Airworthiness Directives; The Boeing Company Airplanes, 58709-58713 [2017-26619]
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Federal Register / Vol. 82, No. 239 / Thursday, December 14, 2017 / Rules and Regulations
Issued in Renton, Washington, on
December 6, 2017.
Dionne Palermo,
Acting Director, System Oversight Division,
Aircraft Certification Service.
(2) Model F28 Mark 0100 airplanes
equipped with Rolls-Royce Deutschland
TAY–620–15 engines.
(d) Subject
Air Transport Association (ATA) of
America Code 76, Engine controls.
[FR Doc. 2017–26833 Filed 12–13–17; 8:45 am]
BILLING CODE 4910–13–P
(e) Reason
This AD was prompted by a report of an
engine multiple fan blade-off (MFBO) event,
caused by engine fan flutter. We are issuing
this AD to prevent engine MFBO events,
which could lead to structural damage and
possible reduced controllability of the
airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(h) Alternative Methods of Compliance
(AMOCs)
The Manager, International Section,
Transport Standards 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 International Section, send it to the
attention of the person identified in
paragraph (i)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. 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.
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(i) Related Information
(1) Refer to MCAI EASA AD 2014–0055,
dated March 7, 2014, for related information.
You may examine the MCAI on the internet
at https://www.regulations.gov by searching
for and locating Docket No. FAA–2017–1103.
(2) For more information about this AD,
contact Tom Rodriguez, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW,
Renton, WA 98057–3356; telephone: 425–
227–1137; fax: 425–227–1149.
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14 CFR Part 39
[Docket No. FAA–2017–0473; Product
Identifier 2016–NM–195–AD; Amendment
39–19124; AD 2017–25–10]
Airworthiness Directives; The Boeing
Company Airplanes
Within 30 days after the effective date of
this AD, request instructions from the
Manager, International Section, Transport
Standards Branch, FAA, to address the
unsafe condition specified in paragraph (e) of
this AD; and accomplish the action(s) at the
times specified in, and in accordance with,
those instructions. Guidance can be found in
Mandatory Continuing Airworthiness
Information (MCAI) European Aviation
Safety Agency (EASA) AD 2014–0055, dated
March 7, 2014.
None.
Federal Aviation Administration
RIN 2120–AA64
(g) Required Action(s)
(j) Material Incorporated by Reference
DEPARTMENT OF TRANSPORTATION
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
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 indicating that wear of the
bearing plate slider bushings could
cause disconnection of certain elevator
hinges, which could excite the
horizontal stabilizer under certain inflight speed/altitude conditions and
lead to degradation of the structure.
This AD requires repetitive inspections
and checks of certain elevator hinges
and related components, repetitive
replacements and tests of the bearing
plate, and related investigative and
corrective actions, if necessary. We are
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective January 18,
2018.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of January 18, 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, 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–2017–
0473.
SUMMARY:
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58709
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–2017–
0473; 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:
George Garrido, Aerospace Engineer,
Airframe Section, FAA, Los Angeles
ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5357; fax: 562–627–
5210; email: george.garrido@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
May 18, 2017 (82 FR 22763). The NPRM
was prompted by a report indicating
that analysis following a special
certification review of the horizontal
stabilizer determined that wear of the
bearing plate slider bushings could
cause disconnection of elevator hinge
number 4 or number 6. This
disconnection could excite the
horizontal stabilizer under certain inflight speed/altitude conditions and
lead to degradation of the structure due
to tab flutter, hinge wear, spar chord
corrosion, hinge rib web chafing, hinge
rib chord cracking, and inspar lower
skin cracking. The NPRM proposed to
require repetitive inspections and
checks of elevator hinge numbers 4 and
6 and related components, repetitive
replacements and tests of the bearing
plate, and related investigative and
corrective actions if necessary.
We are issuing this AD to detect and
correct wear of the bearing plate slider
bushings, which could result in heavy
airplane vibration and damage and
could lead to departure of the elevator
and/or horizontal stabilizer from the
airplane, and loss of continued safe
flight and landing.
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Federal Register / Vol. 82, No. 239 / Thursday, December 14, 2017 / Rules and Regulations
Comments
We gave the public the opportunity to
participate in developing this final rule.
The following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Support for the NPRM
Air Line Pilots Association,
International (ALPA) concurred with
the content of the NPRM.
