Airworthiness Directives; The Boeing Company Airplanes, 49494-49498 [2017-22950]
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Federal Register / Vol. 82, No. 206 / Thursday, October 26, 2017 / Rules and Regulations
limited to stowage of emergency
equipment or airplane- supplied
equipment (i.e., bedding) must meet the
design criteria described in the table
below. Enclosed stowage compartments
greater than 57 feet 3 inches cubic
interior volume are not permitted by
these special conditions.
DESIGN CRITERIA FOR ENCLOSED STOWAGE COMPARTMENTS NOT LIMITED TO STOWAGE OF EMERGENCY OR AIRPLANESUPPLIED EQUIPMENT
Applicability of fire-protection requirements by interior volume
Fire protection features
Less than
25 cubic feet
Compliant Materials of Construction 1 .............................
Smoke or Fire Detectors 2 ...............................................
Liner 3 ...............................................................................
Fire Location Detector 4 ...................................................
25 Cubic feet to
less than 57 Cubic feet
Yes ....................................
No ......................................
No ......................................
No ......................................
Yes ....................................
Yes ....................................
Conditional .........................
Yes ....................................
57 cubic feet
Yes.
Yes.
Yes.
Yes.
1 Compliant Materials of Construction: The material used in constructing each enclosed stowage compartment must at least be fire resistant
and must meet the flammability standards established for interior components (i.e., 14 CFR part 25 Appendix F, Parts I, IV, and V) per the requirements of § 25.853. For compartments less than 25 ft.3 in interior volume, the design must ensure the ability to contain a fire likely to occur
within the compartment under normal use.
2 Smoke or Fire Detectors: Enclosed stowage compartments equal to or exceeding 25 ft.3 in interior volume must be provided with a smoke- or
fire-detection system to ensure that a fire can be detected within a one-minute detection time. Flight tests must be conducted to show compliance with this requirement. Each system (or systems) must provide:
b A visual indication in the flight deck within one minute after the start of a fire.
b An aural warning in the suite compartment.
b A warning in the main passenger cabin. This warning must be readily detectable by a flight attendant, taking into consideration the locations
of flight attendants throughout the main passenger compartment during various phases of flight.
3 Liner: If material used in constructing the stowage compartment can be shown to meet the flammability requirements of a liner for a Class B
cargo compartment (i.e., § 25.855 at Amendment 25–116, and Appendix F, part I, paragraph (a)(2)(ii)), then no liner would be required for enclosed stowage compartments equal to or greater than 25 ft.3 but less than 57 ft.3 in interior volume. For all enclosed stowage compartments
equal to 57 ft.3 in interior volume, a liner must be provided that meets the requirements of § 25.855 for a Class B cargo compartment.
4 Fire Location Detector: If a suite compartment has enclosed stowage compartments exceeding 25 ft.3 interior volume that are located separately from the other stowage compartments (located, for example, away from one central location, such as the entry to the suite compartment or
a common area within the suite compartment, where the other stowage compartments are), that suite compartment would require additional fireprotection features and/or devices to assist the firefighter in determining the location of a fire.
8. Where suites are installed, the
design of each suite must:
a. Maintain minimum main aisle(s),
cross aisle(s), and passageway(s)
requirements of § 25.815 when
subjected to the ultimate inertia forces
listed in § 25.561(d).
b. Prevent structural failure or
deformation of components that could
block access to the available evacuation
routes (e.g., seats, doors, contents of
stowage compartments, etc.).
9. In addition to the requirements of
§ 25.562 for seat systems, which are
occupiable during taxi, takeoff, and
landing, the suite structure must be
designed for the additional loads
imposed by the seats as a result of the
conditions specified in § 25.562(b).
Issued in Renton, Washington, on October
19, 2017.
Suzanne Masterson,
Acting Manager, Transport Standards
Branch, Policy and Innovation Division,
Aircraft Certification Service.
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[FR Doc. 2017–23256 Filed 10–25–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0332; Product
Identifier 2016–NM–164–AD; Amendment
39–19084; AD 2017–22–04]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
The Boeing Company Model 737–200,
–200C, –300, –400, and –500 series
airplanes. This AD was prompted by
reports of skin doublers that disbonded
from their skin panels. This AD requires
repetitive inspections of fuselage skin
panels, and applicable on-condition
actions. We are issuing this AD to
address the unsafe condition on these
products.
SUMMARY:
This AD is effective November
30, 2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of November 30, 2017.
