Airworthiness Directives; the Boeing Company Airplanes, 49978-49982 [2013-19925]
Download as PDF
<![CDATA[
49978
Federal Register / Vol. 78, No. 159 / Friday, August 16, 2013 / Proposed Rules
For reasons set forth above, the DOE’s
actions also violate the principles
outlined in President Obama’s order.
Conclusion
Landmark respectfully requests DOE
immediately halt implementation and
rescind the Rule. In the alternative,
Landmark requests DOE adhere to the
mandates of the APA, and subject the
changes documented in this Petition to
a proper notice and comment.
Respectfully Submitted,
Mark R. Levin, President
Landmark Legal Foundation, 19415 Deerfield
Ave., Suite 312, Leesburg, VA 20176.
JULY 2, 2013
[FR Doc. 2013–19950 Filed 8–15–13; 8:45 am]
BILLING CODE 6450–01–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0694; Directorate
Identifier 2013–NM–097–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) 2002–10–
11, which applies to certain the Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes.
AD 2002–10–11 currently requires
repetitive inspections for cracking and
corrosion of the aft pressure bulkhead,
and corrective actions if necessary; and,
for certain airplanes, enlargement of
frame chord drain holes, and repetitive
inspections of the frame chord drain
path for debris, and corrective actions if
necessary. Since we issued AD 2002–
10–11, we have received three reports of
severe corrosion in the area affected by
that AD. This proposed AD would, for
certain airplanes, reduce the repetitive
inspection interval, and add repetitive
inspections of the frame chord drain
path for obstructions and debris, and
corrective actions if necessary. This
proposed AD would also limit corrosion
and cracking repairs of the aft pressure
bulkhead accomplished after the
effective date of this AD to those
approved by the FAA in a manner
described therein. In reviewing AD
2002–10–11, we noted that the drain
path inspection was not required for
mstockstill on DSK4VPTVN1PROD with PROPOSALS
SUMMARY:
VerDate Mar<15>2010
19:13 Aug 15, 2013
Jkt 229001
certain airplanes, and could be
eliminated for all airplanes if operators
accomplished certain actions required
by AD 2002–10–11. This proposed AD
would add a drain path inspection for
all airplanes. We are proposing this AD
to detect and correct corrosion or
cracking of the aft pressure bulkhead,
which could result in loss of the aft
pressure bulkhead web and stiffeners,
and consequent rapid decompression of
the airplane.
DATES: We must receive comments on
this proposed AD by September 30,
2013.
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 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
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 https://
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:
Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA
98057–3356; phone: 425–917–6450; fax:
PO 00000
Frm 00007
Fmt 4702
Sfmt 4702
425–917–6590; email: alan.pohl@
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–2013–0694; Directorate Identifier
2013–NM–097–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://
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 May 14, 2002, we issued AD
2002–10–11, Amendment 39–12757 (67
FR 36085, May 23, 2002), for certain
Model 737–100, –200, –200C, –300,
–400, and –500 series airplanes. AD
2002–10–11 superseded AD 84–20–03
R1, Amendment 39–5183 (50 FR 51235,
December 16, 1985). AD 2002–10–11
requires repetitive inspections for
cracking and corrosion of the aft
pressure bulkhead, and corrective
actions if necessary; and, for certain
airplanes, enlargement of frame chord
drain holes, repetitive inspections of the
frame chord drain path for obstructions
and debris, and corrective actions if
necessary. We issued AD 2002–10–11 to
detect and correct corrosion or cracking
of the aft pressure bulkhead at body
station (BS) 1016, which could result in
loss of the aft pressure bulkhead web
and stiffeners, and consequent rapid
decompression of the fuselage.
Actions Since AD 2002–10–11,
Amendment 39–12757 (67 FR 36085,
May 23, 2002), Was Issued
Since 2010, we have received three
reports of severe corrosion in the aft
pressure bulkhead. Two of these
airplanes were corroded completely
through the thickness of the pressure
web. The age of the airplanes when
corrosion was found ranged from 12 to
17 years. The total flight hours ranged
from 40,892 to 68,389 hours, and the
total flight cycles ranged from 22,701 to
58,156 flight cycles.
AD 2002–10–11, Amendment 39–
12757 (67 FR 36085, May 23, 2002),
E:\FR\FM\16AUP1.SGM
16AUP1
Federal Register / Vol. 78, No. 159 / Friday, August 16, 2013 / Proposed Rules
requires repetitive inspections for
corrosion at 2-year intervals for
airplanes having line numbers 1 through
1042, and at 4-year intervals for
airplanes having line numbers 1043
through 3132. All reports of severe
corrosion have been from the latter
group of airplanes with the longer
repetitive inspection interval.
In addition, repair procedures in
Boeing Alert Service Bulletin 737–
53A1075, Revision 3, dated June 8,
2000, which is specified in paragraph
(g) of AD 2002–10–11, Amendment 39–
12757 (67 FR 36085, May 23, 2002), as
the appropriate source of service
information, include instructions for
blending out corrosion on the bulkhead
web. The reworked web is more
susceptible to subsequent corrosion.
After consultation with the
manufacturer, we have determined that
reduction of the interval for the
repetitive inspections from 4 years to 2
years, together with removal of repair
instructions for blending out corrosion
on the bulkhead web, will reduce the
frequency and severity of corrosion
findings and provide an acceptable level
of safety.
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 all
requirements of AD 2002–10–11,
Amendment 39–12757 (67 FR 36085,
May 23, 2002). This proposed AD would
reduce the interval for the repetitive
inspections for airplanes having line
numbers (L/N) 1043 through 3132
inclusive from 4 years to 2 years; and
would provide an option to inspect only
the aft side of the aft pressure bulkhead
every 3 months for a maximum of 2
years, at which time both the forward
and aft sides of the aft pressure
bulkhead would require repetitive
inspections at 2-year intervals. This
proposed AD would, for certain
airplanes, add repetitive inspections of
the frame chord drain path for debris,
and corrective actions if necessary.
