[Federal Register Volume 77, Number 216 (Wednesday, November 7, 2012)]
[Proposed Rules]
[Pages 66757-66760]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-27141]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1161; Directorate Identifier 2011-NM-277-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 supersede an existing airworthiness directive
(AD) that applies to certain The Boeing Company Model 737-200, -200C, -
300, -400 and -500 series airplanes. The existing AD currently requires
a one-time mid-frequency eddy current (MFEC) inspection, a low
frequency eddy current (LFEC) inspection, and a detailed inspection for
damage or cracking of stringer S-4L and S-4R lap joints and stringer
clips between body station (BS) 540 and BS 727, and follow-on
inspections and repair if necessary. Since we issued that AD, we have
received reports of cracking of the lap joint lower row. This proposed
AD would instead require repetitive external eddy current inspections
for cracking of certain fuselage crown lap joints and corrective
actions; internal eddy current and detailed inspections for cracking of
certain fuselage crown lap joints, and repair if necessary; and
detailed inspections of certain stringer clips, and replacement with
new stringer clips if necessary. This proposed AD would also add
airplanes to the applicability. We are proposing this AD to detect and
correct cracking of the fuselage lap joints, which could result in
sudden decompression of the airplane.
DATES: We must receive comments on this proposed AD by December 24,
2012.
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 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 review copies of the 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.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; 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: Wayne Lockett, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6447; 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 proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2012-1161;
Directorate Identifier 2011-NM-277-AD'' at the beginning of
[[Page 66758]]
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 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
On April 18, 2003, we issued AD 2003-08-15, Amendment 39-13128 (68
FR 20341, April 25, 2003), for certain The Boeing Company Model 737-
200, -200C, -300, -400 and -500 series airplanes. That AD requires a
one-time MFEC, LFEC, and detailed inspection for damage or cracking of
stringer S-4L and S-4R lap joints and stringer clips between BS 540 and
BS 727, and follow-on inspections and repair if necessary. That AD
resulted from a report indicating that, during a walk-around inspection
on a Model 737-200 series airplane with 60,333 total flight cycles, a
23-inch-long crack was found in the lower row of the stringer S-4L lap
joint between BS 616 and BS 639. Cracking was also found between the
tear straps and in the skin locations common to the tear straps.
Additionally, we received a report of significant cracking on stringer
S-4R of the lap joint between BS 600 and BS 727 on a Model 737-300
series airplane having 52,400 total flight cycles. We issued that AD to
detect and correct cracking of the fuselage lap joints, which could
result in sudden decompression of the airplane.
Actions Since Existing AD 2003-08-15, Amendment 39-13128 (68 FR 20341,
April 25, 2003) Was Issued
Since we issued AD 2003-08-15, Amendment 39-13128 (68 FR 20341,
April 25, 2003), we have received reports of lap joint lower row
cracking on airplanes that were not subject to inspections in AD 2002-
07-08, Amendment 39-12702 (67 FR 17917, April 12, 2002). We are
proposing to supersede AD 2003-08-15 to provide inspections for these
airplanes.
Relevant Service Information
We reviewed Boeing Alert Service Bulletin 737-53A1255, Revision 2,
dated August 7, 2012. For information on the procedures and compliance
times, see this service information at http://www.regulations.gov by
searching for Docket No. FAA-2012-* * *.
Other Relevant Rulemaking
These crown lap joint inspections are currently also contained in
the following service bulletins, which are mandated by AD 2002-07-08,
Amendment 39-12702 (67 FR 17917, April 12, 2002):
Boeing Service Bulletin 737-53A1177, Revision 4, dated
September 2, 1999;
Boeing Service Bulletin 737-53A1177, Revision 5, dated
February 15, 2001; and
Boeing Service Bulletin 737-53A1177, Revision 6, dated May
31, 2001.