DATES:
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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
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–
0332.
ADDRESSES:
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–
0332; 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
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New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Jennifer Tsakoumakis, Aerospace
Engineer, Airframe Section, FAA, Los
Angeles ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5264; fax: 562–627–
5210; email: jennifer.tsakoumakis@
faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain The Boeing Company
Model 737–200, –200C, –300, –400, and
–500 series airplanes. The NPRM
published in the Federal Register on
May 2, 2017 (82 FR 20450). The NPRM
was prompted by reports of skin
doublers that disbonded from their skin
panels. The NPRM proposed to require
repetitive inspections of fuselage skin
panels, and applicable on-condition
actions. We are issuing this AD to detect
and correct disbonded skin panels,
which could result in fuselage skin
cracking, rapid decompression, and loss
of structural integrity of the airplane.
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.
Effect of Winglets on Accomplishment
of the Proposed Actions
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Aviation Partners Boeing stated that
accomplishing Supplemental Type
Certificate (STC) ST01219SE does not
affect the ability to accomplish 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 methods of
compliance (AMOC) approval request is
not necessary to comply with the
requirements of 14 CFR 39.17.
Request To Revise ‘‘Explanation of
Certain Compliance Times’’ Section
Boeing requested that the
‘‘Explanation of Certain Compliance
Times’’ section in the preamble of the
NPRM be revised to clarify that only
disbonded skin panels need to be
replaced. Boeing noted that, if a panel
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is disbonded, it is considered a suspect
panel that went through improper
processing during the phosphoric acid
anodization phase of manufacturing.
Boeing stated that the suspect panel
could develop an additional disbond,
which could lead to further damage, and
then the inspections described in the
service information might not be
adequate.
We acknowledge the commenter’s
request to clarify that only disbonded
skin panels need to be replaced, for the
reasons provided by the commenter. We
agree with the rationale for the request.
However, the ‘‘Explanation of Certain
Compliance Times’’ section only
appears in the preamble of the NPRM
and is not carried over into this final
rule; therefore, no change to this final
rule is necessary regarding this issue.
Request To Include Previously
Accomplished Actions as Terminating
Actions
Qantas requested that we include
previously accomplished repairs as
terminating actions in paragraph (i) of
the proposed AD. Qantas requested that
paragraph (i) of the proposed AD be
revised to include a provision for
previously installed repairs (solid skin
panel replacements) that were approved
by an authorized representative of the
Boeing Commercial Airplanes
Organization Designation Authorization
(ODA) via FAA Form 8110–3,
‘‘Statement of Compliance with the
Federal Aviation Regulations.’’ Qantas
stated that Boeing ODA-approved
repairs completed prior to issuance of
Boeing Alert Service Bulletin 737–
53A1349, dated August 23, 2016, were
not addressed in the NPRM. Qantas also
suggested that solid skin panel
replacements approved via FAA Form
8100–9, ‘‘Statement of Compliance with
Airworthiness Standards,’’ be included
as terminating action. Qantas stated that
including skin panel replacements
approved via FAA Form 8100–9 as
terminating action could help avoid
operators’ requests for AMOCs. In
addition, Qantas recommended that the
language used for approved repairs by
an authorized representative of the
Boeing ODA be revised, as it is not
specific to FAA Form 8110–3 or FAA
Form 8100–9.
We agree with the commenter’s
request. Paragraph (i)(1) of this AD
(paragraph (i) of the proposed AD)
addresses previously installed repairs
approved by an authorized
representative of the Boeing ODA.
Existing Boeing ODA-approved repairs
or preventative modifications are
included in notes in Part 1, Part 2, and
Part 8 of the Accomplishment
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49495
Instruction and in note (a) to tables 1
through 8 in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1349, dated August 23,
2016. Note (a) states, ‘‘If any Boeing
ODA approved preventative
modification or repair was previously
installed via FAA Form 8100–9 or
[structural repair manual] SRM repair
doubler (except disbond repair), initial
and repeat inspections are not required
at the repaired location only.’’
However, repairs that were not
approved by the Boeing ODA and
replacements not done using Boeing
Alert Service Bulletin 737–53A1349,
dated August 23, 2016, were not
addressed in the proposed AD.
