[Federal Register Volume 81, Number 93 (Friday, May 13, 2016)]
[Proposed Rules]
[Pages 29809-29813]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-11169]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-6666; Directorate Identifier 2015-NM-124-AD]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for
certain Boeing Model 737-400 series airplanes. This proposed AD was
prompted by an evaluation by the design approval holder (DAH) which
indicates that the aft fuselage skin is subject to widespread fatigue
damage (WFD) and reports of aft fuselage skin cracking. This proposed
AD would require repetitive inspections to detect cracking of the aft
fuselage skin, 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 cracking in the aft fuselage skin along the
longitudinal edges of the bonded skin doubler, which could result in
possible rapid decompression and reduced 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 http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this proposed 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, Transport Airplane Directorate, 1601 Lind Avenue SW.,
Renton, WA. For information on the availability of this material at the
FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6666.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
6666; 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: [email protected].
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2016-6666;
Directorate Identifier 2015-NM-124-AD'' at the beginning of your
comments. We specifically invite
[[Page 29810]]
comments on the overall regulatory, economic, environmental, and energy
aspects of this proposed AD. We will consider all comments received by
the closing date and may amend this proposed AD because of those
comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
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.
We have received reports of 29 airplanes with skin panel cracking.
Cracks were found on airplanes with between 22,500 and 44,600 total
airplane cycles. The cracks were found on both the left and the right
hand sides of the airplanes between station 727 and station 947 in the
skin panels between stringer S-20 and S-25. The cracks ranged in
lengths from between 0.25 inches to 5.5 inches.
During certain inspections, additional chem-mill step cracks have
been discovered. On the existing skin panel assemblies, the doubler is
chemically milled to create pockets of various depths. At these skin
panel locations on the airplane, the loads could cause a condition
where skin cracks form along the longitudinal edges of the doubler. If
not corrected, skin cracks could extend to multiple bays and result in
possible rapid decompression and loss of structural integrity of the
airplane.
Other Related Rulemaking
On September 25, 2009, we issued AD 2009-21-01, Amendment 39-16038
(74 FR 52395, October 13, 2009) (``AD 2009-21-01''), for certain Boeing
Model 737-300 and 737-400 series airplanes. AD 2009-21-01 requires
repetitive inspections to detect cracking of the aft fuselage skin, and
related investigative/corrective actions if necessary.
We have determined that, in this case, a less burdensome approach
is to issue separate ADs applicable only to each model type. Therefore,
this proposed AD is applicable to certain Model 737-400 series
airplanes. We are considering issuing additional rulemaking that will
supersede AD 2009-21-01 and apply to Model 737-300 series airplanes.
Although this proposed AD does not supersede AD 2009-21-01, this
proposed AD would retain all of the requirements of AD 2009-21-01 for
Model 737-400 series airplanes, except the skin panel replacement is
terminating action only if the skin panel replacement is done with a
production skin panel after 53,000 total flight cycles. Those
requirements are referenced in Special Attention Service Bulletin 737-
53-1187, Revision 3, dated July 10, 2015, which, in turn, is referenced
in paragraph (g) of this proposed AD.
Related Service Information Under 1 CFR Part 51
We reviewed Boeing Special Attention Service Bulletin 737-53-1187,
Revision 3, dated July 10, 2015. The service information describes
procedures for doing inspections of the fuselage skin, repairs, and
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
This proposed AD would require accomplishing the actions specified
in the service information described previously, except as discussed
under ``Differences Between this Proposed AD and the Service
Information.'' For information on the procedures and compliance times,
see this service information at http://www.regulations.gov by searching
for and locating Docket No. FAA-2016-6666.
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 action, 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 737-53-1187, Revision 3,
dated July 10, 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
[[Page 29811]]
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.
Table 7 of paragraph 1.E., ``Compliance,'' of Boeing Special
Attention Service Bulletin 737-53-1187, Revision 3, dated July 10,
2015, specifies post-repair airworthiness limitation inspections in
compliance with 14 CFR 25.571(a)(3) at the repaired locations, which
support compliance with 14 CFR 121.1109(c)(2) or 129.109(b)(2). As
airworthiness limitations, these inspections are required by
maintenance and operational rules. It is therefore unnecessary to
mandate them in this AD. Deviations from these inspections require FAA
approval, but do not require an alternative method of compliance. This
difference has been coordinated with Boeing.
Explanation of Compliance Time
The compliance time for the modification specified in this proposed
AD for addressing WFD was established to ensure that discrepant
structure is modified before WFD develops in airplanes. Standard
inspection techniques cannot be relied on to detect WFD before it
becomes a hazard to 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 84 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
----------------------------------------------------------------------------------------------------------------
Inspections.................... Up to 1,568 $0 Up to $133,280.... Up to $11,195,520.
work[dash]hours x $85
per hour = Up to
$133,280.