Changes to AD 2002–10–11,
Amendment 39–12757 (67 FR 36085,
May 23, 2002)
This proposed AD would retain all
the requirements of AD 2002–10–11,
Amendment 39–12757 (67 FR 36085,
May 23, 2002). Since AD 2002–10–11
was issued, the AD format has been
revised, and certain paragraphs have
been rearranged. As a result, the
corresponding paragraph identifiers
have changed in this proposed AD, as
listed in the following table:
REVISED PARAGRAPH IDENTIFIERS
Requirement in AD
2002–10–11, Amendment 39–12757 (67
FR 36085, May 23,
2002)
paragraph
paragraph
paragraph
paragraph
paragraph
paragraph
paragraph
Corresponding
requirement in this
proposed AD
(a)
(b)
(c)
(d)
(e)
(f)
(g)
paragraph
paragraph
paragraph
paragraph
paragraph
paragraph
paragraph
(g)
(h)
(i)
(j)
(k)
(l)
(m)
Note 2 (detailed inspection definition)
in AD 2002–10–11, Amendment 39–
12757 (67 FR 36085, May 23, 2002), has
been removed from this proposed AD
because it is described in Figure 1 of
Boeing Alert Service Bulletin 737–
53A1075, Revision 3, dated June 8,
2000.
Paragraph (e) of AD 2002–10–11,
Amendment 39–12757 (67 FR 36085,
May 23, 2002), which is paragraph (k)
in this proposed AD, has been revised
49979
to clarify that the required actions
include inspecting the drain path in the
chord frame for debris.
The terminating action statement in
paragraph (e)(1) of AD 2002–10–11,
Amendment 39–12757 (67 FR 36085,
May 23, 2002), has been revised to
terminate only the aft bulkhead
inspection for cracking and corrosion in
paragraph (g) of this proposed AD.
Since we issued AD 2002–10–11,
Amendment 39–12757 (67 FR 36085,
May 23, 2002), Boeing Commercial
Airplanes received an Organization
Designation Authorization (ODA). We
have revised this proposed AD to
delegate the authority to approve an
alternative method of compliance for
any repair required by this AD to the
Boeing Commercial Airplanes ODA
rather than a Designated Engineering
Representative.
Differences Between the Proposed AD
and the Service Information
Boeing Alert Service Bulletin 737–
53A1075, Revision 3, dated June 8,
2000, describes instructions on how to
repair certain conditions, but this
proposed AD would require repairing
those conditions 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 ODA whom we
have authorized to make those findings.
This proposed AD would also reduce
the repeat inspection interval for
corrosion and cracking on airplanes
having line numbers 1043 through 3132.
Costs of Compliance
We estimate that this proposed AD
affects 419 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Labor cost
Parts cost
Inspection .......................
mstockstill on DSK4VPTVN1PROD with PROPOSALS
Action
4 work-hours × $85 per hour = $340 per inspection cycle.
$0
The new requirements of this
proposed AD add no additional
economic burden.
Cost per product
$340 per inspection
cycle.
We estimate the following costs to do
any necessary repairs that would be
required based on the results of the
Cost on U.S. operators
$142,460 per inspection
cycle.
proposed inspection. We have no way of
determining the number of aircraft that
might need these repairs:
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Repair .........................................
Up to 136 work-hours × $85 per hour = Up to $11,560 .............
$5,217
VerDate Mar<15>2010
17:50 Aug 15, 2013
Jkt 229001
PO 00000
Frm 00008
Fmt 4702
Sfmt 4702
E:\FR\FM\16AUP1.SGM
16AUP1
Cost per product
Up to $16,777.
49980
Federal Register / Vol. 78, No. 159 / Friday, August 16, 2013 / Proposed Rules
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 proposed
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.
mstockstill on DSK4VPTVN1PROD with PROPOSALS
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.
VerDate Mar<15>2010
17:50 Aug 15, 2013
Jkt 229001
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing airworthiness directive (AD)
2002–10–11, Amendment 39–12757 (67
FR 36085, May 23, 2002), and adding
the following new AD:
■
The Boeing Company: Docket No. FAA–
2013–0694; Directorate Identifier 2013–
NM–097–AD.
(a) Comments Due Date
The FAA must receive comments on this
AD action by September 30, 2013.
(b) Affected ADs
This AD supersedes AD 2002–10–11,
Amendment 39–12757 (67 FR 36085, May 23,
2002).
(c) Applicability
This AD applies to The Boeing Company
Model 737–100, –200, –200C, –300, –400,
and –500 series airplanes, certificated in any
category, line numbers 1 through 3132
inclusive.
(d) Subject
Joint Aircraft System Component (JASC)/
Air Transport Association (ATA) of America
Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by three reports of
severe corrosion in the area affected by AD
2002–10–11, Amendment 39–12757 (67 FR
36085, May 23, 2002). We are issuing this AD
to detect and correct corrosion or cracking of
the aft pressure bulkhead, which could result
in loss of the aft pressure bulkhead web and
stiffeners, and consequent rapid
decompression of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Initial Aft Pressure Bulkhead
Inspection
This paragraph restates the requirements of
paragraph (a) of AD 2002–10–11,
Amendment 39–12757 (67 FR 36085, May 23,
2002), with clarification of the drain path
inspection. For Model 737 series airplanes
having line numbers (L/N) 1 through 929
inclusive, with more than 20,000 hours timein-service or 7 years since date of
manufacture, whichever occurs first: Within
120 days after January 20, 1986 (the effective
date of AD 84–20–03 R1, Amendment 39–
5183 (50 FR 51235, December 16, 1985)),
unless already accomplished within the 21
months before January 20, 1986, visually
inspect the body station (BS) 1016 pressure
bulkhead, including inspecting for cracking
and corrosion of the pressure bulkhead, and
for debris in the drain path in the chord
frame, according to Boeing Alert Service
Bulletin 737–53A1075, Revision 1, dated
September 2, 1983; Revision 2, dated July 13,
1984; or Revision 3, dated June 8, 2000.