Boeing chose to add the needed inspections for the airplanes not
covered by AD 2002-07-08 to the service information included in AD
2003-08-15, Amendment 39-13128 (68 FR 20341, April 25, 2003), due to
the large scope of changes that would be needed to revise Boeing
Service Bulletin 737-53A1177, Revision 6, dated May 31, 2001. We are
considering further rulemaking to remove reference to those crown lap
joint inspections from that AD.
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 retain none of the requirements of AD 2003-
08-15, Amendment 39-13128 (68 FR 20341, April 25, 2003). This proposed
AD would include new inspection requirements, reduce certain inspection
thresholds, and add repetitive inspections. This proposed AD would also
add airplanes to the applicability statement of the existing AD. This
proposed AD would require accomplishing the actions specified in the
service information described previously.
The phrase ``related investigative actions'' might be used in this
proposed AD. ``Related investigative actions'' are follow-on actions
that (1) are related to the primary actions, and (2) are actions that
further investigate the nature of any condition found. Related
investigative actions in an AD could include, for example, inspections.
In addition, the phrase ``corrective actions'' might be 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.
Costs of Compliance
We estimate that this proposed AD affects 307 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated costs
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Cost per Number of Cost on U.S.
Action Labor cost Parts cost product airplanes operators
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Internal inspection........... Up to 303 work- $0 $25,755 307 $7,906,785
hours x $85 per
hour = $25,755.
External inspection........... Up to 10 work- 0 850 307 260,950
hours x $85 per
hour = $850.
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We have received no definitive data that would enable us to provide
a cost estimate for the on-condition actions specified in this proposed
AD.
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
[[Page 66759]]
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 this AD:
(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
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]
2. The FAA amends Sec. 39.13 by removing airworthiness directive
(AD) 2003-08-15, Amendment 39-13128 (68 FR 20341, April 25, 2003), and
adding the following new AD:
The Boeing Company: Docket No. FAA-2012-1161; Directorate Identifier
2011-NM-277-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by December 24,
2012.
(b) Affected ADs
This AD supersedes AD 2003-08-15, Amendment 39-13128 (68 FR
20341, April 25, 2003).
(c) Applicability
This AD applies to The Boeing Company Model 737-200, -200C, -
300, -400, and -500 series airplanes; certificated in any category;
as specified in Boeing Alert Service Bulletin 737-53A1255, Revision
2, dated August 7, 2012.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of cracking of the lap joint
lower row. We are issuing this AD to detect and correct cracking of
the fuselage lap joints, which could result in sudden decompression
of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) External Crown Lap Joint Inspection and Repair
For airplanes on which the lap splice modification specified in
AD 2002-07-08, Amendment 39-12702 (67 FR 17917, April 12, 2002), has
not been accomplished, except as required by paragraph (l)(1) and
(l)(2) of this AD: At the applicable times specified in paragraph
1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-53A1255,
Revision 2, dated August 7, 2012, do an external eddy current
inspection for cracking in the crown lap joints, in accordance with
the Accomplishment Instructions of Boeing Alert Service Bulletin
737-53A1255, Revision 2, dated August 7, 2012. At the intervals
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service
Bulletin 737-53A1255, Revision 2, dated August 7, 2012, repeat the
inspections, in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1255, Revision 2, dated August
7, 2012. If any cracking is found in a lap joint, before further
flight, repair, in accordance with the Accomplishment Instructions
of Boeing Alert Service Bulletin 737-53A1255, Revision 2, dated
August 7, 2012.
(h) Optional Internal Inspections for Mid-Bay Fastener Locations
As an option to confirm cracks found during the inspections
required by paragraph (g) of this AD, do an internal mid-frequency
eddy current (MFEC) inspection for cracking in the lap joint
fastener row between tear straps of the crown lap and do a detailed
inspection of the lap joint lower fastener row for cracking, in
accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1255, Revision 2, dated August 7, 2012.