Skin replacement............... 698 work-hours x $85 $185,147 $244,477.......... $20,536,068.
per hour = $59,330.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary repairs that
would be required based on the results of the proposed inspections. We
have no way of determining the number of aircraft that might need these
repairs:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Time limited repair................. 24 work-hours x $85 per hour = \[1]\ $2,040 per repair.
$2,040 per repair.
Permanent repair.................... Up to 39 work[dash]hours x $85 \[1]\ Up to $3,315 per
per hour = $3,315 per repair. repair.
----------------------------------------------------------------------------------------------------------------
\[1]\ We have received no definitive data that would enable us to provide the part cost estimates for the on-
condition actions specified in this proposed AD.
We estimate the following costs to do any necessary post-repair
inspections that would be required. We have no way of determining the
number of aircraft that might need these inspections:
Post-Repair Inspection Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Post-repair inspection.............. Up to 7 work[dash]hours x $85 $0 Up to $595.
per hour = $595.
----------------------------------------------------------------------------------------------------------------
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
[[Page 29812]]
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
The Boeing Company: Docket No. FAA-2016-6666; Directorate Identifier
2015-NM-124-AD.
(a) Comments Due Date
We must receive comments by June 27, 2016.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Boeing Model 737-400 series airplanes,
certificated in any category, as identified in Boeing Special
Attention Service Bulletin 737-53-1187, Revision 3, dated July 10,
2015.
(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) which indicates that the aft fuselage skin is subject
to widespread fatigue damage (WFD) and reports of aft fuselage skin
cracking. We are issuing this AD to detect and correct cracking in
the aft fuselage skin along the longitudinal edges of the bonded
skin doubler, which could result in possible rapid decompression and
reduced structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Inspections, Related Investigative and Corrective Actions
At the applicable times specified in tables 1, 2, and 3 of
paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service
Bulletin 737-53-1187, Revision 3, dated July 10, 2015, except as
provided by paragraph (h)(1) and (h)(2) of this AD: Do the
applicable inspections to detect cracks in the aft fuselage skin
panels; and do all applicable related investigative and corrective
actions; in accordance with the Accomplishment Instructions of
Boeing Special Attention Service Bulletin 737-53-1187, Revision 3,
dated July 10, 2015, except as required by paragraphs (h)(3) and
(h)(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 in
tables 1, 2, and 3 of paragraph 1.E., ``Compliance,'' of Boeing
Special Attention Service Bulletin 737-53-1187, Revision 3, dated
July 10, 2015. Accomplishment of a repair in accordance with ``Part
4: Repair'' of the Accomplishment Instructions of Boeing Special
Attention Service Bulletin 737-53-1187, Revision 3, dated July 10,
2015, except as required by paragraph (h)(3) of this AD, is
terminating action for the repetitive inspections required by this
paragraph at the repaired locations only.
(h) Exceptions to Boeing Special Attention Service Bulletin 737-53-
1187, Revision 3, Dated July 10, 2015
(1) Where Boeing Special Attention Service Bulletin 737-53-1187,
Revision 3, dated July 10, 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 737-53-1187, Revision 3,
dated July 10, 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 737-53-1187,
Revision 3, dated July 10, 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 (n) of this
AD, except as required by paragraph (h)(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 before 53,000 total
flight cycles: At the applicable time for the next inspection as
specified in tables 1, 2, and 3 of paragraph 1.E., ``Compliance,''
of Boeing Special Attention Service Bulletin 737-53-1187, Revision
3, dated July 10, 2015, except as provided by paragraph (h)(1) and
(h)(2) of this AD: Perform inspections and applicable corrective
actions using a method approved in accordance with the procedures
specified in paragraph (n) of this AD.
(i) Actions for Airplanes With a Time Limited Repair Installed
(1) For airplanes with a time limited repair installed as
specified in Boeing Service Bulletin 737-53-1187, Revision 2, dated
May 9, 2007: At the applicable times specified in table 4 of
paragraph 1.E., ``Compliance,'' of Boeing Special Attention Service
Bulletin 737-53-1187, Revision 3, dated July 10, 2015, except as
provided by paragraphs (h)(1) and (h)(2) of this AD: Do the actions
specified in paragraphs (i)(1)(i) and (i)(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 737-53-1187, Revision 3, dated July 10,
2015, except as required by paragraph (h)(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 in table 4 of paragraph 1.E.,
``Compliance,'' of Boeing Special Attention Service Bulletin 737-53-
1187, Revision 3, dated July 10, 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 737-53-1187, Revision 3, dated July 10,
2015, except as required by paragraph (h)(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 (i)(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 737-53-1187,
Revision 3, dated July 10, 2015: At the applicable times specified
in table 5 of paragraph 1.E., ``Compliance,'' of Boeing Special
Attention Service Bulletin 737-53-1187, Revision 3, dated July 10,
2015, except as provided by paragraph (h)(2) of this AD: Do the
actions specified in paragraphs (i)(2)(i) and (i)(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 corrective actions; in accordance with the
Accomplishment Instructions of Boeing Special Attention Service
Bulletin 737-53-1187, Revision 3, dated July 10, 2015, except as
required by paragraph (h)(3) of this AD. Do all applicable
corrective actions before further flight. Repeat the applicable
inspections thereafter at the applicable intervals specified in
table 5 of paragraph 1.E., ``Compliance,'' of Boeing Special
Attention Service Bulletin 737-53-1187, Revision 3, dated July 10,
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 737-53-1187, Revision 3, dated July 10,
2015, except as required by paragraph (h)(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 (i)(2)(i)
of this AD for the permanently repaired area only.
