[Federal Register Volume 82, Number 58 (Tuesday, March 28, 2017)]
[Rules and Regulations]
[Pages 15284-15287]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-05768]
[[Page 15284]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9068; Directorate Identifier 2016-NM-067-AD;
Amendment 39-18838; AD 2017-06-14]
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 reports of cracks in the horizontal stabilizer lower
skins. This AD requires inspections for cracking of the horizontal
stabilizer lower skin, and corrective actions if necessary; and also
provides actions that would terminate certain repetitive inspections.
We are issuing this AD to address the unsafe condition on these
products.
DATES: This AD is effective May 2, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of May 2, 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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9068.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9068; 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: George Garrido, Aerospace Engineer,
Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification
Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone:
562-627-5232; 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 Federal Register on September 8, 2016 (81 FR 62022) (``the NPRM'').
The NPRM was prompted by reports of cracks in the horizontal stabilizer
lower skins. The NPRM proposed to require inspections for cracking of
the horizontal stabilizer lower skin, including repetitive inspections,
as applicable, and corrective actions if necessary; and also proposed
actions that would terminate certain repetitive inspections. We are
issuing this AD to detect and correct cracks in horizontal stabilizer
lower skins resulting in reduced local stiffness of the horizontal
stabilizer, which can cause heavy vibration leading to loss of
structural integrity of the horizontal stabilizer.
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 expressed support for the NPRM.
Request To Revise Repair Instructions
All Nippon Airways (ANA) requested that we revise paragraphs (h)(1)
and (h)(3) of the proposed AD to state ``repair common to the rear spar
lower chord between station (STA) 83.50 and STA 249.10,'' instead of
``repair.'' ANA stated that there might be a repair installed on the
lower skin of the horizontal stabilizer that is not addressed in Boeing
Special Attention Service Bulletin 737-55-1059, Revision 1, dated April
6, 2016 (``SASB 737-55-1059 R1''). ANA explained that some structural
repair manual repairs and external doublers are not applicable to the
inspection area specified in SASB 737-55-1059 R1.
We agree with ANA's request. Specifying the location of the
applicable repairs may reduce potential confusion. Therefore, we have
revised paragraphs (h)(1), (h)(2), and (h)(3) of this AD to specify the
location of the applicable repairs.
Request To Clarify Fastener Requirements
ANA requested that we clarify the fastener requirements. ANA stated
that figure 3 in Boeing Special Attention Service Bulletin 737-55-1059,
dated September 10, 1998, specifies to use blind rivets and Hi-lok
fasteners; however, compliance table 2, note (b), in SASB 737-55-1059
R1, states that doublers installed with solid rivets do not need to be
inspected for any loose or missing fasteners. ANA explained that Boeing
told ANA that Hi-lok fasteners do not require inspection for any loose
or missing fasteners.
We agree to clarify the fastener requirements. We infer that ANA is
requesting that we update paragraph (h) of this AD to specify that Hi-
lok fasteners do not require inspection. We have determined that Hi-lok
fasteners do not require inspection. Therefore, we have added paragraph
(i)(3) to this AD to specify that where SASB 737-55-1059 R1 specifies
that doublers installed with solid rivets do not need to be inspected
for loose or missing fasteners, this AD does not require doublers
installed with solid rivets or Hi-lok fasteners to be inspected for
loose or missing fasteners. We have also revised paragraph (h)(1) of
this AD to reference this exception.
Request To Revise Configuration Description
ANA requested that we revise paragraph (h) of the proposed AD to
refer to the horizontal stabilizer configuration with the applicable
repair installed side only. ANA asserted that the wording of paragraph
(h) of the proposed AD could be interpreted to require inspection of
both the repaired and unrepaired sides of the horizontal stabilizer.
We agree with ANA's request. The wording in the proposed AD is not
clear regarding what is required if an airplane has left and right
stabilizers that are different configurations. For example, the left-
side stabilizer may have a repair installed common to the rear spar
lower chord (configuration 2), whereas the right side may not have a
repair (configuration 1). We have revised the affected airplanes in
paragraph (g) of this AD from ``Group 1, Configuration 1,
[[Page 15285]]
airplanes'' to ``any Configuration 1 horizontal stabilizer on Group 1
airplanes''. We have revised the affected products in paragraph (h) of
this AD from ``Group 1, Configuration 2, airplanes'' to ``any
Configuration 2 horizontal stabilizer on Group 1 airplanes.''
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 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 final
rule. Therefore, for airplanes on which STC ST01219SE is installed, a
``change in product'' 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 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 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 SASB 737-55-1059 R1. The service information describes
procedures for doing inspections of the horizontal stabilizer lower
skin, and repairs. The service information also describes procedures
for doing actions that would terminate certain repetitive inspections.
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 270 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
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Parts Cost on U.S.
Action Labor cost cost Cost per product operators
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Inspection........................ 4 work-hours x $85 $0 $340 per inspection $91,800 per
per hour = $340 per cycle. inspection cycle.
inspection cycle.
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Estimated Costs for Optional Actions
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Parts
Action Labor cost cost Cost per product
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Modification............................. Up to 51 work-hours per $721 Up to $5,056 per stabilizer.
stabilizer x $85 per hour =
$4,335.
