Airworthiness Directives; The Boeing Company Airplanes, 29202-29206 [2016-11095]
Download as PDF
<![CDATA[
29202
Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules
Issued in Renton, Washington, on May 3,
2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
(k) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, 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 Branch, send it to ATTN:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov.
(i) 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. The AMOC
approval letter must specifically reference
this AD.
(ii) AMOCs approved previously for AD
2015–05–02, are approved as AMOCs for the
corresponding provisions of paragraphs (g)
and (h) of this AD.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
mstockstill on DSK3G9T082PROD with PROPOSALS
(j) New No Alternative Actions and/or
Intervals
After accomplishing the revision required
by paragraph (i) of this AD, no alternative
actions (e.g., inspections) and/or intervals
may be used unless the actions and/or
intervals are approved as an AMOC in
accordance with the procedures specified in
paragraph (k)(1) of this AD.
DEPARTMENT OF TRANSPORTATION
(l) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2015–0083, dated
May 12, 2015, for related information. This
MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2016–6429.
(2) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
You may view this service information at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
VerDate Sep<11>2014
16:58 May 10, 2016
Jkt 238001
[FR Doc. 2016–10914 Filed 5–10–16; 8:45 am]
BILLING CODE 4910–13–P
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–6430; Directorate
Identifier 2015–NM–176–AD;]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
Airworthiness Directive (AD) 2005–13–
30, which applies to all Boeing Model
737–100, –200, and –200C series
airplanes. AD 2005–13–30 currently
requires repetitive inspections to detect
discrepancies of certain fuselage skin
panels located just aft of the wheel well,
and repair if necessary. Since we issued
AD 2005–13–30, an evaluation by the
design approval holder (DAH) indicates
that the fuselage skin is subject to
widespread fatigue damage (WFD), and
we have received reports of cracks at the
chem-milled steps in the fuselage skin.
This proposed AD would add new
fuselage skin inspections for cracking,
inspections to detect missing or loose
fasteners and any disbonding or
cracking of bonded doublers, permanent
repairs of time-limited repairs, related
investigative and corrective actions if
necessary, and skin panel replacement.
We are proposing this AD to detect and
correct fatigue cracking of the fuselage
skin panels, which could cause rapid
decompression of the airplane.
DATES: We must receive comments on
this proposed AD by June 27, 2016.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
SUMMARY:
PO 00000
Frm 00034
Fmt 4702
Sfmt 4702
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone
206–544–5000, extension 1; fax 206–
766–5680; Internet https://
www.myboeingfleet.com. You may view
this referenced service information at
the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the
availability of this material at the FAA,
call 425–227–1221. It is also available
on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
6430.
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–2016–
6430; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Wade Sullivan, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton,
WA 98057–3356; phone: 425–917–6430;
fax: 425–917–6590; email:
wade.sullivan@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2016–6430; Directorate Identifier
2015–NM–176–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD because of those
comments.
We will post all comments we
receive, without change, to https://
E:\FR\FM\11MYP1.SGM
11MYP1
Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules
mstockstill on DSK3G9T082PROD with PROPOSALS
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
Fatigue damage can occur locally, in
small areas or structural design details,
or globally, in widespread areas.
Multiple-site damage is widespread
damage that occurs in a large structural
element such as a single rivet line of a
lap splice joining two large skin panels.
Widespread damage can also occur in
multiple elements such as adjacent
frames or stringers. Multiple-site
damage and multiple-element damage
cracks are typically too small initially to
be reliably detected with normal
inspection methods. Without
intervention, these cracks will grow,
and eventually compromise the
structural integrity of the airplane. This
condition is known as widespread
fatigue damage. It is associated with
general degradation of large areas of
structure with similar structural details
and stress levels. As an airplane ages,
WFD will likely occur, and will
certainly occur if the airplane is
operated long enough without any
intervention.
The FAA’s WFD final rule (75 FR
69746, November 15, 2010) became
effective on January 14, 2011. The WFD
rule requires certain actions to prevent
structural failure due to WFD
throughout the operational life of
certain existing transport category
airplanes and all of these airplanes that
will be certificated in the future. For
existing and future airplanes subject to
the WFD rule, the rule requires that
DAHs establish a limit of validity (LOV)
of the engineering data that support the
structural maintenance program.
Operators affected by the WFD rule may
not fly an airplane beyond its LOV,
unless an extended LOV is approved.
The WFD rule (75 FR 69746,
November 15, 2010) does not require
identifying and developing maintenance
actions if the DAHs can show that such
actions are not necessary to prevent
WFD before the airplane reaches the
LOV. Many LOVs, however, do depend
on accomplishment of future
maintenance actions. As stated in the
WFD rule, any maintenance actions
necessary to reach the LOV will be
mandated by airworthiness directives
through separate rulemaking actions.
In the context of WFD, this action is
necessary to enable DAHs to propose
LOVs that allow operators the longest
operational lives for their airplanes, and
still ensure that WFD will not occur.
This approach allows for an
VerDate Sep<11>2014
16:58 May 10, 2016
Jkt 238001
implementation strategy that provides
flexibility to DAHs in determining the
timing of service information
development (with FAA approval),
while providing operators with certainty
regarding the LOV applicable to their
airplanes.