Remove any obstruction to the drain hole in
the frame chord and replace any deteriorated
leveling compound as noted in Boeing Alert
Service Bulletin 737–53A1075, Revision 1,
dated September 2, 1983; Revision 2, dated
PO 00000
Frm 00009
Fmt 4702
Sfmt 4702
July 13, 1984; or Revision 3, dated June 8,
2000. Treat the area of inspection with
corrosion inhibitor BMS 3–23, or equivalent.
After the effective date of this AD, use only
Boeing Alert Service Bulletin 737–53A1075,
Revision 3, dated June 8, 2000, to do the
actions required by this paragraph.
(h) Retained Drain Hole Enlargement
This paragraph restates the requirements of
paragraph (b) of AD 2002–10–11,
Amendment 39–12757 (67 FR 36085, May 23,
2002), with revised service bulletin
requirements. For airplanes identified in
paragraph (g) of this AD: Within 1 year after
January 20, 1986 (the effective date of AD 84–
20–03 R1, Amendment 39–5183 (50 FR
51235, December 16, 1985)), accomplish the
drain hole enlargement as shown in Boeing
Alert Service Bulletin 737–53A1075,
Revision 1, dated September 2, 1983;
Revision 2, dated July 13, 1984; or Revision
3, dated June 8, 2000. After the effective date
of this AD, use only Boeing Alert Service
Bulletin 737–53A1075, Revision 3, dated
June 8, 2000, to do the actions required by
this paragraph.
(i) Retained Corrective Action With Revised
Compliance Methods
This paragraph restates the requirements of
paragraph (c) of AD 2002–10–11,
Amendment 39–12757 (67 FR 36085, May 23,
2002), with revised compliance methods. If
cracking or corrosion is found during any
inspection required by paragraph (g) or (j) of
this AD: Before further flight, repair
according to paragraph (i)(1) or (i)(2) of this
AD, as applicable.
(1) If the inspection was done before the
effective date of this AD: Repair according to
Boeing Alert Service Bulletin 737–53A1075,
Revision 1, dated September 2, 1983;
Revision 2, dated July 13, 1984; or Revision
3, dated June 8, 2000.
(2) If the inspection was done on or after
the effective date of this AD: Repair using a
method approved in accordance with the
procedures specified in paragraph (p) of this
AD.
(j) Retained Repetitive Inspections Required
by Paragraph (g) of This AD
This paragraph restates the requirements of
paragraph (d) of AD 2002–10–11,
Amendment 39–12757 (67 FR 36085, May 23,
2002), with revised actions. For airplanes
identified in paragraph (g) of this AD: Repeat
the visual inspections and corrosion inhibitor
treatment specified in paragraph (g) of this
AD at intervals not to exceed 2 years.
Accomplishment of the initial aft pressure
bulkhead inspection required by paragraph
(k) of this AD terminates the inspection
required by this paragraph.
(k) Retained Aft Bulkhead Detailed
Inspection
This paragraph restates the requirements of
paragraph (e) of AD 2002–10–11,
Amendment 39–12757 (67 FR 36085, May 23,
2002), with revised terminating action. Do a
detailed inspection for cracking or corrosion
of the aft pressure bulkhead at BS 1016
(including the forward and aft sides of the
pressure web, forward and aft sides of the
pressure chord, pressure chord radius,
E:\FR\FM\16AUP1.SGM
16AUP1
Federal Register / Vol. 78, No. 159 / Friday, August 16, 2013 / Proposed Rules
forward and aft sides of the angle stiffener,
forward and aft chord, stringer end fitting,
system penetration doublers, channel
stiffeners and fasteners, ‘‘Z’’ stiffeners and
fasteners, and fasteners common to the
pressure chord and pressure web), according
to Boeing Alert Service Bulletin 737–
53A1075, Revision 3, dated June 8, 2000. Do
this inspection at the applicable time shown
in paragraph (k)(1), (k)(2), or (k)(3) of this AD.
(1) For airplanes on which an inspection
has previously been done according to the
requirements of paragraph (g) of this AD: Do
the inspection within 2 years since the most
recent inspection according to paragraph (g)
or (j) of this AD, as applicable. For the
airplanes identified in paragraph (g) of this
AD, accomplishment of the inspection
required by paragraph (k) of this AD
terminates the inspections for cracking and
corrosion required by paragraph (j) of this
AD.
(2) For airplanes having L/Ns 930 through
1042 inclusive, on which an inspection has
not previously been done according to
paragraph (g) of this AD: Do the inspection
within 2 years after June 27, 2002 (the
effective date AD 2002–10–11, Amendment
39–12757 (67 FR 36085, May 23, 2002)).
(3) For airplanes having L/Ns 1043 through
3132 inclusive, on which an inspection has
not previously been done according to
paragraph (g) of this AD: Do the inspection
within 6 years since the airplane’s date of
manufacture, or within 2 years after June 27,
2002 (the effective date AD 2002–10–11,
Amendment 39–12757 (67 FR 36085, May 23,
2002)), whichever occurs later.
mstockstill on DSK4VPTVN1PROD with PROPOSALS
(l) Retained Repetitive Inspections
This paragraph restates the requirements of
paragraph (f) of AD 2002–10–11, Amendment
39–12757 (67 FR 36085, May 23, 2002), with
revised compliance times. Repeat the
inspection in paragraph (k) of this AD at the
applicable time shown in paragraph (l)(1) or
(l)(2) of this AD.