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Request To Change Paragraph (g) of
This AD
Boeing stated that no inspections are
specified in Boeing Alert Service
Bulletin 737–55A1099, Revision 1,
dated October 21, 2016, for Group 1
airplanes and requested that the
reference to Boeing Alert Service
Bulletin 737–55A1099, Revision 1,
dated October 21, 2016, be removed
from paragraph (g) of this AD.
The European Aviation Safety Agency
(EASA) observed that in paragraph (g) of
the proposed AD, the reference to
Boeing Alert Service Bulletin 737–
55A1099, Revision 1, dated October 21,
2016, for Group 1 airplanes, is not
consistent with the Accomplishment
Instructions of Boeing Alert Service
Bulletin 737–55A1099, Revision 1,
dated October 21, 2016, which states
only that Group 1 airplanes have
exceeded their limit of validity (LOV)
and gives no further advice.
We agree with the commenters. We
have removed the reference to Boeing
Alert Service Bulletin 737–55A1099,
Revision 1, dated October 21, 2016,
from the compliance requirements
specified in paragraph (g) of this AD.
Request To Extend Inspections and
Checks to All Hinges
EASA suggested that the inspections
and checks in the proposed AD be
extended to all hinges because any other
loose hinge could create overloading in
adjacent hinges, and therefore could
contribute to the failure of hinges 4 and
6.
We do not agree with the commenter’s
assessment. We have consulted with
Boeing and confirmed the following
information.
Hinge fittings 1 and 2 support thrust
loads only and do not have the sliding
bearing plates. Therefore, these fittings
do not need inspections to address the
unsafe condition.
Boeing’s flutter analysis shows that
failure (disconnect) at either hinge 4 or
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6 is flutter critical. However, a failed
hinge 3 or 5, with the shorter span
between adjacent hinges, will have less
weight relative to stiffness, such that
instability does not occur.
The fatigue loads on the affected
Model 737 airplane elevator are not
substantial. If hinge 3 or 5 becomes
loose, the load increase on hinge 4 or 6
is insignificant. If hinge 3 or 5 fails, the
inspection and replacement program in
Boeing Alert Service Bulletin 737–
55A1099, Revision 1, dated October 21,
2016, will still detect any crack at hinge
4 or 6 before it becomes critical. In
addition, the normal maintenance
procedure of hinge lubrication per the
Maintenance Planning Document during
a C check should detect a failed hinge
3 or 5.
We have not changed this AD in this
regard.
Request for Clarification of Group 2,
Configuration 1 Instructions
EASA requested clarification of the
reason that paragraph (i) of the proposed
AD includes no repeat instruction for
Group 2, Configuration 1 airplanes,
regarding bearing plate replacement.
Group 2, Configuration 1 airplanes are
not included in paragraph (i) of this AD,
which contains requirements for
repetitive bearing plate replacements
and tests, because these airplanes do not
have the bearing plates. We have not
changed this AD regarding this issue.
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) 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 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 final rule.
Request for Confirmation of Sufficient
Access
EASA requested confirmation that
sufficient access exists to adequately
inspect and test all areas via the
methods defined.
Boeing has confirmed that sufficient
access exists. Additionally, Boeing has
released 737–55A1099 Information
Notice 01, dated May 23, 2017, to notify
operators that hinge 4 inspections
cannot be accomplished if existing
repairs are installed in accordance with
Boeing Special Attention Service
Bulletin 737–55–1059, Revision 1, dated
April 6, 2016. In that case, alternative
inspection procedures must be
approved in accordance with the
procedures specified in paragraph (m) of
this AD.
Costs of Compliance
Effect of Winglets on Accomplishment
of the Proposed Actions
Aviation Partners Boeing stated that
accomplishing the Supplemental Type
We estimate that this AD affects 192
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
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Related Service Information Under 1
CFR Part 51
We reviewed Boeing Alert Service
Bulletin 737–55A1099, Revision 1,
dated October 21, 2016. The service
information describes procedures for
repetitive inspections and checks of
elevator hinge numbers 4 and 6 and
related components, repetitive
replacements and tests of the bearing
plate, 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.
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Federal Register / Vol. 82, No. 239 / Thursday, December 14, 2017 / Rules and Regulations
58711
ESTIMATED COSTS
Cost per
product
Action
Labor cost
Elevator hinge high frequency eddy current (HFEC) inspection, loose bolt
check.
Horizontal stabilizer HFEC and low frequency eddy current (LFEC) inspection, loose bolt check.