On June 24, 2005, we issued AD
2005–13–30, Amendment 39–14167 (70
FR 36829, June 27, 2005) (‘‘AD 2005–
13–30’’), for all Boeing Model 737–100,
–200, and –200C series airplanes. AD
2005–13–30 requires repetitive
inspections to detect discrepancies of
certain fuselage skin panels located just
aft of the wheel well, and repair if
necessary. AD 2005–13–30 resulted
from reports of fatigue cracking of the
skins and doublers located aft of the
wing, between body station (BS) 727
and BS 1016, and between body
stringers S–14 and S–25 on numerous
Boeing Model 737–100, –200, and
–200C series airplanes. On some
airplanes, reinforcing angles had been
installed on the skin doublers; however,
cracking was detected on both modified
and unmodified airplanes. The cracking
has been attributed to fatigue from a
combination of shear stresses due to
repeated wrinkling of the skin, and the
skin chem-milled pockets configuration.
We issued AD 2005–13–30 to detect and
correct fatigue cracking of the fuselage
skin panels, which could cause rapid
decompression of the airplane.
Actions Since AD 2005–13–30 Was
Issued
Since we issued AD 2005–13–30, an
evaluation by the DAH indicates that
the fuselage skin is subject to WFD, and
we have received reports of cracks at the
chem-milled steps in the fuselage skin.
Related Service Information Under 1
CFR Part 51
We reviewed Boeing Special
Attention Service Bulletin 737–53–
1065, Revision 3, dated June 30, 2015.
The service information describes
procedures for inspection and repair of
the fuselage skin panels between BS 727
and BS 1016, and between stringers S–
14 and S–25; and also describes
procedures for skin panel replacement.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
FAA’s Determination
We are proposing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other products of the same
type design.
PO 00000
Frm 00035
Fmt 4702
Sfmt 4702
29203
Proposed AD Requirements
Although this proposed AD does not
explicitly restate the requirements of AD
2005–13–30, this proposed AD would
retain certain requirements of AD 2005–
13–30. Those requirements are
referenced in the service information
identified previously, which, in turn, is
referenced in paragraph (h) of this
proposed AD.
This proposed AD would also require
accomplishing the actions specified in
the service information described
previously, except as discussed under
‘‘Differences Between this Proposed AD
and the Service Information.’’ For
airplanes having line numbers 1 through
291, this proposed AD would require
actions done in accordance with a
method approved by the Manager,
Seattle ACO, FAA.
The phrase ‘‘related investigative
actions’’ is used in this proposed AD.
‘‘Related investigative actions’’ are
follow-on actions that (1) are related to
the primary actions, and (2) further
investigate the nature of any condition
found. Related investigative actions in
an AD could include, for example,
inspections.
The phrase ‘‘corrective actions’’ is
used in this proposed AD. ‘‘Corrective
actions’’ are actions that correct or
address any condition found. Corrective
actions in an AD could include, for
example, repairs.
Differences Between This Proposed AD
and the Service Information
Boeing Special Attention Service
Bulletin 737–53–1065, Revision 3, dated
June 30, 2015, specifies to contact the
manufacturer for instructions on how to
repair certain conditions and also to
obtain certain work instructions, but
this proposed AD would require
repairing those conditions and also to
obtain those work instructions in one of
the following ways:
• In accordance with a method that
we approve; or
• Using data that meet the
certification basis of the airplane, and
that have been approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) whom
we have authorized to make those
findings.
Explanation of Compliance Time
The compliance time for the
replacement specified in this proposed
AD for addressing WFD was established
to ensure that discrepant structure is
replaced before WFD develops in
airplanes. Standard inspection
techniques cannot be relied on to detect
WFD before it becomes a hazard to
E:\FR\FM\11MYP1.SGM
11MYP1
29204
Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules
flight. We will not grant any extensions
of the compliance time to complete any
AD-mandated service bulletin related to
WFD without extensive new data that
would substantiate and clearly warrant
such an extension.
Costs of Compliance
We estimate that this proposed AD
affects 9 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Labor cost
Parts
cost
Cost per product
Up to 88 work-hours × $85 per
hour = $7,480 per inspection
cycle.
Up to 1,914 work-hours × $85
per hour = $162,690 per inspection cycle.
688 work-hours × $85 per hour
= $58,480.
$0 ..........
Up to $7,480 per inspection
cycle.
Up to $67,320 per inspection
cycle.
$0 ..........
Up to $162,690 per inspection
cycle.
Up to $1,464,210 per inspection cycle.
$96,000
$154,480 ..................................
$1,390,320.
Action
Inspection [actions retained
from AD 2005–13–30].
Inspection [new proposed action].
Skin panel replacement [new
proposed action].
We estimate the following costs to do
any necessary repairs that would be
required based on the results of the
proposed inspection. We have no way of
Cost on U.S.
operators
determining the number of aircraft that
might need these repairs:
ON-CONDITION COSTS
Action
Labor cost
Time-limited repair ........................................................
Permanent repair ..........................................................
Permanent repair inspection ........................................
24 work-hours × $85 per hour = $2,040 ......................
43 work-hours × $85 per hour = $3,655 ......................
7 work-hours × $85 per hour = $595 ...........................
Cost per
product
Parts cost
( 1)
(1)
(1)
1 $2,040
1 $3,655
1 $595
1 We have received no definitive data that would enable us to provide parts cost estimates for the on-condition actions specified in this proposed AD.
According to the manufacturer, some
of the costs of this proposed AD may be
covered under warranty, thereby
reducing the cost impact on affected
individuals. We do not control warranty
coverage for affected individuals. As a
result, we have included all available
costs in our cost estimate.
mstockstill on DSK3G9T082PROD with PROPOSALS
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.