(1) For airplanes having L/Ns 1 through
1042 inclusive: Repeat the inspection
thereafter at intervals not to exceed 2 years.
(2) For airplanes having L/Ns 1043 through
3132 inclusive: Repeat the inspection
thereafter within 2 years since the last
inspection or within 120 days after the
effective date of this AD, whichever occurs
later.
(m) Retained Repair
This paragraph restates the requirements of
paragraph (g) of AD 2002–10–11,
Amendment 39–12757 (67 FR 36085, May 23,
2002), with revised repair requirements. If
any corrosion or cracking is found during any
inspection according to paragraph (k) or (l) of
this AD: Do the applicable action specified in
paragraph (m)(1) or (m)(2) of this AD.
(1) If the inspection was done prior to the
effective date of this AD: Before further flight,
repair according to Boeing Alert Service
Bulletin 737–53A1075, Revision 3, dated
June 8, 2000. Exception: If corrosion or
cracking of the web and stiffeners is outside
the limits specified in Boeing Alert Service
Bulletin 737–53A1075, Revision 3, dated
June 8, 2000, or if corrosion or cracking is
found in any structure not covered by the
VerDate Mar<15>2010
17:50 Aug 15, 2013
Jkt 229001
repair instructions in Boeing Alert Service
Bulletin 737–53A1075, Revision 3, dated
June 8, 2000, before further flight, repair
according to a method approved by the
Manager, Seattle Aircraft Certification Office
(ACO), or per data meeting the type
certification basis of the airplane approved
by the Boeing Commercial Airplanes
Organization Designation Authorization
(ODA) who has been authorized by the
Manager, Seattle ACO, to make such
findings. For a repair method to be approved
by the Manager, Seattle ACO, as required by
this paragraph, the Manager’s approval letter
must specifically reference this AD.
(2) After the effective date of this AD, if
any corrosion or cracking is found during any
inspection required by this AD: Before
further flight, repair the corrosion or cracking
using a method approved in accordance with
the procedures specified in paragraph (p) of
this AD.
(n) New Drain Path Repetitive Inspection
For airplanes having L/N 1 through 3132
inclusive: Within 2 years since the last
inspection in accordance with paragraph (k)
of this AD or within 2 years after the effective
date of this AD, whichever occurs later: Do
a general visual inspection of the drain path
in the chord frame for debris. Remove any
obstruction to the drain hole in the frame
chord and replace any deteriorated leveling
compound. Treat the area of inspection with
corrosion inhibitor BMS 3–23, or equivalent.
Repeat the actions required by this paragraph
at intervals not to exceed 2 years. Do all
actions required by this paragraph in
accordance with the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1075, Revision 3, dated June 8,
2000. For the purposes of this AD, a general
visual inspection is a visual examination of
an interior or exterior area, installation, or
assembly to detect obvious damage, failure,
or irregularity. This level of inspection is
made from within touching distance unless
otherwise specified. A mirror may be
necessary to ensure visual access to all
surfaces in the inspection area. This level of
inspection is made under normally available
lighting conditions such as daylight, hangar
lighting, flashlight, or droplight and may
require removal or opening of access panels
or doors. Stands, ladders, or platforms may
be required to gain proximity to the area
being checked.
(o) New Optional Repetitive Aft Pressure
Bulkhead Inspection for Certain Airplanes
and Corrective Action
For airplanes having L/Ns 1043 through
3132 inclusive: In lieu of performing the
inspection required by paragraph (l) of this
AD, operators may do the actions specified
in this paragraph. Within 2 years from the
most recent aft pressure bulkhead inspection
done as specified in Boeing Alert Service
Bulletin 737–53A1075, Revision 1, dated
September 2, 1983; Revision 2, dated July 13,
1984; or Revision 3, dated June 8, 2000; or
within 120 days after the effective date of this
AD, whichever occurs later, do a detailed
inspection for cracking or corrosion of the aft
side of the aft pressure bulkhead at BS 1016
(including the aft sides of the pressure web,
PO 00000
Frm 00010
Fmt 4702
Sfmt 4702
49981
aft sides of the pressure chord, pressure
chord radius, aft chord, stringer end fitting,
system penetration doublers, and fasteners
common to the pressure chord and pressure
web), in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1075, Revision 3,
dated June 8, 2000. If any corrosion or
cracking is found: Before further flight, repair
the corrosion or cracking using a method
approved in accordance with the procedures
specified in paragraph (p) of this AD. Repeat
the inspection thereafter at intervals not to
exceed 90 days. Within 2 years after the
initial inspection done in accordance with
this paragraph: Do the actions specified in
paragraph (k) of this AD, and repeat
thereafter at intervals not to exceed 2 years.
(p) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle 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 9-ANMSeattle-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
required by this AD if it is approved by the
Boeing Commercial Airplanes 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 previously in
accordance with AD 2002–10–11,
Amendment 39–12757 (67 FR 36085, May 23,
2002), are approved as AMOCs for the
corresponding provisions of this AD.
(q) Related Information
(1) For more information about this AD,
contact Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue SW., Renton, Washington 98057–
3356; phone: (425) 917–6450; fax: (425) 917–
6590; email: alan.pohl@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, Washington 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, Washington.
For information on the availability of this
material at the FAA, call 425–227–1221.
E:\FR\FM\16AUP1.SGM
16AUP1
49982
Federal Register / Vol. 78, No. 159 / Friday, August 16, 2013 / Proposed Rules
Issued in Renton, Washington, on August
9, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–19925 Filed 8–15–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0695; Directorate
Identifier 2011–NM–264–AD]
RIN 2120–AA64
Airworthiness Directives; Saab AB,
Saab Aerosystems Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
• 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.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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:
Gregory Thiele, Aerospace Engineer,
Special Certification Office, ASW–190,
FAA, 2601 Meacham Boulevard, Fort
Worth, TX 76137; phone: (817) 222–
5229; fax: (817) 222–5785; email:
gregory.thiele@faa.gov.