Therefore, we have redesignated
paragraph (i) (in the proposed AD) as
paragraph (i)(1) and added paragraph
(i)(2) to this AD to state that any skin
panel replacement done before the
effective date of this AD terminates the
inspections required by paragraph (g) of
this AD for that skin panel only,
provided the replacement was done
using a skin panel manufactured on or
after April 1, 1997, and the replacement
was done using an FAA-approved
method. A replacement accomplished
using an FAA-approved method would
still address the unsafe condition and
the need for the inspections required by
paragraph (g) of this AD would be
terminated.
We have also added paragraph (i)(3)
to this AD to state that any FAAapproved reinforced repair doubler
(except disbond repair) installed before
the effective date of this AD terminates
the inspections required by paragraph
(g) of this AD at the repaired location
only.
Request To Allow Termination of All
Inspections
Southwest Airlines (SWA) requested
that we allow the terminating action
specified in paragraph (i) of the
proposed AD to terminate the initial
inspections in paragraph (g) of the
proposed AD and not only the repetitive
inspections in paragraph (g) of the
proposed AD. Specifically, SWA
requested that paragraph (i) of the
proposed AD be revised to include the
provision that replacement of any skin
panel in accordance with the
Accomplishment Instructions of Boeing
Alert Service Bulletin 737–53A1349,
dated August 23, 2016, except as
specified in paragraph (h)(2) of the
proposed AD, terminates the
requirement for the initial inspection
specified in paragraph (g) of the
proposed AD, for the replaced skin
panel only. SWA noted that an operator
could replace a skin panel prior to doing
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the initial inspection specified in
paragraph (g) of the proposed AD,
therefore the operator would not be
required to do the initial or repetitive
inspections specified in paragraph (g) of
the proposed AD.
We agree with the commenters’
requests. We have clarified paragraph
(i)(1) of this AD (paragraph (i) of the
proposed AD) to state that
accomplishment of any skin panel
replacement using a skin panel
manufactured on or after April 1, 1997,
terminates the inspections required by
paragraph (g) of this AD for that skin
panel only, provided the replacement is
done as specified in the
Accomplishment Instructions of Boeing
Alert Service Bulletin 737–53A1349,
dated August 23, 2016, except as
required by paragraph (h)(2) of this AD.
Request To Include an Additional
Terminating Action for AD 2003–14–06
SWA requested that paragraph (j) of
the proposed AD be revised to include
a provision that replacement of skin
panels, in accordance with the
Accomplishment Instructions of Boeing
Alert Service Bulletin 737–53A1349,
dated August 23, 2016, except as
required by paragraph (h)(2) of the
proposed AD, terminates all of the
requirements of AD 2003–14–06,
Amendment 39–13225 (68 FR 40759,
July 9, 2003; corrected July 21, 2003 (68
FR 42596) (‘‘AD 2003–14–06’’)). SWA
noted that an operator could replace a
skin panel prior to doing the initial
inspection specified in paragraph (g) of
the proposed AD; therefore, the operator
would not be required to do the initial
or repetitive inspections specified in
paragraph (g) of the proposed AD, and
all of the requirements of AD 2003–14–
06 would be terminated.
We agree with the commenter’s
request. We redesignated paragraph (j)
in the proposed AD as paragraph (j)(1)
and added paragraph (j)(2) to this AD to
include a statement that replacement of
any skin panel with a skin panel
manufactured on or after April 1, 1997,
as specified in the Accomplishment
Instructions of Boeing Alert Service
Bulletin 737–53A1349, dated August 23,
2016, except as required by paragraph
(h)(2) of this AD, terminates all of the
requirements of AD 2003–14–06 for that
skin panel only.
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 737–53A1349, dated August 23,
2016. The service information describes
procedures for repetitive inspections of
fuselage skin panels for cracking,
corrosion, and existing disbond repairs;
and applicable on-condition 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 169
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
ESTIMATED COSTS
Action
External general visual and
detailed inspections.
External high frequency bond
test inspection.
Ultrasonic disbond inspection
and internal detailed skin
inspection.
Labor cost
Parts cost
180 work-hours × $85 per
hour = $15,300 per inspection cycle.
450 work hours × $85 per
hour = $38,250 per inspection cycle.
630 work-hours × $85 per
hour = $53,550 per inspection cycle.
We estimate the following costs to do
any necessary on-condition actions that
Cost per product
$0
Cost on U.S. operators
$15,300 per inspection cycle
$2,585,700 per inspection
cycle.
0
$38,250 inspection cycle .......
$6,464,250 per inspection
cycle.