(j) Modification of Certain Permanent Repairs
For airplanes with an existing time limited repair that was made
permanent as specified in Boeing Service Bulletin 737-53-1187,
[[Page 29813]]
Revision 2, dated May 9, 2007: At the applicable time specified in
table 6 of paragraph 1.E., ``Compliance,'' of Boeing Special
Attention Service Bulletin 737-53-1187, Revision 3, dated July 10,
2015, except as provided by paragraph (h)(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 737-53-1187, Revision 3, dated July 10, 2015, except as
required by paragraph (h)(3) of this AD. Do all applicable related
investigative and corrective actions before further flight.
(k) Post-Repair Inspections
Table 7 of paragraph 1.E., ``Compliance,'' of Boeing Special
Attention Service Bulletin 737-53-1187, Revision 3, dated July 10,
2015, specifies post-repair airworthiness limitation inspections in
compliance with 14 CFR 25.571(a)(3) at the repaired locations, which
support compliance with 14 CFR 121.1109(c)(2) or 129.109(b)(2). As
airworthiness limitations, these inspections are required by
maintenance and operational rules. It is therefore unnecessary to
mandate them in this AD. Deviations from these inspections require
FAA approval, but do not require an alternative method of
compliance.
(l) Skin Panel Replacement
At the later of the times specified in paragraphs (l)(1) and
(l)(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 737-53-1187, Revision 3, dated July 10,
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 paragraphs
(g), (i), and (j) of this AD for that skin panel only, provided the
skin panel replacement was done with a production skin panel after
53,000 total flight cycles.
(1) Before 60,000 total flight cycles, but not before 53,000
total flight cycles.
(2) Within 6,000 flight cycles after the effective date of this
AD, but not before 53,000 total flight cycles.
(m) Credit for Previous Actions
(1) This paragraph provides credit for the actions required by
paragraph (g) of this AD, if those actions were performed before the
effective date of this AD using Boeing Service Bulletin 737-53-1187,
Revision 2, dated May 9, 2007, except as required by paragraph
(h)(4) of this AD. Boeing Service Bulletin 737-53-1187, Revision 2,
dated May 9, 2007, was incorporated by reference in AD 2009-21-01,
Amendment 39-16038 (74 FR 52395, October 13, 2009) (``AD 2009-21-
01'').
(2) This paragraph provides credit for the actions required by
paragraph (l) of this AD, if those actions were performed before the
effective date of this AD using Boeing Service Bulletin 737-53-1187,
Revision 2, dated May 9, 2007, except as required by paragraph
(h)(4) of this AD; provided the skin panel replacement was done with
a production skin panel after 53,000 total flight cycles. Boeing
Service Bulletin 737-53-1187, Revision 2, dated May 9, 2007, was
incorporated by reference in AD 2009-21-01.
(3) This paragraph provides credit for the actions required by
paragraph (l) of this AD, if those actions were performed before
November 17, 2009 (the effective date of AD 2009-21-01) using Part
III of the Accomplishment Instructions of Boeing Service Bulletin
737-53-1187, dated November 2, 1995; or Part III of the
Accomplishment Instructions of Boeing Service Bulletin 737-53-1187,
Revision 1, dated January 16, 1997, except as required by paragraph
(h)(4) of this AD; provided the skin panel replacement was done with
a production skin panel after 53,000 total flight cycles. Boeing
Service Bulletin 737-53-1187, dated November 2, 1995; and Boeing
Service Bulletin 737-53-1187, Revision 1, dated January 16, 1997;
are not incorporated by reference in this AD.
(n) 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 (o)(1) of this AD.
Information may be emailed to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(3) An AMOC that provides an acceptable level of safety may be
used for any repair, modification, or alteration required by this AD
if it is approved by the Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, Seattle ACO, to make those findings. To be approved, the
repair method, modification deviation, or alteration deviation must
meet the certification basis of the airplane and the approval must
specifically refer to this AD.
(4) AMOCs approved for repairs for AD 2009-21-01 are approved as
AMOCs for the corresponding provisions of paragraph (g) of this AD.
(5) AMOCs approved for previous modifications done as optional
terminating action for AD 2009-21-01 are approved as AMOCs for the
modification required by paragraph (l) of this AD provided the
previous modification was done after the airplane had accumulated
53,000 total flight cycles or more.
(o) 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: [email protected].
(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, WA. 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. 2016-11169 Filed 5-12-16; 8:45 am]
BILLING CODE 4910-13-P