SUPPLEMENTARY INFORMATION:
We propose to adopt a new
airworthiness directive (AD) for certain
Saab AB, Saab Aerosystems Model 340A
(SAAB/SF340A) and SAAB 340B
airplanes modified by Supplemental
Type Certificate SA7971SW. This
proposed AD was prompted by reports
of smoke, a burning odor, and possible
fire in the flight deck and cabin of the
airplane, which was caused by brushes
wearing beyond their limits, in the air
conditioning motor. This proposed AD
would require an inspection to
determine if a certain air compressor
motor is installed, an inspection to
determine the age of a certain
compressor hour meter since new or
overhauled, and repetitive replacement
of the brushes on affected air
conditioning compressor motor units.
As an option to the replacement, this
proposed AD allows pulling the air
conditioning circuit breaker and adding
a placard. We are proposing this AD to
detect and correct worn brushes
contacting the commutator, which could
result in a fire under the cabin floor
with no means to detect or extinguish
the fire.
DATES: We must receive comments on
this proposed AD by September 30,
2013.
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–
2013–0695; Directorate Identifier 2011–
NM–264–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://
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.
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.
Discussion
We received reports of smoke, a
burning odor, and possible fire in the
flight deck and cabin of the airplane,
which was caused by brushes wearing
beyond their limits, in the air
conditioning motor. The rivets in the
SUMMARY:
mstockstill on DSK4VPTVN1PROD with PROPOSALS
ADDRESSES:
VerDate Mar<15>2010
17:50 Aug 15, 2013
Jkt 229001
PO 00000
Frm 00011
Fmt 4702
Sfmt 4702
brush contacted the commutator, which
caused sparks (the ignition source). The
air conditioners (two units) are located
under the floor, forward of the wing
box. There is no fire detection or fire
extinguishing equipment in the
installed location. This condition (worn
brushes contacting the commutator), if
not corrected, could result in a fire
under the cabin floor with no means to
detect or extinguish the fire.
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 these same
type designs.
Proposed AD Requirements
This proposed AD would require an
inspection to determine if a certain air
compressor motor is installed, an
inspection to determine the age of a
certain compressor hour meter since
new or overhauled, and repetitive
replacement of the brushes on affected
air conditioning compressor motor
units. As an option to the replacement,
this proposed AD allows pulling the air
conditioning circuit breaker and adding
a placard. This proposed AD also
requires sending the inspection results
to the FAA.
This proposed AD contains detailed
steps to address the unsafe condition
rather than referring to service
information. However, under the
provisions of paragraph (p) of this
proposed AD, operators may request
approval of an alternative method of
compliance (AMOC), if sufficient data
are submitted to substantiate that the
AMOC would provide an acceptable
level of safety.
Interim Action
We consider this proposed AD
interim action. The inspection reports
that would be required by this proposed
AD will enable us to obtain better
insight into the nature, cause, and
extent of the brush wear, and eventually
to develop final action to address the
unsafe condition. Once final action has
been identified, we might consider
further rulemaking.
Costs of Compliance
We estimate that this proposed AD
affects 23 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
E:\FR\FM\16AUP1.SGM
16AUP1
]]>Agencies
[Federal Register Volume 78, Number 159 (Friday, August 16, 2013)]
[Proposed Rules]
[Pages 49978-49982]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-19925]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0694; Directorate Identifier 2013-NM-097-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) 2002-10-
11, which applies to certain the Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes. AD 2002-10-11 currently
requires repetitive inspections for cracking and corrosion of the aft
pressure bulkhead, and corrective actions if necessary; and, for
certain airplanes, enlargement of frame chord drain holes, and
repetitive inspections of the frame chord drain path for debris, and
corrective actions if necessary. Since we issued AD 2002-10-11, we have
received three reports of severe corrosion in the area affected by that
AD. This proposed AD would, for certain airplanes, reduce the
repetitive inspection interval, and add repetitive inspections of the
frame chord drain path for obstructions and debris, and corrective
actions if necessary. This proposed AD would also limit corrosion and
cracking repairs of the aft pressure bulkhead accomplished after the
effective date of this AD to those approved by the FAA in a manner
described therein. In reviewing AD 2002-10-11, we noted that the drain
path inspection was not required for certain airplanes, and could be
eliminated for all airplanes if operators accomplished certain actions
required by AD 2002-10-11. This proposed AD would add a drain path
inspection for all airplanes. We are proposing this AD to detect and
correct corrosion or cracking of the aft pressure bulkhead, which could
result in loss of the aft pressure bulkhead web and stiffeners, and
consequent rapid decompression of the airplane.
DATES: We must receive comments on this proposed AD by September 30,
2013.
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 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 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 https://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: Alan Pohl, Aerospace Engineer,
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office,
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6450; fax:
425-917-6590; email: alan.pohl@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-2013-0694;
Directorate Identifier 2013-NM-097-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://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 May 14, 2002, we issued AD 2002-10-11, Amendment 39-12757 (67 FR
36085, May 23, 2002), for certain Model 737-100, -200, -200C, -300, -
400, and -500 series airplanes. AD 2002-10-11 superseded AD 84-20-03
R1, Amendment 39-5183 (50 FR 51235, December 16, 1985). AD 2002-10-11
requires repetitive inspections for cracking and corrosion of the aft
pressure bulkhead, and corrective actions if necessary; and, for
certain airplanes, enlargement of frame chord drain holes, repetitive
inspections of the frame chord drain path for obstructions and debris,
and corrective actions if necessary. We issued AD 2002-10-11 to detect
and correct corrosion or cracking of the aft pressure bulkhead at body
station (BS) 1016, which could result in loss of the aft pressure
bulkhead web and stiffeners, and consequent rapid decompression of the
fuselage.