0
$53,550 per inspection cycle
$9,049,950 per inspection
cycle.
will be required based on the results of
the inspections. We have no way of
determining the number of aircraft that
might need these on-condition actions:
ON-CONDITION COSTS PER SKIN PANEL
Labor cost
Parts cost
On-condition inspections ................
Repairs ...........................................
Skin panel replacement ..................
Up to 25 work-hours × $85 per hour = $2,125 ....................................
Up to 68 work-hours × $85 per hour = $5,780 ....................................
304 work-hours × $85 per hour = $25,840 ..........................................
$0 .....................
Up to $100 .......
$95,000 ............
Authority for This Rulemaking
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Action
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
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
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Cost per product
Up to $2,125.
Up to $5,880.
$120,840.
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
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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
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):
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■
2017–22–04 The Boeing Company:
Amendment 39–19084; Docket No.
FAA–2017–0332; Product Identifier
2016–NM–164–AD.
(a) Effective Date
This AD is effective November 30, 2017.
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(b) Affected ADs
This AD affects AD 2003–14–06,
Amendment 39–13225 (68 FR 40759, July 9,
2003; corrected July 21, 2003 (68 FR 42956))
(‘‘AD 2003–14–06’’).
(c) Applicability
(1) This AD applies to The Boeing
Company Model 737–200, –200C, –300,
–400, and –500 series airplanes, certificated
in any category, as identified in Boeing Alert
Service Bulletin 737–53A1349, dated August
23, 2016.
(2) Installation of Supplemental Type
Certificate (STC) ST01219SE (https://
rgl.faa.gov/Regulatory_and_Guidance_
Library/rgstc.nsf/0/EBD1CEC7B301293
E86257CB30045557A?OpenDocument&
Highlight=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.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of skin
doublers that disbonded from their skin
panels. We are issuing this AD to detect and
correct disbonded skin panels, which could
result in fuselage skin cracking, rapid
decompression, and loss of structural
integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Actions Required for Compliance
Except as required by paragraph (h) of this
AD: Do all applicable actions identified as
required for compliance (‘‘RC’’) in, and in
accordance with, the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1349, dated August 23, 2016. Do the
actions at the applicable times specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1349, dated
August 23, 2016.
(h) Exceptions to Service Information
Specifications
(1) Where Boeing Alert Service Bulletin
737–53A1349, dated August 23, 2016, uses
the phrase ‘‘after the original issue of this
service bulletin,’’ for purposes of determining
compliance with the requirements of this AD,
the phrase ‘‘after the effective date of this
AD’’ must be used.
(2) Where Boeing Alert Service Bulletin
737–53A1349, dated August 23, 2016,
specifies contacting Boeing for instructions,
and specifies that action as ‘‘RC’’ (Required
for Compliance): This AD requires using a
method approved in accordance with the
procedures specified in paragraph (k) of this
AD.
(3) For replaced skin panels identified in
table 9 of paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–53A1349,
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49497
dated August 23, 2016, on which the onetime internal inspection specified in Boeing
Service Bulletin 737–53–1179, Revision 2,
dated October 25, 2001, has not been done:
The compliance time for accomplishment of
the actions specified in Part 8 of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1349, dated August
23, 2016, is at the latest of the times specified
in paragraphs (h)(3)(i), (h)(3)(ii), and
(h)(3)(iii) of this AD.
(i) Within 50,000 flight cycles after the skin
panel replacement.
(ii) Within 20,000 flight cycles after July
14, 2003 (the effective date of AD 2003–14–
16).
(iii) Within 4,500 flight cycles after the
effective date of this AD.
(i) Terminating Action for Required
Inspections
(1) Accomplishment of any skin panel
replacement using a skin panel manufactured
on or after April 1, 1997, terminates the
inspections required by paragraph (g) of this
AD for that skin panel only, provided the
replacement is done as specified in the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1349, dated August
23, 2016, except as required by paragraph
(h)(2) of this AD.
(2) Accomplishment of any skin panel
replacement done before the effective date of
this AD terminates the inspections required
by paragraph (g) of this AD for that skin
panel only, provided the conditions specified
in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD
are met.
(i) The replacement was done using a skin
panel manufactured on or after April 1, 1997.
(ii) The replacement was done using an
FAA-approved method.
(3) Installation of an FAA-approved
reinforced repair doubler (except disbond
repair) before the effective date of this AD
terminates the inspections required by
paragraph (g) of this AD at the repaired
location only.
(j) Terminating Action for AD 2003–14–06
(1) Accomplishment of the initial
inspections required by paragraph (g) of this
AD terminates all requirements of AD 2003–
14–06.