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We estimate the following costs to do any necessary repairs that
will be required based on the results of the inspection. We have no way
of determining the number of aircraft that might need these repairs:
On-Condition Costs
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Parts
Action Labor cost cost Cost per product
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Skin splice repair....................... Up to 438 work-hours x $85 $0 Up to $37,230.
per hour = $37,230.
External doubler repair.................. 26 work-hours x $85 per hour 0 $2,210.
= $2,210.
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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.
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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):
2017-06-14 The Boeing Company: Amendment 39-18838; Docket No. FAA-
2016-9068; Directorate Identifier 2016-NM-067-AD.
(a) Effective Date
This AD is effective May 2, 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, as
identified in Boeing Special Attention Service Bulletin 737-55-1059,
Revision 1, dated April 6, 2016 (``SASB 737-55-1059 R1'').
(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 55; Horizontal
stabilizer.
(e) Unsafe Condition
This AD was prompted by reports of cracks in horizontal
stabilizer lower skins. We are issuing this AD to detect and correct
cracks in horizontal stabilizer lower skins, resulting in reduced
local stiffness of the stabilizer, which can cause heavy vibration
leading to loss of structural integrity of the horizontal
stabilizer.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspections, Related Investigative Actions, and Corrective Actions
for Configuration 1 Horizontal Stabilizers on Group 1 Airplanes
For any Configuration 1 horizontal stabilizer on Group 1
airplanes, as identified in SASB 737-55-1059 R1: Except as specified
in paragraph (i)(1) of this AD, at the applicable time specified in
paragraph 1.E., ``Compliance,'' of SASB 737-55-1059 R1, do a
detailed inspection for cracking of the horizontal stabilizer lower
skin; and do all applicable related investigative and corrective
actions; in accordance with the Accomplishment Instructions of SASB
737-55-1059 R1, except as specified in paragraph (i)(2) of this AD.
Do all applicable related investigative and corrective actions
before further flight. Repeat the inspection of the horizontal
stabilizer lower skin, if applicable, thereafter at the applicable
intervals specified in paragraph 1.E., ``Compliance,'' of SASB 737-
55-1059 R1. Options specified in SASB 737-55-1059 R1 for
accomplishing the inspections are acceptable for the corresponding
requirements of this paragraph provided that the inspections are
done at the applicable times in paragraph 1.E., ``Compliance,'' of
the SASB 737-55-1059 R1.
(h) Inspections, Related Investigative Actions, and Corrective Actions
for Configuration 2 Horizontal Stabilizers on Group 1 Airplanes
For any Configuration 2 horizontal stabilizer on Group 1
airplanes, as identified in SASB 737-55-1059 R1: Except as specified
in paragraph (i)(1) of this AD, at the applicable time specified in
paragraph 1.E., ``Compliance,'' of SASB 737-55-1059 R1, do the
actions specified in paragraphs (h)(1), (h)(2), and (h)(3) of this
AD; and do all applicable related investigative and corrective
actions; in accordance with the Accomplishment Instructions of SASB
737-55-1059 R1, except as specified in paragraph (i)(2) of this AD.
Do all applicable related investigative and corrective actions
before further flight. Repeat the inspections specified in
paragraphs (h)(1), (h)(2), and (h)(3) of this AD, if applicable,
thereafter at the applicable intervals specified in paragraph 1.E.,
``Compliance,'' of SASB 737-55-1059 R1. Options specified in SASB
737-55-1059 R1, for accomplishing the inspections are acceptable for
the corresponding requirements of this paragraph provided that the
inspections are done at the applicable times in paragraph 1.E.,
``Compliance,'' of SASB 737-55-1059 R1.
(1) Do a high frequency eddy current inspection for cracking of
the skin around any repair common to the rear spar lower chord
between station (STA) 83.50 and STA 249.10 which was done as
specified in the structural repair manual or any external doubler
repair, and a detailed inspection for any loose or any missing
fastener of repaired doublers, except as specified in paragraph
(i)(3) of this AD.
(2) Do a detailed inspection for cracking of the inspar lower
skin between STA 83.50 and STA 249.10, except in areas repaired
common to the rear spar lower chord.
(3) Do a low frequency eddy current inspection for cracking of
the forward fastener row of any external doubler repair common to
the rear spar lower chord between STA 83.50 and STA 249.10.
(i) Service Information Exceptions
(1) Where SASB 737-55-1059 R1 specifies a compliance time
``after the Revision 1 date of this service bulletin,'' this AD
requires compliance within the specified compliance time after the
effective date of this AD.
(2) If any cracking, corrosion, hole elongation, or loose or
missing fastener is found during any inspection required by this AD,
and SASB 737-55-1059 R1 specifies to contact Boeing for repair
instructions: Before further flight, repair the cracking, corrosion,
hole elongation, loose or missing fasteners using a method approved
in accordance with the procedures specified in paragraph (j) of this
AD.
(3) Where SASB 737-55-1059 R1 specifies that doublers installed
with solid rivets do not need to be inspected for loose or missing
fasteners, this AD does not require doublers installed with solid
rivets or Hi-lok fasteners to be inspected for loose or missing
fasteners.
(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.
(k) Related Information
For more information about this AD, contact George Garrido,
Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO,
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5232; 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 Special Attention Service Bulletin 737-55-1059,
Revision 1, dated April 6, 2016.
(ii) Reserved.
(3) For Boeing service information identified in this AD,
contact Boeing
[[Page 15287]]
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 March 16, 2017.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-05768 Filed 3-27-17; 8:45 am]
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