VerDate Sep<11>2014
16:58 May 10, 2016
Jkt 238001
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. This proposed AD would not
have a substantial direct effect on the
States, on the relationship between the
national Government and the States, or
on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the proposed regulation:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
the DOT Regulatory Policies and
Procedures (44 FR 11034, February 26,
1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
PO 00000
Frm 00036
Fmt 4702
Sfmt 4702
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
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
removing Airworthiness Directive (AD)
2005–13–30, Amendment 39–14167 (70
FR 36829, June 27, 2005), and adding
the following new AD:
■
The Boeing Company: Docket No. FAA–
2016–6430; Directorate Identifier 2015–
NM–176–AD.
(a) Comments Due Date
The FAA must receive comments on this
AD action by June 27, 2016.
(b) Affected ADs
This AD replaces AD 2005–13–30,
Amendment 39–14167 (70 FR 36829, June
27, 2005) (‘‘AD 2005–13–30’’).
(c) Applicability
This AD applies to all The Boeing
Company Model 737–100, –200, and –200C
series airplanes, certificated in any category.
E:\FR\FM\11MYP1.SGM
11MYP1
Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by an evaluation by
the design approval holder (DAH) indicating
that the fuselage skin is subject to
widespread fatigue damage (WFD), and
reports of cracks at the chem-milled steps in
the fuselage skin. We are issuing this AD to
detect and correct fatigue cracking of the
fuselage skin panels, which could cause
rapid decompression of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Actions for Group 1 Airplanes
For Group 1 airplanes identified in Boeing
Special Attention Service Bulletin 737–53–
1065, Revision 3, dated June 30, 2015: Within
120 days after the effective date of this AD,
accomplish actions to correct the unsafe
condition (e.g., inspections, repairs,
modifications, and related investigative and
corrective actions) using a method approved
in accordance with the procedures specified
in paragraph (o) of this AD.
mstockstill on DSK3G9T082PROD with PROPOSALS
(h) Inspections, Related Investigative and
Corrective Actions
Except for Group 1 airplanes identified in
Boeing Special Attention Service Bulletin
737–53–1065, Revision 3, dated June 30,
2015: At the applicable times specified in
tables 1 and 2 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Special Attention
Service Bulletin 737–53–1065, Revision 3,
dated June 30, 2015, except as required by
paragraphs (i)(1) and (i)(2) of this AD: Do the
applicable inspections to detect cracks in the
fuselage skin panels; and do all applicable
related investigative and corrective actions;
in accordance with the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 737–53–1065, Revision 3,
dated June 30, 2015, except as required by
paragraphs (i)(3) and (i)(4) of this AD. Do all
applicable related investigative and
corrective actions before further flight.
Repeat the applicable inspections thereafter
at the applicable intervals specified Boeing
Special Attention Service Bulletin 737–53–
1065, Revision 3, dated June 30, 2015.
Accomplishment of a repair in accordance
with ‘‘Part 3: Repair’’ of the Accomplishment
Instructions of Boeing Special Attention
Service Bulletin 737–53–1065, Revision 3,
dated June 30, 2015, except as required by
paragraph (i)(3) of this AD, is terminating
action for the repetitive inspections required
by this paragraph at the repaired locations
only.
(i) Exceptions to Boeing Special Attention
Service Bulletin 737–53–1065, Revision 3,
Dated June 30, 2015
(1) Where Boeing Special Attention Service
Bulletin 737–53–1065, Revision 3, dated June
30, 2015, specifies compliance times ‘‘after
the Revision 3 date of this service bulletin,’’
this AD requires compliance within the
specified compliance times after the effective
date of this AD.
VerDate Sep<11>2014
16:58 May 10, 2016
Jkt 238001
(2) The Condition column of paragraph
1.E., ‘‘Compliance,’’ of Boeing Special
Attention Service Bulletin 737–53–1065,
Revision 3, dated June 30, 2015, refers to
airplanes in certain configurations as of the
‘‘issue date of Revision 3 of this service
bulletin.’’ However, this AD applies to
airplanes in the specified configurations ‘‘as
of the effective date of this AD.’’
(3) Where Boeing Special Attention Service
Bulletin 737–53–1065, Revision 3, dated June
30, 2015, specifies contacting Boeing for
repair instructions or work instructions,
before further flight, repair or perform the
work instructions using a method approved
in accordance with the procedures specified
in paragraph (o) of this AD, except as
required by paragraph (i)(4) of this AD.
(4) For airplanes on which an operator has
a record that a skin panel was replaced with
a production skin panel at or before 59,000
total flight cycles: At the applicable time for
the next inspection as specified in tables 1
and 2 of paragraph 1.E., ‘‘Compliance,’’
Boeing Special Attention Service Bulletin
737–53–1065, Revision 3, dated June 30,
2015, except as provided by paragraphs (i)(1)
and (i)(2) of this AD: Perform inspections and
applicable corrective actions using a method
approved in accordance with the procedures
specified in paragraph (o) of this AD.
(j) Actions for Airplanes With a Time
Limited Repair Installed
Except for Group 1 airplanes identified in
Boeing Special Attention Service Bulletin
737–53–1065, Revision 3, dated June 30,
2015: Do the applicable actions required by
paragraphs (j)(1) and (j)(2) of this AD.
(1) For airplanes with a time limited repair
installed as specified in Boeing Special
Attention Service Bulletin 737–53–1065,
Revision 2, dated April 19, 2001: At the
applicable times specified in table 3 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Special Attention Service Bulletin 737–53–
1065, Revision 3, dated June 30, 2015, except
as provided by paragraphs (i)(1) and (i)(2) of
this AD: Do the actions specified in
paragraphs (j)(1)(i) and (j)(1)(ii) of this AD.
