[Federal Register Volume 82, Number 40 (Thursday, March 2, 2017)]
[Proposed Rules]
[Pages 12303-12305]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-03996]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0126; Directorate Identifier 2016-NM-211-AD]
RIN 2120-AA64
Airworthiness Directives; the Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and
-500 series airplanes. This proposed AD was prompted by reports of
frame web cracking at certain locations. This proposed AD would require
repetitive inspections in certain locations of the frame web, and
corrective action if necessary. We are proposing this AD to address the
unsafe condition on these products.
DATES: We must receive comments on this proposed AD by April 17, 2017.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, 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. It is also
available on the Internet at http://www.regulations.gov by searching
for and locating Docket No. FAA-2017-0126.
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-
0126; 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 proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Gaetano Settineri, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6577; fax: 425-917-6590; email: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2017-0126;
Directorate Identifier 2016-NM-211-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
We have received reports of frame web cracking at the station (STA)
344 system penetration holes between stringer S-22L and stringer S-24L.
There were 11 reports of cracking on airplanes having accumulated
between 25,713 and 68,093 total flight cycles and between 55,058 and
76,358 total flight hours. Crack lengths ranged from 0.78 inch to 1.57
inches. Frame cracking is the result of fatigue caused by cyclic
pressurization of the fuselage. Undetected cracks can grow until the
frames sever. Ultimately, multiple adjacent frames could be severed, or
a severed frame could exist near cracks in
[[Page 12304]]
the chem-milled fuselage skin. This condition, if not corrected, could
result in uncontrolled decompression of the airplane.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 737-53A1354, dated
December 2, 2016. The service information describes procedures for
repetitive high frequency eddy current (HFEC), detailed, and general
visual inspections in certain locations of the frame web. 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.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements
This proposed AD would require accomplishing the actions specified
in the service information described previously, except as discussed
under ``Differences Between this Proposed AD and the Service
Information.'' For information on the procedures and compliance times,
see this service information at http://www.regulations.gov by searching
for and locating Docket No. FAA-2017-0126.
The phrase ``corrective actions'' is used in this proposed AD.
Corrective actions correct or address any condition found. Corrective
actions in an AD could include, for example, repairs.
Differences Between This Proposed AD and the Service Information
Boeing Alert Service Bulletin 737-53A1354, dated December 2, 2016,
specifies to contact the manufacturer for certain instructions, but
this proposed AD would require using repair methods, modification
deviations, and alteration deviations in one of the following ways:
In accordance with a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by the Boeing Commercial
Airplanes Organization Designation Authorization (ODA) whom we have
authorized to make those findings.
Costs of Compliance
We estimate that this proposed AD affects 82 airplanes of U.S.
registry. We estimate the following costs to comply with this proposed
AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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HFEC, detailed, and general 114 work-hours x $0 $9,690 per $794,580 per
visual inspections. $85 per hour = inspection cycle. inspection cycle.
$9,690 per
inspection cycle.
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We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this proposed
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
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the 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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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):
The Boeing Company: Docket No. FAA-2017-0126; Directorate Identifier
2016-NM-211-AD.
(a) Comments Due Date
We must receive comments by April 17, 2017.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any
category, as identified in Boeing Alert Service Bulletin 737-
53A1354, dated December 2, 2016.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of frame web cracking at station
(STA) 344 system
[[Page 12305]]
penetration holes between stringer S-22L and stringer S-24L. We are
issuing this AD to detect and correct such cracking, which could
grow in size until frames sever. Multiple adjacent severed frames,
or a severed frame near cracks in the chem-milled fuselage skin,
could result in an uncontrolled decompression of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Group 1 Airplanes: Inspections and Corrective Actions
For airplanes identified as Group 1 in Boeing Alert Service
Bulletin 737-53A1354, dated December 2, 2016: Within 120 days after
the effective date of this AD, inspect the left- and right-side
fuselage frames, as specified in Parts 2 and 3 of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1354, dated
December 2, 2016, and do all applicable corrective actions, using a
method approved in accordance with the procedures specified in
paragraph (j) of this AD. Do all applicable corrective actions
before further flight.
(h) Group 2 Airplanes: Repetitive Inspections and Corrective Actions
For airplanes identified as Group 2 in Boeing Alert Service
Bulletin 737-53A1354, dated December 2, 2016: At the applicable
times specified in paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1354, dated December 2, 2016, except as
required by paragraph (i)(1) of this AD: Do the inspections
specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD, and
do all applicable corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 757-
53A1354, dated December 2, 2016, except as required by paragraph
(i)(2) of this AD. Repeat the inspections thereafter at the
applicable times specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 757-53A1354, dated December 2, 2016.
Do all applicable corrective actions before further flight.
(1) Do high frequency eddy current (HFEC), detailed, and general
visual inspections for cracking of the left side section 41 lower
lobe frames, between STA 268.25 and STA 360.
(2) Do detailed and general visual inspections for cracking of
the right side section 41 lower lobe frames, between STA 268.25 and
STA 360.
(3) Do an HFEC inspection for cracking of the right side STA
312, STA 328, and STA 344, section 41 lower lobe frames.
(i) Service Information Exceptions
(1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1354, dated December 2, 2016, specifies a
compliance time ``after the original date of this service
bulletin,'' this AD requires compliance within the specified
compliance time after the effective date of this AD.
(2) Where Boeing Alert Service Bulletin 737-53A1354, dated
December 2, 2016, specifies to contact Boeing for repair
instructions, and specifies that action as Required for Compliance
(RC), this AD requires repair before further flight using a method
approved in accordance with the procedures specified in paragraph
(j) of this AD.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle 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)(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, Seattle 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 (i)(2) 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
(1) For more information about this AD, contact Gaetano
Settineri, Aerospace Engineer, Airframe Branch, ANM-120S, FAA,
Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone:
425-917-6577; fax: 425-917-6590; email: [email protected].
(2) 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. 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.
Issued in Renton, Washington, on February 21, 2017.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-03996 Filed 3-1-17; 8:45 am]
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