(2) Accomplishment of any skin panel
replacement with a skin panel manufactured
on or after April 1, 1997, as specified in the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1349, dated August
23, 2016, except as required by paragraph
(h)(2) of this AD, terminates all requirements
of AD 2003–14–06 for that skin panel only.
(k) 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 (l) of this
AD. Information may be emailed to: 9–ANM–
LAACO–AMOC–Requests@faa.gov.
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(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 (h)(2)
of this AD: For service information that
contains steps that are labeled as Required
for Compliance (RC), the provisions of
paragraphs (k)(4)(i) and (k)(4)(ii) 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.
ethrower on DSK3G9T082PROD with RULES
(l) Related Information
For more information about this AD,
contact Jennifer Tsakoumakis, Airframe
Section, FAA, Los Angeles ACO Branch,
3960 Paramount Boulevard, Lakewood, CA
90712–4137; phone: 562–627–5264; fax: 562–
627–5210; email: jennifer.tsakoumakis@
faa.gov.
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 737–
53A1349, dated August 23, 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
VerDate Sep<11>2014
18:08 Oct 25, 2017
Jkt 244001
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 October
11, 2017.
Dionne Palermo,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2017–22950 Filed 10–25–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0521; Product
Identifier 2016–NM–189–AD; Amendment
39–19086; AD 2017–22–06]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc., Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Bombardier, Inc., Model CL–600–2B16
(CL–601–3A, CL–601–3R, and CL–604
Variants) airplanes. This AD was
prompted by reports of fuel leaks in the
engine and auxiliary power unit (APU)
electrical fuel pump (EFP) cartridge/
canister electrical connectors and
conduits. This AD requires repetitive
inspections for fuel leakage at the
engine and APU fuel pumps, 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 November
30, 2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of November 30, 2017.
ADDRESSES: For service information
identified in this final rule, contact
ˆ
Bombardier, Inc., 400 Cote-Vertu Road
´
West, Dorval, Quebec H4S 1Y9, Canada;
Widebody Customer Response Center
North America toll-free telephone 1–
866–538–1247 or direct-dial telephone
1–514–855–2999; fax 514–855–7401;
email ac.yul@aero.bombardier.com;
Internet https://www.bombardier.com.
You may view this referenced service
information at the FAA, Transport
Standards Branch, 1601 Lind Avenue
SUMMARY:
PO 00000
Frm 00014
Fmt 4700
Sfmt 4700
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–
0521.
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–
0521; 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 street address for
the Docket Office (telephone 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:
Steven Dzierzynski, Aerospace
Engineer, Avionics and Administrative
Services Section, FAA, New York ACO
Branch, 1600 Stewart Avenue, Suite
410, Westbury, NY 11590; telephone
516–228–7367; fax 516–794–5531.
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 Bombardier, Inc., Model
CL–600–2B16 (CL–601–3A, CL–601–3R,
and CL–604 Variants) airplanes. The
NPRM published in the Federal
Register on June 2, 2017 (82 FR 25556)
(‘‘the NPRM’’). The NPRM was
prompted by reports of fuel leaks in the
engine and APU EFP cartridge/canister
electrical connectors and conduits. The
NPRM proposed to require repetitive
inspections for fuel leakage at the
engine and APU fuel pumps, and
related investigative and corrective
actions if necessary. We are issuing this
AD to detect and correct fuel leaks in
certain fuel pumps to remove a potential
fuel ignition hazard.
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Airworthiness Directive CF–2016–32R1,
dated October 12, 2016 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Bombardier, Inc., Model CL–
600–2B16 (CL–601–3A, CL–601–3R, and
CL–604 Variants) airplanes. The MCAI
states:
E:\FR\FM\26OCR1.SGM
26OCR1
]]>Agencies
[Federal Register Volume 82, Number 206 (Thursday, October 26, 2017)]
[Rules and Regulations]
[Pages 49494-49498]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-22950]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-0332; Product Identifier 2016-NM-164-AD; Amendment
39-19084; AD 2017-22-04]
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 certain
The Boeing Company Model 737-200, -200C, -300, -400, and -500 series
airplanes. This AD was prompted by reports of skin doublers that
disbonded from their skin panels. This AD requires repetitive
inspections of fuselage skin panels, and applicable on-condition
actions. We are issuing this AD to address the unsafe condition on
these products.
DATES: This AD is effective November 30, 2017.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of November 30,
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 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-
0332.