(i) Internal Crown Lap Joint Inspection and Repair
For airplanes on which the lap splice modification specified in
AD 2002-07-08, Amendment 39-12702 (67 FR 17917, April 12, 2002) has
not been accomplished: At the times specified in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1255,
Revision 2, dated August 7, 2012, except as required by paragraphs
(l)(1) and (l)(2) of this AD, do an internal MFEC, low frequency
eddy current (LFEC), and detailed inspection for cracking in the
crown lap joints and stringer clips, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1255, Revision 2, dated August 7, 2012.
(1) If any cracking is found in any lap joint, before further
flight, repair, in accordance with the Accomplishment Instructions
of Boeing Alert Service Bulletin 737-53A1255, Revision 2, dated
August 7, 2012.
(2) If any cracking is found in any stringer clip, before
further flight, replace the stringer clip with a new stringer clip,
in accordance with the Accomplishment Instructions of Boeing Alert
Service Bulletin 737-53A1255, Revision 2, dated August 7, 2012.
(3) Repeat the inspections at the intervals specified in
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin
737-53A1255, Revision 2, dated August 7, 2012.
(j) Optional Inspections for Tear Strap Locations Only
As an option to confirm cracks found while doing the inspections
required by paragraph (i) of this AD, do an open-hole inspection for
cracking at the tear strap locations, in accordance with the
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1255, Revision 2, dated August 7, 2012.
(k) Terminating Action
(1) Accomplishing a repair of a crown lap joint in accordance
with Boeing Alert Service Bulletin 737-53A1255, Revision 2, dated
August 7, 2012, terminates the inspections required by paragraphs
(g) and (i) of this AD for the repaired area only.
(2) Accomplishing the modification of the crown lap joints in
accordance with any of the service bulletins specified in paragraphs
(k)(2)(i), (k)(2)(ii), and (k)(2)(iii) of this AD terminates the
inspections required by paragraphs (g) and (i) of this AD for the
modified area only.
(i) Boeing Service Bulletin 737-53A1177, Revision 4, dated
September 2, 1999.
(ii) Boeing Service Bulletin 737-53A1177, Revision 5, dated
February 15, 2001.
(iii) Boeing Service Bulletin 737-53A1177, Revision 6, dated May
31, 2001.
(l) Exceptions
(1) Where paragraph 1.E., ``Compliance,'' of Boeing Alert
Service Bulletin 737-53A1255, Revision 2, dated August 7, 2012,
states a compliance time ``from the Revision 1 date of this service
bulletin,'' this AD requires a compliance time ``after the effective
date of this AD.''
(2) Where the ``condition'' column, in paragraph 1.E.,
``Compliance,'' of Boeing Alert Service Bulletin 737-53A1255,
Revision 2, dated August 7, 2012, specifies airplanes with certain
flight cycles ``at the Revision 1 date of this service bulletin,''
for this AD the condition is for airplanes with corresponding flight
cycles ``as of the effective date of this AD.''
(m) Credit for Previous Actions
This paragraph provides credit for the actions required by
paragraphs (g), (h), (i), and (j) of this AD, if those actions were
performed before the effective date of this AD
[[Page 66760]]
using Boeing Alert Service Bulletin 737-53A1255, Revision 1, dated
November 7, 2011, which is 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 the Related Information
section 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 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. For a repair method to be approved, the repair must
meet the certification basis of the airplane, and the approval must
specifically refer to this AD.
(4) AMOCs approved for paragraphs (a), (b), (c), (d), and (e) of
AD 2002-07-08, Amendment 39-12702 (67 FR 17917, April 12, 2002)
before the effective date of this AD, are approved for the
corresponding requirements of paragraphs (g), (i), and (k) of this
AD.
(5) As of the effective date of this AD, any AMOCs approved for
paragraphs (g) and (i) of this AD are approved as AMOCs for the
corresponding requirements of paragraphs (a), (b), (c), (d), and (e)
of AD 2002-07-08, Amendment 39-12702 (67 FR 17917, April 12, 2002).
(o) Related Information
(1) For more information about this AD, contact Wayne Lockett,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356;
phone: 425-917-6447; 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 review copies of the 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.
Issued in Renton, Washington, on October 31, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-27141 Filed 11-6-12; 8:45 am]
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