Horizontal stabilizer detailed corrosion
inspection.
Elevator general visual inspection for
ply damage.
Elevator skin tap test inspection for
delamination.
Elevator hinge bearing plate replacement and binding test.
15 work-hours × $85 per hour = $1,275
per inspection/check cycle.
$0
$1,275 per inspection/check cycle.
13 work-hours × $85 per hour = $1,105
per inspection/check cycle.
0
$1,105 per inspection/check cycle.
5 work-hours × $85 per hour = $425
per inspection cycle.
Up to 4 work-hours × $85 per hour =
$340 per inspection cycle.
Up to 6 work-hours × $85 per hour =
$510 per inspection cycle.
Up to 20 work-hours × $85 per hour =
$1,700 per replacement/test cycle.
0
Elevator hinge fitting HFEC inspection ..
Up to 5 work-hours × $85 per hour =
$425 per inspection cycle.
$425 per inspection
cycle.
Up to $340 per inspection cycle.
Up to $510 per inspection cycle.
Up to $6,560 per
replacement/test
cycle.
Up to $425 per inspection cycle.
We estimate the following costs to do
any necessary related investigative and
corrective actions that would be
Parts cost
0
0
4,860
0
required based on the results of the
inspection. We have no way of
Cost on U.S.
operators
$244,800 per inspection/check
cycle.
$212,160 per inspection/check
cycle.
$81,600 per inspection cycle.
Up to $65,280 per
inspection cycle.
Up to $97,920 per
inspection cycle.
Up to $1,259,520
per replacement/
test cycle.
Up to $81,600 per
inspection cycle.
determining the number of aircraft that
might need these actions:
ON-CONDITION COSTS
Labor cost
Elevator hinge conditional inspections, measurements, replacements, and repairs.
Horizontal stabilizer conditional inspections, replacements, and repairs.
28 work-hours × $85 per hour = $2,380 ......................
1 $0
$2,380
28 work-hours × $85 per hour = $2,380 ......................
1 $0
2,380
1 We
have received no definitive data that would enable us to provide cost estimates for the parts for on-condition repairs.
Authority for This Rulemaking
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Parts cost
Cost per
product
Action
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.
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
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Compliance and Airworthiness
Division, but during this transition
period, the Executive Director has
delegated the authority to issue ADs
applicable to transport category
airplanes to the Director of the System
Oversight Division.
under the criteria of the Regulatory
Flexibility Act.
Regulatory Findings
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
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
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List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2017–25–10 The Boeing Company:
Amendment 39–19124; Docket No.
FAA–2017–0473; Product Identifier
2016–NM–195–AD.
(a) Effective Date
This AD is effective January 18, 2018.
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Federal Register / Vol. 82, No. 239 / Thursday, December 14, 2017 / Rules and Regulations
(b) Affected ADs
None.
(c) Applicability
(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/ebd1cec7b301293e
86257cb30045557a/$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, Stabilizers.
(e) Unsafe Condition
This AD was prompted by a report
indicating that wear of the bearing plate
slider bushings could cause disconnection of
elevator hinge number 4 or number 6, which
could excite the horizontal stabilizer under
certain in-flight speed/altitude conditions
and lead to degradation of the structure,
departure of the elevator or horizontal
stabilizer from the airplane, and loss of
continued safe flight and landing.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Actions for Group 1 Airplanes
For airplanes identified as Group 1 in
Boeing Alert Service Bulletin 737–55A1099,
Revision 1, dated October 21, 2016: Within
120 days after the effective date of this AD,
do inspections and checks of the elevator and
horizontal stabilizer at elevator hinge
numbers 4 and 6 and the replacement and
test of the bearing plate at elevator hinge
numbers 4 and 6, and do all applicable
related investigative and corrective actions,
using a method approved in accordance with
the procedures specified in paragraph (m) of
this AD.
(h) Inspections and Checks for Groups 2 and
3 Airplanes
For airplanes identified as Groups 2 and 3
in Boeing Alert Service Bulletin 737–
55A1099, Revision 1, dated October 21, 2016:
Except as required by paragraph (j)(1) of this
AD, at the applicable time specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–55A1099,
Revision 1, dated October 21, 2016, do the
applicable inspections and checks of elevator
hinge numbers 4 and 6 and related
components specified in paragraphs (h)(1)
through (h)(8) of this AD, and do all
applicable related investigative and
corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–55A1099, Revision 1,
dated October 21, 2016, except as required by
paragraph (j)(2) of this AD. Do all applicable
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related investigative and corrective actions
before further flight. Repeat the actions
specified in paragraphs (h)(1) through (h)(8)
of this AD thereafter at the applicable times
specified in paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–55A1099,
Revision 1, dated October 21, 2016.
