeing Alert Service Bulletin
737-57A1323, dated December 5, 2014, except as provided by paragraph
(j)(2) of this AD. Do all applicable corrective actions before
further flight.
(2) Do an HFEC surface probe inspection for cracks in the wing
inspar skin, and perform all applicable corrective actions, in
accordance with Part 2, Option 2 of the Accomplishment Instructions
of Boeing Alert Service Bulletin 737-57A1323, dated December 5,
2014, except as provided by paragraph (j)(2) of this AD. Do all
applicable corrective actions before further flight.

(j) Exceptions to Service Information Specifications

(1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-57A1323, dated December 5, 2014, specifies a
compliance time ``after the original issue date of this service
bulletin,'' this AD requires

[[Page 5896]]

compliance within the specified compliance time ``after the
effective date of this AD.''
(2) Although Boeing Alert Service Bulletin 737-57A1323, dated
December 5, 2014, specifies to contact Boeing for repair
instructions, and specifies that action as ``RC'' (Required for
Compliance), this AD requires repair before further flight using a
method approved in accordance with the procedures specified in
paragraph (k) of this AD.

(k) 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 (l) of this AD.
Information may be emailed to: 9-ANM-LAACO-AMOC-Requests@faa.gov.
(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)(2) of this AD: For
service information that contains steps that are labeled as Required
for Compliance (RC), the provisions of paragraphs (k)(4)(i) and
(k)(4)(ii) apply.
(i) The steps labeled as RC, including substeps under an RC step
and any figures identified in an RC step, must be done to comply
with the AD. An AMOC is required for any deviations to RC steps,
including substeps and identified figures.
(ii) Steps not labeled as RC may be deviated from using accepted
methods in accordance with the operator's maintenance or inspection
program without obtaining approval of an AMOC, provided the RC
steps, including substeps and identified figures, can still be done
as specified, and the airplane can be put back in an airworthy
condition.

(l) Related Information

For more information about this AD, contact Jennifer
Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los
Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137;
phone: 562-627-5264; fax: 562-627-5210; email:
jennifer.tsakoumakis@faa.gov.

(m) 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 737-57A1323, dated December 5,
2014.
(ii) Reserved.
(3) For Boeing service information identified in this AD,
contact Boeing Commercial Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207;
telephone 206-544-5000, extension 1; fax 206-766-5680; Internet
https://www.myboeingfleet.com.
(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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

Issued in Renton, Washington, on January 25, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-01827 Filed 2-3-16; 8:45 am]
BILLING CODE 4910-13-P

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