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-
0332; 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
[[Page 49495]]
New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Jennifer Tsakoumakis, Aerospace
Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5264; 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 737-200, -200C, -300, -400, and -500 series airplanes. The NPRM
published in the Federal Register on May 2, 2017 (82 FR 20450). The
NPRM was prompted by reports of skin doublers that disbonded from their
skin panels. The NPRM proposed to require repetitive inspections of
fuselage skin panels, and applicable on-condition actions. We are
issuing this AD to detect and correct disbonded skin panels, which
could result in fuselage skin cracking, rapid decompression, and loss
of structural integrity of the airplane.
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.
Effect of Winglets on Accomplishment of the Proposed Actions
Aviation Partners Boeing stated that accomplishing Supplemental
Type Certificate (STC) ST01219SE does not affect the ability to
accomplish 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 methods of compliance (AMOC) approval request is not
necessary to comply with the requirements of 14 CFR 39.17.
Request To Revise ``Explanation of Certain Compliance Times'' Section
Boeing requested that the ``Explanation of Certain Compliance
Times'' section in the preamble of the NPRM be revised to clarify that
only disbonded skin panels need to be replaced. Boeing noted that, if a
panel is disbonded, it is considered a suspect panel that went through
improper processing during the phosphoric acid anodization phase of
manufacturing. Boeing stated that the suspect panel could develop an
additional disbond, which could lead to further damage, and then the
inspections described in the service information might not be adequate.
We acknowledge the commenter's request to clarify that only
disbonded skin panels need to be replaced, for the reasons provided by
the commenter. We agree with the rationale for the request. However,
the ``Explanation of Certain Compliance Times'' section only appears in
the preamble of the NPRM and is not carried over into this final rule;
therefore, no change to this final rule is necessary regarding this
issue.
Request To Include Previously Accomplished Actions as Terminating
Actions
Qantas requested that we include previously accomplished repairs as
terminating actions in paragraph (i) of the proposed AD. Qantas
requested that paragraph (i) of the proposed AD be revised to include a
provision for previously installed repairs (solid skin panel
replacements) that were approved by an authorized representative of the
Boeing Commercial Airplanes Organization Designation Authorization
(ODA) via FAA Form 8110-3, ``Statement of Compliance with the Federal
Aviation Regulations.'' Qantas stated that Boeing ODA-approved repairs
completed prior to issuance of Boeing Alert Service Bulletin 737-
53A1349, dated August 23, 2016, were not addressed in the NPRM. Qantas
also suggested that solid skin panel replacements approved via FAA Form
8100-9, ``Statement of Compliance with Airworthiness Standards,'' be
included as terminating action. Qantas stated that including skin panel
replacements approved via FAA Form 8100-9 as terminating action could
help avoid operators' requests for AMOCs. In addition, Qantas
recommended that the language used for approved repairs by an
authorized representative of the Boeing ODA be revised, as it is not
specific to FAA Form 8110-3 or FAA Form 8100-9.
We agree with the commenter's request. Paragraph (i)(1) of this AD
(paragraph (i) of the proposed AD) addresses previously installed
repairs approved by an authorized representative of the Boeing ODA.
Existing Boeing ODA-approved repairs or preventative modifications are
included in notes in Part 1, Part 2, and Part 8 of the Accomplishment
Instruction and in note (a) to tables 1 through 8 in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1349, dated
August 23, 2016. Note (a) states, ``If any Boeing ODA approved
preventative modification or repair was previously installed via FAA
Form 8100-9 or [structural repair manual] SRM repair doubler (except
disbond repair), initial and repeat inspections are not required at the
repaired location only.''
However, repairs that were not approved by the Boeing ODA and
replacements not done using Boeing Alert Service Bulletin 737-53A1349,
dated August 23, 2016, were not addressed in the proposed AD.
Therefore, we have redesignated paragraph (i) (in the proposed AD) as
paragraph (i)(1) and added paragraph (i)(2) to this AD to state that
any skin panel replacement done before the effective date of this AD
terminates the inspections required by paragraph (g) of this AD for
that skin panel only, provided the replacement was done using a skin
panel manufactured on or after April 1, 1997, and the replacement was
done using an FAA-approved method. A replacement accomplished using an
FAA-approved method would still address the unsafe condition and the
need for the inspections required by paragraph (g) of this AD would be
terminated.