(1) For Groups 2 and 3 airplanes: A high
frequency eddy current (HFEC) inspection for
cracking of the elevator hinge numbers 4 and
6.
(2) For Groups 2 and 3 airplanes: A loose
bolt check at elevator hinge numbers 4 and
6.
(3) For Groups 2 and 3 airplanes: An HFEC
inspection and low frequency eddy current
(LFEC) inspection for cracking of the
horizontal stabilizer forward of elevator
hinge numbers 4 and 6.
(4) For Groups 2 and 3 airplanes: A loose
bolt check of horizontal stabilizer attach
plates at elevator hinge numbers 4 and 6.
(5) For Groups 2 and 3 airplanes: A
detailed inspection of the horizontal
stabilizer rear spar outer mold line, gusset
plate, and inspar skin for any corrosion.
(6) For Group 2, Configuration 2, and
Group 3 airplanes: A general visual
inspection of the elevator front spar around
hinge numbers 4 and 6 for any ply damage.
(7) For Group 2 and 3 airplanes: A tap test
inspection of the elevator skin for any
delamination at elevator hinge numbers 4
and 6.
(8) For Group 2, Configuration 2, and
Group 3 airplanes on which elevator hinge
fitting assembly 65C31307–( ) is installed at
elevator hinge number 6: An HFEC
inspection of the hinge fitting for any crack.
(i) Repetitive Bearing Plate Replacement and
Test
For airplanes identified as Group 2,
Configuration 2, and Group 3 in Boeing Alert
Service Bulletin 737–55A1099, Revision 1,
dated October 21, 2016: Except as required
by paragraph (j)(1) of this AD, at the
applicable time specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–55A1099, Revision 1, dated
October 21, 2016, do the actions specified in
paragraphs (i)(1) and (i)(2) of this AD, and do
all applicable related investigative and
corrective actions, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–55A1099, Revision 1,
dated October 21, 2016, except as required by
paragraph (j)(2) of this AD. All applicable
related investigative and corrective actions
must be done before further flight. Repeat the
actions specified in paragraphs (i)(1) and
(i)(2) of this AD thereafter at the applicable
time specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–55A1099, Revision 1, dated
October 21, 2016.
(1) Replace the bearing plates at elevator
hinge numbers 4 and 6.
(2) Do an elevator hinge bearing plate
binding test at elevator hinge numbers 4 and
6.
(j) Exceptions to Service Information
Specifications
(1) Where Boeing Alert Service Bulletin
737–55A1099, Revision 1, dated October 21,
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2016, 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) Although Boeing Alert Service Bulletin
737–55A1099, Revision 1, dated October 21,
2016, 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 (m) of this
AD.
(k) Parts Installation Limitation
As of the effective date of this AD: A
horizontal stabilizer, an elevator, or a bearing
plate may be installed on any airplane,
provided the actions required by paragraphs
(h) and (i) of this AD are done within the
applicable compliance times specified in
paragraphs (h) and (i) of this AD.
(l) Credit for Previous Actions
This paragraph provides credit for the
actions specified in paragraphs (h) and (i) of
this AD, if those actions were performed
before the effective date of this AD using
Boeing Alert Service Bulletin 737–55A1099,
dated July 5, 2016.
(m) 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 (n) of this
AD. Information may be emailed to: 9-ANMLAACO-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 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) 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 (m)(4)(i) and (m)(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
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58713
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.
DEPARTMENT OF TRANSPORTATION
RIN 2120–AA64
Discussion
(n) Related Information
Airworthiness Directives; Alexander
Schleicher GmbH & Co.
Segelflugzeugbau Gliders
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Alexander Schleicher GmbH
& Co. Segelflugzeugbau Models ASH
25M and ASH 26E gliders. The NPRM
was published in the Federal Register
on September 22, 2017 (82 FR 44361).
The NPRM proposed to correct an
unsafe condition for the specified
products and was based on mandatory
continuing airworthiness information
(MCAI) originated by an aviation
authority of another country. The MCAI
states:
For more information about this AD,
contact George Garrido, Aerospace Engineer,
Airframe Section, FAA, Los Angeles ACO
Branch, 3960 Paramount Boulevard,
Lakewood, CA 90712–4137; phone: 562–627–
5357; fax: 562–627–5210; email:
george.garrido@faa.gov.