(i) Do the applicable inspections to detect
missing or loose fasteners and any
disbonding or cracking of bonded doublers;
and do all applicable related investigative
and corrective actions; in accordance with
the Accomplishment Instructions of Boeing
Special Attention Service Bulletin 737–53–
1065, Revision 3, dated June 30, 2015, except
as required by paragraph (i)(3) of this AD. Do
all applicable related investigative and
corrective actions before further flight.
Repeat the applicable inspections thereafter
at the applicable intervals specified Boeing
Special Attention Service Bulletin 737–53–
1065, Revision 3, dated June 30, 2015.
(ii) Make the time limited repair
permanent; and do all applicable related
investigative and corrective actions; in
accordance the Accomplishment Instructions
of Boeing Special Attention Service Bulletin
737–53–1065, Revision 3, dated June 30,
2015, except as required by paragraph (i)(3)
of this AD. Do all applicable related
investigative and corrective actions before
further flight. Accomplishing the permanent
repair required by this paragraph terminates
PO 00000
Frm 00037
Fmt 4702
Sfmt 4702
29205
the inspections required by paragraph (j)(1)(i)
of this AD for the permanently repaired area
only.
(2) For airplanes with a time limited repair
installed as specified in Boeing Special
Attention Service Bulletin 737–53–1065,
Revision 3, dated June 30, 2015: At the
applicable times specified in table 4 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Special Attention Service Bulletin 737–53–
1065, Revision 3, dated June 30, 2015: Do the
actions specified in paragraphs (j)(2)(i) and
(j)(2)(ii) of this AD.
(i) Do the applicable inspections to detect
missing or loose fasteners and any
disbonding or cracking of bonded doublers;
and do all applicable related investigative
and corrective actions; in accordance with
the Accomplishment Instructions of Boeing
Special Attention Service Bulletin 737–53–
1065, Revision 3, dated June 30, 2015, except
as required by paragraph (i)(3) of this AD. Do
all applicable related investigative and
corrective actions before further flight.
Repeat the applicable inspections thereafter
at the applicable intervals specified Boeing
Special Attention Service Bulletin 737–53–
1065, Revision 3, dated June 30, 2015.
(ii) Make the time limited repair
permanent; and do all applicable related
investigative and corrective actions; in
accordance the Accomplishment Instructions
of Boeing Special Attention Service Bulletin
737–53–1065, Revision 3, dated June 30,
2015, except as required by paragraph (i)(3)
of this AD. Do all applicable related
investigative and corrective actions before
further flight. Accomplishing the permanent
repair required by this paragraph terminates
the inspections required by paragraph (j)(2)(i)
of this AD for the permanently repaired area
only.
(k) Modification of Certain Permanent
Repairs
Except for Group 1 airplanes identified in
Boeing Special Attention Service Bulletin
737–53–1065, Revision 3, dated June 30,
2015: For airplanes with an existing time
limited repair that was made permanent as
specified in Boeing Special Attention Service
Bulletin 737–53–1065, Revision 2, dated
April 19, 2001: At the applicable times
specified in table 5 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Special Attention
Service Bulletin 737–53–1065, Revision 3,
dated June 30, 2015, except as required by
paragraph (i)(1) of this AD: Modify the
existing permanent repair; and do all
applicable related investigative and
corrective actions; in accordance the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 737–53–
1065, Revision 3, dated June 30, 2015, except
as required by paragraph (i)(3) of this AD. Do
all applicable related investigative and
corrective actions before further flight.
(l) Certain Post-Repair Inspections
For airplanes with a permanent repair
installed as specified in Boeing Special
Attention Service Bulletin 737–53–1065,
Revision 3, dated June 30, 2015: At the
applicable time specified in table 6 of
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Special Attention Service Bulletin 737–53–
E:\FR\FM\11MYP1.SGM
11MYP1
29206
Federal Register / Vol. 81, No. 91 / Wednesday, May 11, 2016 / Proposed Rules
1065, Revision 3, dated June 30, 2015: Do an
external low frequency eddy current (LFEC)
inspection for cracking of the skin at the
critical fastener row of the repair doubler;
and do all applicable corrective actions; in
accordance the Accomplishment Instructions
of Boeing Special Attention Service Bulletin
737–53–1065, Revision 3, dated June 30,
2015, except as required by paragraph (i)(3)
of this AD. Do all applicable corrective
actions before further flight. Repeat the LFEC
inspection thereafter at the applicable
intervals specified in Boeing Special
Attention Service Bulletin 737–53–1065,
Revision 3, dated June 30, 2015.
(m) Skin Panel Replacement
Except for Group 1 airplanes identified in
Boeing Special Attention Service Bulletin
737–53–1065, Revision 3, dated June 30,
2015: At the later of the times specified in
paragraphs (m)(1) and (m)(2) of this AD:
Replace the applicable skin panels, and do
all applicable related investigative and
corrective actions, in accordance with the
Accomplishment Instructions of Boeing
Special Attention Service Bulletin 737–53–
1065, Revision 3, dated June 30, 2015. Do all
applicable related investigative and
corrective actions before further flight. Doing
the skin panel replacement required by this
paragraph terminates the inspection
requirements of paragraph (h) of this AD for
that skin panel only, provided the skin panel
was replaced with a production skin panel
after 59,000 total flight cycles.
(1) Before 60,000 total flight cycles, but not
at or before 59,000 total flight cycles.
(2) Within 6,000 flight cycles after the
effective date of this AD, but not at or before
59,000 total flight cycles.
mstockstill on DSK3G9T082PROD with PROPOSALS
(n) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraph (h) of this AD,
if those actions were performed before the
effective date of this AD using Boeing Special
Attention Service Bulletin 737–53–1065,
Revision 2, dated April 19, 2001, which was
incorporated by reference in AD 2005–13–30.