We have also added paragraph (i)(3) to this AD to state that any
FAA-approved reinforced repair doubler (except disbond repair)
installed before the effective date of this AD terminates the
inspections required by paragraph (g) of this AD at the repaired
location only.
Request To Allow Termination of All Inspections
Southwest Airlines (SWA) requested that we allow the terminating
action specified in paragraph (i) of the proposed AD to terminate the
initial inspections in paragraph (g) of the proposed AD and not only
the repetitive inspections in paragraph (g) of the proposed AD.
Specifically, SWA requested that paragraph (i) of the proposed AD be
revised to include the provision that replacement of any skin panel in
accordance with the Accomplishment Instructions of Boeing Alert Service
Bulletin 737-53A1349, dated August 23, 2016, except as specified in
paragraph (h)(2) of the proposed AD, terminates the requirement for the
initial inspection specified in paragraph (g) of the proposed AD, for
the replaced skin panel only. SWA noted that an operator could replace
a skin panel prior to doing
[[Page 49496]]
the initial inspection specified in paragraph (g) of the proposed AD,
therefore the operator would not be required to do the initial or
repetitive inspections specified in paragraph (g) of the proposed AD.
We agree with the commenters' requests. We have clarified paragraph
(i)(1) of this AD (paragraph (i) of the proposed AD) to state that
accomplishment of any skin panel replacement using a skin panel
manufactured on or after April 1, 1997, terminates the inspections
required by paragraph (g) of this AD for that skin panel only, provided
the replacement is done as specified in the Accomplishment Instructions
of Boeing Alert Service Bulletin 737-53A1349, dated August 23, 2016,
except as required by paragraph (h)(2) of this AD.
Request To Include an Additional Terminating Action for AD 2003-14-06
SWA requested that paragraph (j) of the proposed AD be revised to
include a provision that replacement of skin panels, in accordance with
the Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1349, dated August 23, 2016, except as required by paragraph (h)(2)
of the proposed AD, terminates all of the requirements of AD 2003-14-
06, Amendment 39-13225 (68 FR 40759, July 9, 2003; corrected July 21,
2003 (68 FR 42596) (``AD 2003-14-06'')). SWA noted that an operator
could replace a skin panel prior to doing the initial inspection
specified in paragraph (g) of the proposed AD; therefore, the operator
would not be required to do the initial or repetitive inspections
specified in paragraph (g) of the proposed AD, and all of the
requirements of AD 2003-14-06 would be terminated.
We agree with the commenter's request. We redesignated paragraph
(j) in the proposed AD as paragraph (j)(1) and added paragraph (j)(2)
to this AD to include a statement that replacement of any skin panel
with a skin panel manufactured on or after April 1, 1997, as specified
in the Accomplishment Instructions of Boeing Alert Service Bulletin
737-53A1349, dated August 23, 2016, except as required by paragraph
(h)(2) of this AD, terminates all of the requirements of AD 2003-14-06
for that skin panel only.
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 737-53A1349, dated August
23, 2016. The service information describes procedures for repetitive
inspections of fuselage skin panels for cracking, corrosion, and
existing disbond repairs; and applicable on-condition 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 169 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
External general visual and 180 work-hours x $0 $15,300 per $2,585,700 per
detailed inspections. $85 per hour = inspection cycle. inspection cycle.
$15,300 per
inspection cycle.
External high frequency bond test 450 work hours x 0 $38,250 inspection $6,464,250 per
inspection. $85 per hour = cycle. inspection cycle.
$38,250 per
inspection cycle.
Ultrasonic disbond inspection and 630 work-hours x 0 $53,550 per $9,049,950 per
internal detailed skin $85 per hour = inspection cycle. inspection cycle.
inspection. $53,550 per
inspection cycle.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary on-condition
actions that will be required based on the results of the inspections.
We have no way of determining the number of aircraft that might need
these on-condition actions:
On-Condition Costs per Skin Panel
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
On-condition inspections......... Up to 25 work-hours x $85 $0...................... Up to $2,125.
per hour = $2,125.
Repairs.......................... Up to 68 work-hours x $85 Up to $100.............. Up to $5,880.
per hour = $5,780.
Skin panel replacement........... 304 work-hours x $85 per $95,000................. $120,840.
hour = $25,840.
----------------------------------------------------------------------------------------------------------------
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
[[Page 49497]]
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):
2017-22-04 The Boeing Company: Amendment 39-19084; Docket No. FAA-
2017-0332; Product Identifier 2016-NM-164-AD.
(a) Effective Date
This AD is effective November 30, 2017.