Actions Since AD 2002-10-11, Amendment 39-12757 (67 FR 36085, May 23,
2002), Was Issued
Since 2010, we have received three reports of severe corrosion in
the aft pressure bulkhead. Two of these airplanes were corroded
completely through the thickness of the pressure web. The age of the
airplanes when corrosion was found ranged from 12 to 17 years. The
total flight hours ranged from 40,892 to 68,389 hours, and the total
flight cycles ranged from 22,701 to 58,156 flight cycles.
AD 2002-10-11, Amendment 39-12757 (67 FR 36085, May 23, 2002),
[[Page 49979]]
requires repetitive inspections for corrosion at 2-year intervals for
airplanes having line numbers 1 through 1042, and at 4-year intervals
for airplanes having line numbers 1043 through 3132. All reports of
severe corrosion have been from the latter group of airplanes with the
longer repetitive inspection interval.
In addition, repair procedures in Boeing Alert Service Bulletin
737-53A1075, Revision 3, dated June 8, 2000, which is specified in
paragraph (g) of AD 2002-10-11, Amendment 39-12757 (67 FR 36085, May
23, 2002), as the appropriate source of service information, include
instructions for blending out corrosion on the bulkhead web. The
reworked web is more susceptible to subsequent corrosion.
After consultation with the manufacturer, we have determined that
reduction of the interval for the repetitive inspections from 4 years
to 2 years, together with removal of repair instructions for blending
out corrosion on the bulkhead web, will reduce the frequency and
severity of corrosion findings and provide an acceptable level of
safety.
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 all requirements of AD 2002-10-11,
Amendment 39-12757 (67 FR 36085, May 23, 2002). This proposed AD would
reduce the interval for the repetitive inspections for airplanes having
line numbers (L/N) 1043 through 3132 inclusive from 4 years to 2 years;
and would provide an option to inspect only the aft side of the aft
pressure bulkhead every 3 months for a maximum of 2 years, at which
time both the forward and aft sides of the aft pressure bulkhead would
require repetitive inspections at 2-year intervals. This proposed AD
would, for certain airplanes, add repetitive inspections of the frame
chord drain path for debris, and corrective actions if necessary.
Changes to AD 2002-10-11, Amendment 39-12757 (67 FR 36085, May 23,
2002)
This proposed AD would retain all the requirements of AD 2002-10-
11, Amendment 39-12757 (67 FR 36085, May 23, 2002). Since AD 2002-10-11
was issued, the AD format has been revised, and certain paragraphs have
been rearranged. As a result, the corresponding paragraph identifiers
have changed in this proposed AD, as listed in the following table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Requirement in AD 2002-10-11,
Amendment 39-12757 (67 FR 36085, Corresponding requirement in this
May 23, 2002) proposed AD
------------------------------------------------------------------------
paragraph (a) paragraph (g)
paragraph (b) paragraph (h)
paragraph (c) paragraph (i)
paragraph (d) paragraph (j)
paragraph (e) paragraph (k)
paragraph (f) paragraph (l)
paragraph (g) paragraph (m)
------------------------------------------------------------------------
Note 2 (detailed inspection definition) in AD 2002-10-11, Amendment
39-12757 (67 FR 36085, May 23, 2002), has been removed from this
proposed AD because it is described in Figure 1 of Boeing Alert Service
Bulletin 737-53A1075, Revision 3, dated June 8, 2000.
Paragraph (e) of AD 2002-10-11, Amendment 39-12757 (67 FR 36085,
May 23, 2002), which is paragraph (k) in this proposed AD, has been
revised to clarify that the required actions include inspecting the
drain path in the chord frame for debris.
The terminating action statement in paragraph (e)(1) of AD 2002-10-
11, Amendment 39-12757 (67 FR 36085, May 23, 2002), has been revised to
terminate only the aft bulkhead inspection for cracking and corrosion
in paragraph (g) of this proposed AD.
Since we issued AD 2002-10-11, Amendment 39-12757 (67 FR 36085, May
23, 2002), Boeing Commercial Airplanes received an Organization
Designation Authorization (ODA). We have revised this proposed AD to
delegate the authority to approve an alternative method of compliance
for any repair required by this AD to the Boeing Commercial Airplanes
ODA rather than a Designated Engineering Representative.
Differences Between the Proposed AD and the Service Information
Boeing Alert Service Bulletin 737-53A1075, Revision 3, dated June
8, 2000, describes instructions on how to repair certain conditions,
but this proposed AD would require repairing those conditions 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 ODA whom we have authorized to make those findings.
This proposed AD would also reduce the repeat inspection interval
for corrosion and cracking on airplanes having line numbers 1043
through 3132.
Costs of Compliance
We estimate that this proposed AD affects 419 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...................... 4 work-hours x $85 per $0 $340 per inspection $142,460 per
hour = $340 per cycle. inspection cycle.
inspection cycle.
----------------------------------------------------------------------------------------------------------------
The new requirements of this proposed AD add no additional economic
burden.
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
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Repair................................. Up to 136 work-hours x $85 per $5,217 Up to $16,777.
hour = Up to $11,560.
----------------------------------------------------------------------------------------------------------------
[[Page 49980]]
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 proposed 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)
2002-10-11, Amendment 39-12757 (67 FR 36085, May 23, 2002), and adding
the following new AD:
The Boeing Company: Docket No. FAA-2013-0694; Directorate Identifier
2013-NM-097-AD.
(a) Comments Due Date
The FAA must receive comments on this AD action by September 30,
2013.
(b) Affected ADs
This AD supersedes AD 2002-10-11, Amendment 39-12757 (67 FR
36085, May 23, 2002).
(c) Applicability
This AD applies to The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any
category, line numbers 1 through 3132 inclusive.