(o) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the ACO, send it to the
attention of the person identified in
paragraph (p)(1) of this AD. Information may
be emailed to: 9–ANM-Seattle-ACO–AMOCRequests@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
VerDate Sep<11>2014
16:58 May 10, 2016
Jkt 238001
been authorized by the Manager, Seattle
ACO, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) AMOCs approved previously for AD
2005–13–30, are approved as AMOCs for the
corresponding provisions of paragraph (h) of
this AD.
(p) Related Information
(1) For more information about this AD,
contact Wade Sullivan, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
ACO, 1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6430; fax: 425–
917–6590; email: wade.sullivan@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P. O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone 206–
544–5000, extension 1; fax 206–766–5680;
Internet https://www.myboeingfleet.com. You
may view this referenced service information
at the FAA, 1601 Lind Avenue SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221.
Issued in Renton, Washington, on May 4,
2016.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–11095 Filed 5–10–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–6428; Directorate
Identifier 2015–NM–119–AD]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
The Boeing Company Model 787–8
airplanes. This proposed AD was
prompted by reports indicating that
certain wing side-of-body stringer
fittings have been installed with faying
surface mismatch beyond the allowed
machining tolerance. This proposed AD
would require inspection of certain
stringer fittings for faying surface
mismatch common to the side-of-body
rib chord, replacement if necessary, and
replacement of the clearance fit
fasteners common to the side-of-body
SUMMARY:
PO 00000
Frm 00038
Fmt 4702
Sfmt 4702
fittings and upper side-of-body rib
chord with tapered sleeve bolts. We are
proposing this AD to prevent an
unacceptable reduction of the fatigue
life in the upper side-of-body rib chord.
Associated fatigue cracks can reduce the
structural capability to a point where it
cannot sustain limit load, which could
adversely affect the structural integrity
of the airplane.
DATES: We must receive comments on
this proposed AD by June 27, 2016.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this NPRM, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone
206–544–5000, extension 1; fax 206–
766–5680; Internet https://
www.myboeingfleet.com. You may view
this referenced service information at
the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the
availability of this material at the FAA,
call 425–227–1221. It is also available
on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
6428.
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–2016–
6428; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Allen Rauschendorfer, Aerospace
Engineer, Airframe Branch, ANM–120S,
E:\FR\FM\11MYP1.SGM
11MYP1
]]>Agencies
[Federal Register Volume 81, Number 91 (Wednesday, May 11, 2016)]
[Proposed Rules]
[Pages 29202-29206]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-11095]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-6430; Directorate Identifier 2015-NM-176-AD;]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede Airworthiness Directive (AD) 2005-13-
30, which applies to all Boeing Model 737-100, -200, and -200C series
airplanes. AD 2005-13-30 currently requires repetitive inspections to
detect discrepancies of certain fuselage skin panels located just aft
of the wheel well, and repair if necessary. Since we issued AD 2005-13-
30, an evaluation by the design approval holder (DAH) indicates that
the fuselage skin is subject to widespread fatigue damage (WFD), and we
have received reports of cracks at the chem-milled steps in the
fuselage skin. This proposed AD would add new fuselage skin inspections
for cracking, inspections to detect missing or loose fasteners and any
disbonding or cracking of bonded doublers, permanent repairs of time-
limited repairs, related investigative and corrective actions if
necessary, and skin panel replacement. We are proposing this AD to
detect and correct fatigue cracking of the fuselage skin panels, which
could cause rapid decompression of the airplane.
DATES: We must receive comments on this proposed AD by June 27, 2016.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact Boeing
Commercial Airplanes, Attention: Data & Services Management, P.O. Box
3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000,
extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com.
You may view this referenced service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information
on the availability of this material at the FAA, call 425-227-1221. It
is also available on the Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA-2016-6430.
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-2016-
6430; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will
be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Wade Sullivan, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office
(ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-
6430; fax: 425-917-6590; email: wade.sullivan@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-6430;
Directorate Identifier 2015-NM-176-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to https://
[[Page 29203]]
www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
Fatigue damage can occur locally, in small areas or structural
design details, or globally, in widespread areas. Multiple-site damage
is widespread damage that occurs in a large structural element such as
a single rivet line of a lap splice joining two large skin panels.
Widespread damage can also occur in multiple elements such as adjacent
frames or stringers. Multiple-site damage and multiple-element damage
cracks are typically too small initially to be reliably detected with
normal inspection methods. Without intervention, these cracks will
grow, and eventually compromise the structural integrity of the
airplane. This condition is known as widespread fatigue damage. It is
associated with general degradation of large areas of structure with
similar structural details and stress levels. As an airplane ages, WFD
will likely occur, and will certainly occur if the airplane is operated
long enough without any intervention.
The FAA's WFD final rule (75 FR 69746, November 15, 2010) became
effective on January 14, 2011. The WFD rule requires certain actions to
prevent structural failure due to WFD throughout the operational life
of certain existing transport category airplanes and all of these
airplanes that will be certificated in the future. For existing and
future airplanes subject to the WFD rule, the rule requires that DAHs
establish a limit of validity (LOV) of the engineering data that
support the structural maintenance program. Operators affected by the
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV
is approved.
The WFD rule (75 FR 69746, November 15, 2010) does not require
identifying and developing maintenance actions if the DAHs can show
that such actions are not necessary to prevent WFD before the airplane
reaches the LOV. Many LOVs, however, do depend on accomplishment of
future maintenance actions. As stated in the WFD rule, any maintenance
actions necessary to reach the LOV will be mandated by airworthiness
directives through separate rulemaking actions.