(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–
55A1099, Revision 1, dated October 21, 2016.
(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,
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/ibrlocations.html.
Issued in Renton, Washington, on
December 4, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft
Certification Service.
sradovich on DSK3GMQ082PROD with RULES
BILLING CODE 4910–13–P
VerDate Sep<11>2014
15:57 Dec 13, 2017
Jkt 244001
14 CFR Part 39
[Docket No. FAA–2017–0911; Product
Identifier 2017–CE–025–AD; Amendment
39–19121; AD 2017–25–07]
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Alexander Schleicher GmbH & Co.
Segelflugzeugbau Models ASH 25M and
ASH 26E gliders. This AD results from
mandatory continuing airworthiness
information (MCAI) issued by an
aviation authority of another country to
identify and correct an unsafe condition
on an aviation product. The MCAI
describes the unsafe condition as fatigue
cracks found on the exhaust silencer.
We are issuing this AD to require
actions to address the unsafe condition
on these products.
DATES: This AD is effective January 18,
2018.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of January 18, 2018.
ADDRESSES: You may examine the AD
docket on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0911; or in person at Document
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 service information identified in
this AD, contact Alexander Schleicher
GmbH & Co. Segelflugzeugbau,
Alexander-Schleicher-Str. 1, D–36163
Poppenhausen, Germany; phone: +49
(0) 06658 89–0; fax: +49 (0) 06658 89–
40; internet: https://www.alexanderschleicher.de; email: info@alexanderschleicher.de. You may view this
referenced service information at the
FAA, Policy and Innovation Division,
901 Locust, Kansas City, Missouri
64106. For information on the
availability of this material at the FAA,
call (816) 329–4148. It is also available
on the internet at https://
www.regulations.gov by searching for
Docket No. FAA–2017–0911.
SUMMARY:
(o) Material Incorporated by Reference
[FR Doc. 2017–26619 Filed 12–13–17; 8:45 am]
Federal Aviation Administration
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
Jim
Rutherford, Aerospace Engineer, FAA,
Small Airplane Standards Branch, 901
Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329–
4165; fax: (816) 329–4090; email:
jim.rutherford@faa.gov.
FOR FURTHER INFORMATION CONTACT:
SUPPLEMENTARY INFORMATION:
Occurrences were reported of finding
cracks on exhaust silencer part number (P/N)
800.65.0001, installed on ASK 21 Mi
powered sailplanes. Subsequent investigation
determined that the affected part is
susceptible to fatigue cracking and is also
installed on other Schleicher powered
sailplanes.
This condition, if not corrected, could lead
to heat damage in the engine compartment
and to the engine installation, possibly
resulting in reduced control of the powered
sailplane.
To address this potentially unsafe
condition, Schleicher issued Technical Note
(TN) ASK 21 Mi No. 11, TN ASW 22 BLE 50R
No. 16, TN ASH 25 M/Mi No. 32 and TN
ASH 26 E No. 19 (single document, hereafter
referred to as ‘the TN’ in this [EASA] AD),
to provide replacement instructions.
For the reasons described above, this
[EASA] AD requires replacement of the
affected exhaust silencer with an improved
part and introduces installation restrictions
of a part with P/N 800.65.0001].
The MCAI can be found in the AD
docket on the internet at https://
www.regulations.gov/
document?D=FAA-2017-0911-0002.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Conclusion
We reviewed the relevant data and
determined that air safety and the
public interest require adopting this AD
as proposed except for minor editorial
changes. We have determined that these
minor changes:
E:\FR\FM\14DER1.SGM
14DER1
]]>Agencies
[Federal Register Volume 82, Number 239 (Thursday, December 14, 2017)]
[Rules and Regulations]
[Pages 58709-58713]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-26619]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0473; Product Identifier 2016-NM-195-AD; Amendment
39-19124; AD 2017-25-10]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
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 indicating that wear of the
bearing plate slider bushings could cause disconnection of certain
elevator hinges, which could excite the horizontal stabilizer under
certain in-flight speed/altitude conditions and lead to degradation of
the structure. This AD requires repetitive inspections and checks of
certain elevator hinges and related components, repetitive replacements
and tests of the bearing plate, and related investigative and
corrective actions, if necessary. We are issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective January 18, 2018.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 18,
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, 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-2017-
0473.