(d) Subject
Joint Aircraft System Component (JASC)/Air Transport Association
(ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by three reports of severe corrosion in the
area affected by AD 2002-10-11, Amendment 39-12757 (67 FR 36085, May
23, 2002). We are issuing this AD to detect and correct corrosion or
cracking of the aft pressure bulkhead, which could result in loss of
the aft pressure bulkhead web and stiffeners, and consequent rapid
decompression of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Initial Aft Pressure Bulkhead Inspection
This paragraph restates the requirements of paragraph (a) of AD
2002-10-11, Amendment 39-12757 (67 FR 36085, May 23, 2002), with
clarification of the drain path inspection. For Model 737 series
airplanes having line numbers (L/N) 1 through 929 inclusive, with
more than 20,000 hours time-in-service or 7 years since date of
manufacture, whichever occurs first: Within 120 days after January
20, 1986 (the effective date of AD 84-20-03 R1, Amendment 39-5183
(50 FR 51235, December 16, 1985)), unless already accomplished
within the 21 months before January 20, 1986, visually inspect the
body station (BS) 1016 pressure bulkhead, including inspecting for
cracking and corrosion of the pressure bulkhead, and for debris in
the drain path in the chord frame, according to Boeing Alert Service
Bulletin 737-53A1075, Revision 1, dated September 2, 1983; Revision
2, dated July 13, 1984; or Revision 3, dated June 8, 2000. Remove
any obstruction to the drain hole in the frame chord and replace any
deteriorated leveling compound as noted in Boeing Alert Service
Bulletin 737-53A1075, Revision 1, dated September 2, 1983; Revision
2, dated July 13, 1984; or Revision 3, dated June 8, 2000. Treat the
area of inspection with corrosion inhibitor BMS 3-23, or equivalent.
After the effective date of this AD, use only Boeing Alert Service
Bulletin 737-53A1075, Revision 3, dated June 8, 2000, to do the
actions required by this paragraph.
(h) Retained Drain Hole Enlargement
This paragraph restates the requirements of paragraph (b) of AD
2002-10-11, Amendment 39-12757 (67 FR 36085, May 23, 2002), with
revised service bulletin requirements. For airplanes identified in
paragraph (g) of this AD: Within 1 year after January 20, 1986 (the
effective date of AD 84-20-03 R1, Amendment 39-5183 (50 FR 51235,
December 16, 1985)), accomplish the drain hole enlargement as shown
in Boeing Alert Service Bulletin 737-53A1075, Revision 1, dated
September 2, 1983; Revision 2, dated July 13, 1984; or Revision 3,
dated June 8, 2000. After the effective date of this AD, use only
Boeing Alert Service Bulletin 737-53A1075, Revision 3, dated June 8,
2000, to do the actions required by this paragraph.
(i) Retained Corrective Action With Revised Compliance Methods
This paragraph restates the requirements of paragraph (c) of AD
2002-10-11, Amendment 39-12757 (67 FR 36085, May 23, 2002), with
revised compliance methods. If cracking or corrosion is found during
any inspection required by paragraph (g) or (j) of this AD: Before
further flight, repair according to paragraph (i)(1) or (i)(2) of
this AD, as applicable.
(1) If the inspection was done before the effective date of this
AD: Repair according to Boeing Alert Service Bulletin 737-53A1075,
Revision 1, dated September 2, 1983; Revision 2, dated July 13,
1984; or Revision 3, dated June 8, 2000.
(2) If the inspection was done on or after the effective date of
this AD: Repair using a method approved in accordance with the
procedures specified in paragraph (p) of this AD.
(j) Retained Repetitive Inspections Required by Paragraph (g) of This
AD
This paragraph restates the requirements of paragraph (d) of AD
2002-10-11, Amendment 39-12757 (67 FR 36085, May 23, 2002), with
revised actions. For airplanes identified in paragraph (g) of this
AD: Repeat the visual inspections and corrosion inhibitor treatment
specified in paragraph (g) of this AD at intervals not to exceed 2
years. Accomplishment of the initial aft pressure bulkhead
inspection required by paragraph (k) of this AD terminates the
inspection required by this paragraph.
(k) Retained Aft Bulkhead Detailed Inspection
This paragraph restates the requirements of paragraph (e) of AD
2002-10-11, Amendment 39-12757 (67 FR 36085, May 23, 2002), with
revised terminating action. Do a detailed inspection for cracking or
corrosion of the aft pressure bulkhead at BS 1016 (including the
forward and aft sides of the pressure web, forward and aft sides of
the pressure chord, pressure chord radius,
[[Page 49981]]
forward and aft sides of the angle stiffener, forward and aft chord,
stringer end fitting, system penetration doublers, channel
stiffeners and fasteners, ``Z'' stiffeners and fasteners, and
fasteners common to the pressure chord and pressure web), according
to Boeing Alert Service Bulletin 737-53A1075, Revision 3, dated June
8, 2000. Do this inspection at the applicable time shown in
paragraph (k)(1), (k)(2), or (k)(3) of this AD.
(1) For airplanes on which an inspection has previously been
done according to the requirements of paragraph (g) of this AD: Do
the inspection within 2 years since the most recent inspection
according to paragraph (g) or (j) of this AD, as applicable. For the
airplanes identified in paragraph (g) of this AD, accomplishment of
the inspection required by paragraph (k) of this AD terminates the
inspections for cracking and corrosion required by paragraph (j) of
this AD.
(2) For airplanes having L/Ns 930 through 1042 inclusive, on
which an inspection has not previously been done according to
paragraph (g) of this AD: Do the inspection within 2 years after
June 27, 2002 (the effective date AD 2002-10-11, Amendment 39-12757
(67 FR 36085, May 23, 2002)).