In the context of WFD, this action is necessary to enable DAHs to
propose LOVs that allow operators the longest operational lives for
their airplanes, and still ensure that WFD will not occur. This
approach allows for an implementation strategy that provides
flexibility to DAHs in determining the timing of service information
development (with FAA approval), while providing operators with
certainty regarding the LOV applicable to their airplanes.
On June 24, 2005, we issued AD 2005-13-30, Amendment 39-14167 (70
FR 36829, June 27, 2005) (``AD 2005-13-30''), for all Boeing Model 737-
100, -200, and -200C series airplanes. AD 2005-13-30 requires
repetitive inspections to detect discrepancies of certain fuselage skin
panels located just aft of the wheel well, and repair if necessary. AD
2005-13-30 resulted from reports of fatigue cracking of the skins and
doublers located aft of the wing, between body station (BS) 727 and BS
1016, and between body stringers S-14 and S-25 on numerous Boeing Model
737-100, -200, and -200C series airplanes. On some airplanes,
reinforcing angles had been installed on the skin doublers; however,
cracking was detected on both modified and unmodified airplanes. The
cracking has been attributed to fatigue from a combination of shear
stresses due to repeated wrinkling of the skin, and the skin chem-
milled pockets configuration. We issued AD 2005-13-30 to detect and
correct fatigue cracking of the fuselage skin panels, which could cause
rapid decompression of the airplane.
Actions Since AD 2005-13-30 Was Issued
Since we issued AD 2005-13-30, an evaluation by the DAH indicates
that the fuselage skin is subject to WFD, and we have received reports
of cracks at the chem-milled steps in the fuselage skin.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Special Attention Service Bulletin 737-53-1065,
Revision 3, dated June 30, 2015. The service information describes
procedures for inspection and repair of the fuselage skin panels
between BS 727 and BS 1016, and between stringers S-14 and S-25; and
also describes procedures for skin panel replacement. This service
information is reasonably available because the interested parties have
access to it through their normal course of business or by the means
identified in the ADDRESSES section.
FAA's Determination
We are proposing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other products of the same type design.
Proposed AD Requirements
Although this proposed AD does not explicitly restate the
requirements of AD 2005-13-30, this proposed AD would retain certain
requirements of AD 2005-13-30. Those requirements are referenced in the
service information identified previously, which, in turn, is
referenced in paragraph (h) of this proposed AD.
This proposed AD would also require accomplishing the actions
specified in the service information described previously, except as
discussed under ``Differences Between this Proposed AD and the Service
Information.'' For airplanes having line numbers 1 through 291, this
proposed AD would require actions done in accordance with a method
approved by the Manager, Seattle ACO, FAA.
The phrase ``related investigative actions'' is used in this
proposed AD. ``Related investigative actions'' are follow-on actions
that (1) are related to the primary actions, and (2) further
investigate the nature of any condition found. Related investigative
actions in an AD could include, for example, inspections.
The phrase ``corrective actions'' is used in this proposed AD.
``Corrective actions'' are actions that correct or address any
condition found. Corrective actions in an AD could include, for
example, repairs.
Differences Between This Proposed AD and the Service Information
Boeing Special Attention Service Bulletin 737-53-1065, Revision 3,
dated June 30, 2015, specifies to contact the manufacturer for
instructions on how to repair certain conditions and also to obtain
certain work instructions, but this proposed AD would require repairing
those conditions and also to obtain those work instructions in one of
the following ways:
In accordance with a method that we approve; or
Using data that meet the certification basis of the
airplane, and that have been approved by the Boeing Commercial
Airplanes Organization Designation Authorization (ODA) whom we have
authorized to make those findings.
Explanation of Compliance Time
The compliance time for the replacement specified in this proposed
AD for addressing WFD was established to ensure that discrepant
structure is replaced before WFD develops in airplanes. Standard
inspection techniques cannot be relied on to detect WFD before it
becomes a hazard to
[[Page 29204]]
flight. We will not grant any extensions of the compliance time to
complete any AD-mandated service bulletin related to WFD without
extensive new data that would substantiate and clearly warrant such an
extension.
Costs of Compliance
We estimate that this proposed AD affects 9 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection [actions retained Up to 88 work- $0................ Up to $7,480 per Up to $67,320 per
from AD 2005-13-30]. hours x $85 per inspection cycle. inspection cycle.
hour = $7,480 per
inspection cycle.
Inspection [new proposed action] Up to 1,914 work- $0................ Up to $162,690 per Up to $1,464,210
hours x $85 per inspection cycle. per inspection
hour = $162,690 cycle.
per inspection
cycle.
Skin panel replacement [new 688 work-hours x $96,000........... $154,480.......... $1,390,320.
proposed action]. $85 per hour =
$58,480.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs that
would be required based on the results of the proposed inspection. We
have no way of determining the number of aircraft that might need these
repairs:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Time-limited repair........................... 24 work-hours x $85 per hour = (1) \1\ $2,040
$2,040.
Permanent repair.............................. 43 work-hours x $85 per hour = (1) \1\ $3,655
$3,655.
Permanent repair inspection................... 7 work-hours x $85 per hour = (1) \1\ $595
$595.
----------------------------------------------------------------------------------------------------------------
\1\ We have received no definitive data that would enable us to provide parts cost estimates for the on-
condition actions specified in this proposed AD.