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-2017-
0473; 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: George Garrido, Aerospace Engineer,
Airframe Section, FAA, Los Angeles ACO Branch, 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 all The Boeing Company
Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. The
NPRM published in the Federal Register on May 18, 2017 (82 FR 22763).
The NPRM was prompted by a report indicating that analysis following a
special certification review of the horizontal stabilizer determined
that wear of the bearing plate slider bushings could cause
disconnection of elevator hinge number 4 or number 6. This
disconnection could excite the horizontal stabilizer under certain in-
flight speed/altitude conditions and lead to degradation of the
structure due to tab flutter, hinge wear, spar chord corrosion, hinge
rib web chafing, hinge rib chord cracking, and inspar lower skin
cracking. The NPRM proposed to require repetitive inspections and
checks of elevator hinge numbers 4 and 6 and related components,
repetitive replacements and tests of the bearing plate, and related
investigative and corrective actions if necessary.
We are issuing this AD to detect and correct wear of the bearing
plate slider bushings, which could result in heavy airplane vibration
and damage and could lead to departure of the elevator and/or
horizontal stabilizer from the airplane, and loss of continued safe
flight and landing.
[[Page 58710]]
Comments
We gave the public the opportunity to participate in developing
this final rule. The following presents the comments received on the
NPRM and the FAA's response to each comment.
Support for the NPRM
Air Line Pilots Association, International (ALPA) concurred with
the content of the NPRM.
Request To Change Paragraph (g) of This AD
Boeing stated that no inspections are specified in Boeing Alert
Service Bulletin 737-55A1099, Revision 1, dated October 21, 2016, for
Group 1 airplanes and requested that the reference to Boeing Alert
Service Bulletin 737-55A1099, Revision 1, dated October 21, 2016, be
removed from paragraph (g) of this AD.
The European Aviation Safety Agency (EASA) observed that in
paragraph (g) of the proposed AD, the reference to Boeing Alert Service
Bulletin 737-55A1099, Revision 1, dated October 21, 2016, for Group 1
airplanes, is not consistent with the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-55A1099, Revision 1, dated October
21, 2016, which states only that Group 1 airplanes have exceeded their
limit of validity (LOV) and gives no further advice.
We agree with the commenters. We have removed the reference to
Boeing Alert Service Bulletin 737-55A1099, Revision 1, dated October
21, 2016, from the compliance requirements specified in paragraph (g)
of this AD.
Request To Extend Inspections and Checks to All Hinges
EASA suggested that the inspections and checks in the proposed AD
be extended to all hinges because any other loose hinge could create
overloading in adjacent hinges, and therefore could contribute to the
failure of hinges 4 and 6.
We do not agree with the commenter's assessment. We have consulted
with Boeing and confirmed the following information.
Hinge fittings 1 and 2 support thrust loads only and do not have
the sliding bearing plates. Therefore, these fittings do not need
inspections to address the unsafe condition.
Boeing's flutter analysis shows that failure (disconnect) at either
hinge 4 or 6 is flutter critical. However, a failed hinge 3 or 5, with
the shorter span between adjacent hinges, will have less weight
relative to stiffness, such that instability does not occur.
The fatigue loads on the affected Model 737 airplane elevator are
not substantial. If hinge 3 or 5 becomes loose, the load increase on
hinge 4 or 6 is insignificant. If hinge 3 or 5 fails, the inspection
and replacement program in Boeing Alert Service Bulletin 737-55A1099,
Revision 1, dated October 21, 2016, will still detect any crack at
hinge 4 or 6 before it becomes critical. In addition, the normal
maintenance procedure of hinge lubrication per the Maintenance Planning
Document during a C check should detect a failed hinge 3 or 5.
We have not changed this AD in this regard.
Request for Clarification of Group 2, Configuration 1 Instructions
EASA requested clarification of the reason that paragraph (i) of
the proposed AD includes no repeat instruction for Group 2,
Configuration 1 airplanes, regarding bearing plate replacement.
Group 2, Configuration 1 airplanes are not included in paragraph
(i) of this AD, which contains requirements for repetitive bearing
plate replacements and tests, because these airplanes do not have the
bearing plates. We have not changed this AD regarding this issue.
Request for Confirmation of Sufficient Access
EASA requested confirmation that sufficient access exists to
adequately inspect and test all areas via the methods defined.