(b) Affected ADs
This AD affects AD 2003-14-06, Amendment 39-13225 (68 FR 40759,
July 9, 2003; corrected July 21, 2003 (68 FR 42956)) (``AD 2003-14-
06'').
(c) Applicability
(1) This AD applies to The Boeing Company Model 737-200, -200C,
-300, -400, and -500 series airplanes, certificated in any category,
as identified in Boeing Alert Service Bulletin 737-53A1349, dated
August 23, 2016.
(2) Installation of Supplemental Type Certificate (STC)
ST01219SE (https://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/EBD1CEC7B301293E86257CB30045557A?OpenDocument&Highlight=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.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of skin doublers that disbonded
from their skin panels. We are issuing this AD to detect and correct
disbonded skin panels, which could result in fuselage skin cracking,
rapid decompression, and loss of structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Actions Required for Compliance
Except as required by paragraph (h) of this AD: Do all
applicable actions identified as required for compliance (``RC'')
in, and in accordance with, the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1349, dated August 23, 2016. Do
the actions at the applicable times specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1349, dated
August 23, 2016.
(h) Exceptions to Service Information Specifications
(1) Where Boeing Alert Service Bulletin 737-53A1349, dated
August 23, 2016, uses the phrase ``after the original issue of this
service bulletin,'' for purposes of determining compliance with the
requirements of this AD, the phrase ``after the effective date of
this AD'' must be used.
(2) Where Boeing Alert Service Bulletin 737-53A1349, dated
August 23, 2016, specifies contacting Boeing for instructions, and
specifies that action as ``RC'' (Required for Compliance): This AD
requires using a method approved in accordance with the procedures
specified in paragraph (k) of this AD.
(3) For replaced skin panels identified in table 9 of paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1349,
dated August 23, 2016, on which the one-time internal inspection
specified in Boeing Service Bulletin 737-53-1179, Revision 2, dated
October 25, 2001, has not been done: The compliance time for
accomplishment of the actions specified in Part 8 of the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1349, dated August 23, 2016, is at the latest of the times
specified in paragraphs (h)(3)(i), (h)(3)(ii), and (h)(3)(iii) of
this AD.
(i) Within 50,000 flight cycles after the skin panel
replacement.
(ii) Within 20,000 flight cycles after July 14, 2003 (the
effective date of AD 2003-14-16).
(iii) Within 4,500 flight cycles after the effective date of
this AD.
(i) Terminating Action for Required Inspections
(1) Accomplishment of any skin panel replacement using a skin
panel manufactured on or after April 1, 1997, terminates the
inspections required by paragraph (g) of this AD for that skin panel
only, provided the replacement is done as specified in the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1349, dated August 23, 2016, except as required by paragraph
(h)(2) of this AD.
(2) Accomplishment of any skin panel replacement done before the
effective date of this AD terminates the inspections required by
paragraph (g) of this AD for that skin panel only, provided the
conditions specified in paragraphs (i)(2)(i) and (i)(2)(ii) of this
AD are met.
(i) The replacement was done using a skin panel manufactured on
or after April 1, 1997.
(ii) The replacement was done using an FAA-approved method.
(3) Installation of an FAA-approved reinforced repair doubler
(except disbond repair) before the effective date of this AD
terminates the inspections required by paragraph (g) of this AD at
the repaired location only.
(j) Terminating Action for AD 2003-14-06
(1) Accomplishment of the initial inspections required by
paragraph (g) of this AD terminates all requirements of AD 2003-14-
06.
(2) Accomplishment of any skin panel replacement with a skin
panel manufactured on or after April 1, 1997, as specified in the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1349, dated August 23, 2016, except as required by paragraph
(h)(2) of this AD, terminates all requirements of AD 2003-14-06 for
that skin panel only.
(k) 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 (l) of this AD. Information may
be emailed to: [email protected].
[[Page 49498]]
(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 (h)(2) of this AD: For
service information that contains steps that are labeled as Required
for Compliance (RC), the provisions of paragraphs (k)(4)(i) and
(k)(4)(ii) 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.
(l) Related Information
For more information about this AD, contact Jennifer
Tsakoumakis, Airframe Section, FAA, Los Angeles ACO Branch, 3960
Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5264;
fax: 562-627-5210; email: [email protected].
(m) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 737-53A1349, dated August 23,
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 October 11, 2017.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2017-22950 Filed 10-25-17; 8:45 am]
BILLING CODE 4910-13-P