According to the manufacturer, some of the costs of this proposed
AD may be covered under warranty, thereby reducing the cost impact on
affected individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all available costs in our
cost estimate.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2005-13-30, Amendment 39-14167 (70 FR 36829, June 27, 2005), and adding
the following new AD:
The Boeing Company: Docket No. FAA-2016-6430; Directorate Identifier
2015-NM-176-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by June 27,
2016.
(b) Affected ADs
This AD replaces AD 2005-13-30, Amendment 39-14167 (70 FR 36829,
June 27, 2005) (``AD 2005-13-30'').
(c) Applicability
This AD applies to all The Boeing Company Model 737-100, -200,
and -200C series airplanes, certificated in any category.
[[Page 29205]]
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by an evaluation by the design approval
holder (DAH) indicating that the fuselage skin is subject to
widespread fatigue damage (WFD), and reports of cracks at the chem-
milled steps in the fuselage skin. We are issuing this AD to detect
and correct fatigue cracking of the fuselage skin panels, which
could cause rapid decompression of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Actions for Group 1 Airplanes
For Group 1 airplanes identified in Boeing Special Attention
Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015:
Within 120 days after the effective date of this AD, accomplish
actions to correct the unsafe condition (e.g., inspections, repairs,
modifications, and related investigative and corrective actions)
using a method approved in accordance with the procedures specified
in paragraph (o) of this AD.
(h) Inspections, Related Investigative and Corrective Actions
Except for Group 1 airplanes identified in Boeing Special
Attention Service Bulletin 737-53-1065, Revision 3, dated June 30,
2015: At the applicable times specified in tables 1 and 2 of
paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service
Bulletin 737-53-1065, Revision 3, dated June 30, 2015, except as
required by paragraphs (i)(1) and (i)(2) of this AD: Do the
applicable inspections to detect cracks in the fuselage skin panels;
and do all applicable related investigative and corrective actions;
in accordance with the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 737-53-1065, Revision 3, dated June 30,
2015, except as required by paragraphs (i)(3) and (i)(4) of this AD.
Do all applicable related investigative and corrective actions
before further flight. Repeat the applicable inspections thereafter
at the applicable intervals specified Boeing Special Attention
Service Bulletin 737-53-1065, Revision 3, dated June 30, 2015.
Accomplishment of a repair in accordance with ``Part 3: Repair'' of
the Accomplishment Instructions of Boeing Special Attention Service
Bulletin 737-53-1065, Revision 3, dated June 30, 2015, except as
required by paragraph (i)(3) of this AD, is terminating action for
the repetitive inspections required by this paragraph at the
repaired locations only.
(i) Exceptions to Boeing Special Attention Service Bulletin 737-53-
1065, Revision 3, Dated June 30, 2015
(1) Where Boeing Special Attention Service Bulletin 737-53-1065,
Revision 3, dated June 30, 2015, specifies compliance times ``after
the Revision 3 date of this service bulletin,'' this AD requires
compliance within the specified compliance times after the effective
date of this AD.
(2) The Condition column of paragraph 1.E., ``Compliance,'' of
Boeing Special Attention Service Bulletin 737-53-1065, Revision 3,
dated June 30, 2015, refers to airplanes in certain configurations
as of the ``issue date of Revision 3 of this service bulletin.''
However, this AD applies to airplanes in the specified
configurations ``as of the effective date of this AD.''
(3) Where Boeing Special Attention Service Bulletin 737-53-1065,
Revision 3, dated June 30, 2015, specifies contacting Boeing for
repair instructions or work instructions, before further flight,
repair or perform the work instructions using a method approved in
accordance with the procedures specified in paragraph (o) of this
AD, except as required by paragraph (i)(4) of this AD.
(4) For airplanes on which an operator has a record that a skin
panel was replaced with a production skin panel at or before 59,000
total flight cycles: At the applicable time for the next inspection
as specified in tables 1 and 2 of paragraph 1.E., ``Compliance,''
Boeing Special Attention Service Bulletin 737-53-1065, Revision 3,
dated June 30, 2015, except as provided by paragraphs (i)(1) and
(i)(2) of this AD: Perform inspections and applicable corrective
actions using a method approved in accordance with the procedures
specified in paragraph (o) of this AD.
(j) Actions for Airplanes With a Time Limited Repair Installed
Except for Group 1 airplanes identified in Boeing Special
Attention Service Bulletin 737-53-1065, Revision 3, dated June 30,
2015: Do the applicable actions required by paragraphs (j)(1) and
(j)(2) of this AD.
(1) For airplanes with a time limited repair installed as
specified in Boeing Special Attention Service Bulletin 737-53-1065,
Revision 2, dated April 19, 2001: At the applicable times specified
in table 3 of paragraph 1.E., ``Compliance,'' of Boeing Special
Attention Service Bulletin 737-53-1065, Revision 3, dated June 30,
2015, except as provided by paragraphs (i)(1) and (i)(2) of this AD:
Do the actions specified in paragraphs (j)(1)(i) and (j)(1)(ii) of
this AD.
(i) Do the applicable inspections to detect missing or loose
fasteners and any disbonding or cracking of bonded doublers; and do
all applicable related investigative and corrective actions; in
accordance with the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 737-53-1065, Revision 3, dated June 30,
2015, except as required by paragraph (i)(3) of this AD. Do all
applicable related investigative and corrective actions before
further flight. Repeat the applicable inspections thereafter at the
applicable intervals specified Boeing Special Attention Service
Bulletin 737-53-1065, Revision 3, dated June 30, 2015.