Boeing has confirmed that sufficient access exists. Additionally,
Boeing has released 737-55A1099 Information Notice 01, dated May 23,
2017, to notify operators that hinge 4 inspections cannot be
accomplished if existing repairs are installed in accordance with
Boeing Special Attention Service Bulletin 737-55-1059, Revision 1,
dated April 6, 2016. In that case, alternative inspection procedures
must be approved in accordance with the procedures specified in
paragraph (m) of this AD.
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) 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 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 final
rule.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Alert Service Bulletin 737-55A1099, Revision 1,
dated October 21, 2016. The service information describes procedures
for repetitive inspections and checks of elevator hinge numbers 4 and 6
and related components, repetitive replacements and tests of the
bearing plate, 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 192 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:
[[Page 58711]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Elevator hinge high frequency 15 work-hours x $85 per $0 $1,275 per $244,800 per
eddy current (HFEC) hour = $1,275 per inspection/check inspection/check
inspection, loose bolt check. inspection/check cycle. cycle. cycle.
Horizontal stabilizer HFEC and 13 work-hours x $85 per 0 $1,105 per $212,160 per
low frequency eddy current hour = $1,105 per inspection/check inspection/check
(LFEC) inspection, loose bolt inspection/check cycle. cycle. cycle.
check.
Horizontal stabilizer detailed 5 work-hours x $85 per 0 $425 per $81,600 per
corrosion inspection. hour = $425 per inspection cycle. inspection cycle.
inspection cycle.
Elevator general visual Up to 4 work-hours x 0 Up to $340 per Up to $65,280 per
inspection for ply damage. $85 per hour = $340 inspection cycle. inspection cycle.
per inspection cycle.
Elevator skin tap test Up to 6 work-hours x 0 Up to $510 per Up to $97,920 per
inspection for delamination. $85 per hour = $510 inspection cycle. inspection cycle.
per inspection cycle.
Elevator hinge bearing plate Up to 20 work-hours x 4,860 Up to $6,560 per Up to $1,259,520
replacement and binding test. $85 per hour = $1,700 replacement/test per replacement/
per replacement/test cycle. test cycle.
cycle.
Elevator hinge fitting HFEC Up to 5 work-hours x 0 Up to $425 per Up to $81,600 per
inspection. $85 per hour = $425 inspection cycle. inspection cycle.
per inspection cycle.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary related
investigative and corrective actions that would be required based on
the results of the inspection. We have no way of determining the number
of aircraft that might need these actions:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Elevator hinge conditional inspections, 28 work-hours x $85 per hour = 1 $0 $2,380
measurements, replacements, and repairs. $2,380.
Horizontal stabilizer conditional inspections, 28 work-hours x $85 per hour = 1 $0 2,380
replacements, and repairs. $2,380.
----------------------------------------------------------------------------------------------------------------
1 We have received no definitive data that would enable us to provide cost estimates for the parts for on-
condition repairs.
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.
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 to
the Director of the System Oversight Division.
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):
2017-25-10 The Boeing Company: Amendment 39-19124; Docket No. FAA-
2017-0473; Product Identifier 2016-NM-195-AD.
(a) Effective Date
This AD is effective January 18, 2018.
[[Page 58712]]
(b) Affected ADs
None.
(c) Applicability
(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 55, Stabilizers.
(e) Unsafe Condition
This AD was prompted by a report indicating that wear of the
bearing plate slider bushings could cause disconnection of elevator
hinge number 4 or number 6, which could excite the horizontal
stabilizer under certain in-flight speed/altitude conditions and
lead to degradation of the structure, departure of the elevator or
horizontal stabilizer from the airplane, and loss of continued safe
flight and landing.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Actions for Group 1 Airplanes
For airplanes identified as Group 1 in Boeing Alert Service
Bulletin 737-55A1099, Revision 1, dated October 21, 2016: Within 120
days after the effective date of this AD, do inspections and checks
of the elevator and horizontal stabilizer at elevator hinge numbers
4 and 6 and the replacement and test of the bearing plate at
elevator hinge numbers 4 and 6, and do all applicable related
investigative and corrective actions, using a method approved in
accordance with the procedures specified in paragraph (m) of this
AD.