(3) For airplanes having L/Ns 1043 through 3132 inclusive, on
which an inspection has not previously been done according to
paragraph (g) of this AD: Do the inspection within 6 years since the
airplane's date of manufacture, or within 2 years after June 27,
2002 (the effective date AD 2002-10-11, Amendment 39-12757 (67 FR
36085, May 23, 2002)), whichever occurs later.
(l) Retained Repetitive Inspections
This paragraph restates the requirements of paragraph (f) of AD
2002-10-11, Amendment 39-12757 (67 FR 36085, May 23, 2002), with
revised compliance times. Repeat the inspection in paragraph (k) of
this AD at the applicable time shown in paragraph (l)(1) or (l)(2)
of this AD.
(1) For airplanes having L/Ns 1 through 1042 inclusive: Repeat
the inspection thereafter at intervals not to exceed 2 years.
(2) For airplanes having L/Ns 1043 through 3132 inclusive:
Repeat the inspection thereafter within 2 years since the last
inspection or within 120 days after the effective date of this AD,
whichever occurs later.
(m) Retained Repair
This paragraph restates the requirements of paragraph (g) of AD
2002-10-11, Amendment 39-12757 (67 FR 36085, May 23, 2002), with
revised repair requirements. If any corrosion or cracking is found
during any inspection according to paragraph (k) or (l) of this AD:
Do the applicable action specified in paragraph (m)(1) or (m)(2) of
this AD.
(1) If the inspection was done prior to the effective date of
this AD: Before further flight, repair according to Boeing Alert
Service Bulletin 737-53A1075, Revision 3, dated June 8, 2000.
Exception: If corrosion or cracking of the web and stiffeners is
outside the limits specified in Boeing Alert Service Bulletin 737-
53A1075, Revision 3, dated June 8, 2000, or if corrosion or cracking
is found in any structure not covered by the repair instructions in
Boeing Alert Service Bulletin 737-53A1075, Revision 3, dated June 8,
2000, before further flight, repair according to a method approved
by the Manager, Seattle Aircraft Certification Office (ACO), or per
data meeting the type certification basis of the airplane approved
by the Boeing Commercial Airplanes Organization Designation
Authorization (ODA) who has been authorized by the Manager, Seattle
ACO, to make such findings. For a repair method to be approved by
the Manager, Seattle ACO, as required by this paragraph, the
Manager's approval letter must specifically reference this AD.
(2) After the effective date of this AD, if any corrosion or
cracking is found during any inspection required by this AD: Before
further flight, repair the corrosion or cracking using a method
approved in accordance with the procedures specified in paragraph
(p) of this AD.
(n) New Drain Path Repetitive Inspection
For airplanes having L/N 1 through 3132 inclusive: Within 2
years since the last inspection in accordance with paragraph (k) of
this AD or within 2 years after the effective date of this AD,
whichever occurs later: Do a general visual inspection of the drain
path in the chord frame for debris. Remove any obstruction to the
drain hole in the frame chord and replace any deteriorated leveling
compound. Treat the area of inspection with corrosion inhibitor BMS
3-23, or equivalent. Repeat the actions required by this paragraph
at intervals not to exceed 2 years. Do all actions required by this
paragraph in accordance with the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1075, Revision 3, dated June 8,
2000. For the purposes of this AD, a general visual inspection is a
visual examination of an interior or exterior area, installation, or
assembly to detect obvious damage, failure, or irregularity. This
level of inspection is made from within touching distance unless
otherwise specified. A mirror may be necessary to ensure visual
access to all surfaces in the inspection area. This level of
inspection is made under normally available lighting conditions such
as daylight, hangar lighting, flashlight, or droplight and may
require removal or opening of access panels or doors. Stands,
ladders, or platforms may be required to gain proximity to the area
being checked.
(o) New Optional Repetitive Aft Pressure Bulkhead Inspection for
Certain Airplanes and Corrective Action
For airplanes having L/Ns 1043 through 3132 inclusive: In lieu
of performing the inspection required by paragraph (l) of this AD,
operators may do the actions specified in this paragraph. Within 2
years from the most recent aft pressure bulkhead inspection done as
specified in Boeing Alert Service Bulletin 737-53A1075, Revision 1,
dated September 2, 1983; Revision 2, dated July 13, 1984; or
Revision 3, dated June 8, 2000; or within 120 days after the
effective date of this AD, whichever occurs later, do a detailed
inspection for cracking or corrosion of the aft side of the aft
pressure bulkhead at BS 1016 (including the aft sides of the
pressure web, aft sides of the pressure chord, pressure chord
radius, aft chord, stringer end fitting, system penetration
doublers, and fasteners common to the pressure chord and pressure
web), in accordance with the Accomplishment Instructions of Boeing
Alert Service Bulletin 737-53A1075, Revision 3, dated June 8, 2000.
If any corrosion or cracking is found: Before further flight, repair
the corrosion or cracking using a method approved in accordance with
the procedures specified in paragraph (p) of this AD. Repeat the
inspection thereafter at intervals not to exceed 90 days. Within 2
years after the initial inspection done in accordance with this
paragraph: Do the actions specified in paragraph (k) of this AD, and
repeat thereafter at intervals not to exceed 2 years.
(p) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Seattle 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 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 required by this AD if it is approved by the
Boeing Commercial Airplanes 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 previously in accordance with AD 2002-10-11,
Amendment 39-12757 (67 FR 36085, May 23, 2002), are approved as
AMOCs for the corresponding provisions of this AD.
(q) Related Information
(1) For more information about this AD, contact Alan Pohl,
Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft
Certification Office, 1601 Lind Avenue SW., Renton, Washington
98057-3356; phone: (425) 917-6450; fax: (425) 917-6590; email:
alan.pohl@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, Washington 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, Washington. For information on the
availability of this material at the FAA, call 425-227-1221.
[[Page 49982]]
Issued in Renton, Washington, on August 9, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-19925 Filed 8-15-13; 8:45 am]
BILLING CODE 4910-13-P