(ii) Make the time limited repair permanent; and do all
applicable related investigative and corrective actions; in
accordance the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 737-53-1065, Revision 3, dated June 30,
2015, except as required by paragraph (i)(3) of this AD. Do all
applicable related investigative and corrective actions before
further flight. Accomplishing the permanent repair required by this
paragraph terminates the inspections required by paragraph (j)(1)(i)
of this AD for the permanently repaired area only.
(2) For airplanes with a time limited repair installed as
specified in Boeing Special Attention Service Bulletin 737-53-1065,
Revision 3, dated June 30, 2015: At the applicable times specified
in table 4 of paragraph 1.E., ``Compliance,'' of Boeing Special
Attention Service Bulletin 737-53-1065, Revision 3, dated June 30,
2015: Do the actions specified in paragraphs (j)(2)(i) and
(j)(2)(ii) of this AD.
(i) Do the applicable inspections to detect missing or loose
fasteners and any disbonding or cracking of bonded doublers; and do
all applicable related investigative and corrective actions; in
accordance with the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 737-53-1065, Revision 3, dated June 30,
2015, except as required by paragraph (i)(3) of this AD. Do all
applicable related investigative and corrective actions before
further flight. Repeat the applicable inspections thereafter at the
applicable intervals specified Boeing Special Attention Service
Bulletin 737-53-1065, Revision 3, dated June 30, 2015.
(ii) Make the time limited repair permanent; and do all
applicable related investigative and corrective actions; in
accordance the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 737-53-1065, Revision 3, dated June 30,
2015, except as required by paragraph (i)(3) of this AD. Do all
applicable related investigative and corrective actions before
further flight. Accomplishing the permanent repair required by this
paragraph terminates the inspections required by paragraph (j)(2)(i)
of this AD for the permanently repaired area only.
(k) Modification of Certain Permanent Repairs
Except for Group 1 airplanes identified in Boeing Special
Attention Service Bulletin 737-53-1065, Revision 3, dated June 30,
2015: For airplanes with an existing time limited repair that was
made permanent as specified in Boeing Special Attention Service
Bulletin 737-53-1065, Revision 2, dated April 19, 2001: At the
applicable times specified in table 5 of paragraph 1.E.,
``Compliance,'' of Boeing Special Attention Service Bulletin 737-53-
1065, Revision 3, dated June 30, 2015, except as required by
paragraph (i)(1) of this AD: Modify the existing permanent repair;
and do all applicable related investigative and corrective actions;
in accordance the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 737-53-1065, Revision 3, dated June 30,
2015, except as required by paragraph (i)(3) of this AD. Do all
applicable related investigative and corrective actions before
further flight.
(l) Certain Post-Repair Inspections
For airplanes with a permanent repair installed as specified in
Boeing Special Attention Service Bulletin 737-53-1065, Revision 3,
dated June 30, 2015: At the applicable time specified in table 6 of
paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service
Bulletin 737-53-
[[Page 29206]]
1065, Revision 3, dated June 30, 2015: Do an external low frequency
eddy current (LFEC) inspection for cracking of the skin at the
critical fastener row of the repair doubler; and do all applicable
corrective actions; in accordance the Accomplishment Instructions of
Boeing Special Attention Service Bulletin 737-53-1065, Revision 3,
dated June 30, 2015, except as required by paragraph (i)(3) of this
AD. Do all applicable corrective actions before further flight.
Repeat the LFEC inspection thereafter at the applicable intervals
specified in Boeing Special Attention Service Bulletin 737-53-1065,
Revision 3, dated June 30, 2015.
(m) Skin Panel Replacement
Except for Group 1 airplanes identified in Boeing Special
Attention Service Bulletin 737-53-1065, Revision 3, dated June 30,
2015: At the later of the times specified in paragraphs (m)(1) and
(m)(2) of this AD: Replace the applicable skin panels, and do all
applicable related investigative and corrective actions, in
accordance with the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 737-53-1065, Revision 3, dated June 30,
2015. Do all applicable related investigative and corrective actions
before further flight. Doing the skin panel replacement required by
this paragraph terminates the inspection requirements of paragraph
(h) of this AD for that skin panel only, provided the skin panel was
replaced with a production skin panel after 59,000 total flight
cycles.
(1) Before 60,000 total flight cycles, but not at or before
59,000 total flight cycles.
(2) Within 6,000 flight cycles after the effective date of this
AD, but not at or before 59,000 total flight cycles.
(n) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraph (h) of this AD, if those actions were performed before the
effective date of this AD using Boeing Special Attention Service
Bulletin 737-53-1065, Revision 2, dated April 19, 2001, which was
incorporated by reference in AD 2005-13-30.
(o) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle Aircraft Certification Office (ACO),
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the ACO, send it to the
attention of the person identified in paragraph (p)(1) of this AD.
Information may be emailed to: 9-ANM-Seattle-ACO-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, Seattle ACO, to make those findings. To be approved, the
repair method, modification deviation, or alteration deviation must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(4) AMOCs approved previously for AD 2005-13-30, are approved as
AMOCs for the corresponding provisions of paragraph (h) of this AD.
(p) Related Information
(1) For more information about this AD, contact Wade Sullivan,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6430;
fax: 425-917-6590; email: wade.sullivan@faa.gov.
(2) For service information identified in this AD, contact
Boeing Commercial Airplanes, Attention: Data & Services Management,
P. O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service
information at the FAA, 1601 Lind Avenue SW., Renton, Washington.
For information on the availability of this material at the FAA,
call 425-227-1221.
Issued in Renton, Washington, on May 4, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-11095 Filed 5-10-16; 8:45 am]
BILLING CODE 4910-13-P