(h) Inspections and Checks for Groups 2 and 3 Airplanes
For airplanes identified as Groups 2 and 3 in Boeing Alert
Service Bulletin 737-55A1099, Revision 1, dated October 21, 2016:
Except as required by paragraph (j)(1) of this AD, at the applicable
time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-55A1099, Revision 1, dated October 21, 2016, do
the applicable inspections and checks of elevator hinge numbers 4
and 6 and related components specified in paragraphs (h)(1) through
(h)(8) of this AD, and do all applicable related investigative and
corrective actions, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-55A1099, Revision
1, dated October 21, 2016, except as required by paragraph (j)(2) of
this AD. Do all applicable related investigative and corrective
actions before further flight. Repeat the actions specified in
paragraphs (h)(1) through (h)(8) of this AD thereafter at the
applicable times specified in paragraph 1.E., ``Compliance,'' of
Boeing Alert Service Bulletin 737-55A1099, Revision 1, dated October
21, 2016.
(1) For Groups 2 and 3 airplanes: A high frequency eddy current
(HFEC) inspection for cracking of the elevator hinge numbers 4 and
6.
(2) For Groups 2 and 3 airplanes: A loose bolt check at elevator
hinge numbers 4 and 6.
(3) For Groups 2 and 3 airplanes: An HFEC inspection and low
frequency eddy current (LFEC) inspection for cracking of the
horizontal stabilizer forward of elevator hinge numbers 4 and 6.
(4) For Groups 2 and 3 airplanes: A loose bolt check of
horizontal stabilizer attach plates at elevator hinge numbers 4 and
6.
(5) For Groups 2 and 3 airplanes: A detailed inspection of the
horizontal stabilizer rear spar outer mold line, gusset plate, and
inspar skin for any corrosion.
(6) For Group 2, Configuration 2, and Group 3 airplanes: A
general visual inspection of the elevator front spar around hinge
numbers 4 and 6 for any ply damage.
(7) For Group 2 and 3 airplanes: A tap test inspection of the
elevator skin for any delamination at elevator hinge numbers 4 and
6.
(8) For Group 2, Configuration 2, and Group 3 airplanes on which
elevator hinge fitting assembly 65C31307-( ) is installed at
elevator hinge number 6: An HFEC inspection of the hinge fitting for
any crack.
(i) Repetitive Bearing Plate Replacement and Test
For airplanes identified as Group 2, Configuration 2, and Group
3 in Boeing Alert Service Bulletin 737-55A1099, Revision 1, dated
October 21, 2016: Except as required by paragraph (j)(1) of this AD,
at the applicable time specified in paragraph 1.E., ``Compliance,''
of Boeing Alert Service Bulletin 737-55A1099, Revision 1, dated
October 21, 2016, do the actions specified in paragraphs (i)(1) and
(i)(2) of this AD, and do all applicable related investigative and
corrective actions, in accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-55A1099, Revision
1, dated October 21, 2016, except as required by paragraph (j)(2) of
this AD. All applicable related investigative and corrective actions
must be done before further flight. Repeat the actions specified in
paragraphs (i)(1) and (i)(2) of this AD thereafter at the applicable
time specified in paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-55A1099, Revision 1, dated October 21, 2016.
(1) Replace the bearing plates at elevator hinge numbers 4 and
6.
(2) Do an elevator hinge bearing plate binding test at elevator
hinge numbers 4 and 6.
(j) Exceptions to Service Information Specifications
(1) Where Boeing Alert Service Bulletin 737-55A1099, Revision 1,
dated October 21, 2016, 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) Although Boeing Alert Service Bulletin 737-55A1099, Revision
1, dated October 21, 2016, 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 (m) of this AD.
(k) Parts Installation Limitation
As of the effective date of this AD: A horizontal stabilizer, an
elevator, or a bearing plate may be installed on any airplane,
provided the actions required by paragraphs (h) and (i) of this AD
are done within the applicable compliance times specified in
paragraphs (h) and (i) of this AD.
(l) Credit for Previous Actions
This paragraph provides credit for the actions specified in
paragraphs (h) and (i) of this AD, if those actions were performed
before the effective date of this AD using Boeing Alert Service
Bulletin 737-55A1099, dated July 5, 2016.
(m) 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 (n) 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) 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 (m)(4)(i) and
(m)(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
[[Page 58713]]
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.
(n) Related Information
For more information about this AD, contact George Garrido,
Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch,
3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-
5357; fax: 562-627-5210; email: [email protected].
(o) 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 737-55A1099, Revision 1, dated
October 21, 2016.
(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, 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 December 4, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-26619 Filed 12-13-17; 8:45 am]
BILLING CODE 4910-13-P
