Airworthiness Directives; The Boeing Company Airplanes, 52953-52957 [2014-21019]
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Rules and Regulations
Federal Register
Vol. 79, No. 172
Friday, September 5, 2014
This section of the FEDERAL REGISTER
contains regulatory documents having general
applicability and legal effect, most of which
are keyed to and codified in the Code of
Federal Regulations, which is published under
50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by
the Superintendent of Documents. Prices of
new books are listed in the first FEDERAL
REGISTER issue of each week.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0623; Directorate
Identifier 2014–NM–139–AD; Amendment
39–17966; AD 2014–18–02]
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2014–05–
02 for certain The Boeing Company
Model 737–100, –200, –200C, –300,
–400, and –500 series airplanes. AD
2014–05–02 required repetitive
inspections for cracking and corrosion
of the aft pressure bulkhead, repetitive
inspections of the frame chord drain
path for debris, and corrective actions if
necessary; and, for certain airplanes,
enlargement of frame chord drain holes.
This AD requires the same actions as
AD 2014–05–02, but revises a certain
repetitive inspection interval to avoid a
misunderstanding of the repetitive
inspection interval for the aft pressure
bulkhead. This AD was prompted by
reports from operators expressing
confusion regarding a certain repetitive
inspection interval for the aft pressure
bulkhead. 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.
DATES: This AD is effective September
22, 2014.
The Director of the Federal Register
approved the incorporation by reference
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SUMMARY:
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of certain publications listed in this AD
as of June 27, 2002 (67 FR 36085, May
23, 2002).
We must receive any comments on
this AD by October 20, 2014.
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: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590, 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 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.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2014–
0623; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (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
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425–917–6590; email: alan.pohl@
faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On February 18, 2014, we issued AD
2014–05–02, Amendment 39–17775 (79
FR 12045, March 4, 2014), for certain
The Boeing Company Model 737–100,
–200, –200C, –300, –400, and –500
series airplanes. AD 2014–05–02
required repetitive inspections for
cracking and corrosion of the aft
pressure bulkhead, repetitive
inspections of the frame chord drain
path for debris, and corrective actions if
necessary; and, for certain airplanes,
enlargement of frame chord drain holes.
AD 2014–05–02 resulted from three
reports of severe corrosion in the area
affected by AD 2002–10–11,
Amendment 39–12757 (67 FR 36085,
May 23, 2002), which AD 2014–05–02
superseded. We issued AD 2014–05–02
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.
Actions Since AD 2014–05–02,
Amendment 39–17775 (79 FR 12045,
March 4, 2014) Was Issued
Since we issued AD 2014–05–02,
Amendment 39–17775 (79 FR 12045,
March 4, 2014), we have received
reports from operators expressing
confusion regarding the repetitive
inspection interval for the aft pressure
bulkhead inspection that was required
by paragraph (l)(2) of AD 2014–05–02.
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.
FAA’s Determination
We are issuing 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.
AD Requirements
This AD requires the same actions
that were required by AD 2014–05–02,
Amendment 39–17775 (79 FR 12045,
March 4, 2014), but we have revised the
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wording of the repetitive inspection
interval for the aft pressure bulkhead
specified in paragraph (l)(2) of this AD
to clarify the required action. We have
stated that the repetitive inspection
interval must be repeated at intervals
not to exceed 2 years.
Additional Change to AD 2014–05–02,
Amendment 39–17775 (79 FR 12045,
March 4, 2014)
We have corrected a typographical
error in the supplemental type
certificate number that is in paragraph
(c)(2) of AD 2014–05–02, Amendment
39–17775 (79 FR 12045, March 4, 2014).
We have also added a statement to
paragraphs (k) and (o) of this AD that for
repaired areas, the required inspection
may be accomplished without removal
of the repairs. This change will not
increase the economic burden on any
operator, nor will it increase the scope
of this AD.
FAA’s Justification and Determination
of the Effective Date
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
rule because operators have been
uncertain of the correct repetitive
inspection interval for the aft pressure
bulkhead inspection. Therefore, we find
that notice and opportunity for prior
public comment are impracticable and
that good cause exists for making this
amendment effective in less than 30
days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not provide you with notice and
an opportunity to provide your
comments before it becomes effective.
However, we invite you to send any
written data, views, or arguments about
this AD. Send your comments to an
address listed under the ADDRESSES
section. Include the docket number
FAA–2014–0623, and directorate
identifier 2014–NM–139–AD at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this 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 AD.
Costs of Compliance
We estimate that this AD affects 419
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Parts cost
Inspection [actions retained from AD
2014–05–02, Amendment 39–
17775 (79 FR 12045, March 4,
2014)].
4 work-hours × $85 per hour = $
340 per inspection cycle.
$0
The requirements of this 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.
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 [actions retained from AD 2014–05–02, Amendment
39–17775 (79 FR 12045, March 4, 2014)].
Up to 136 work-hours × $85 per hour = Up to
$11,560.
$5,217
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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
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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
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
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Cost per
product
Up to $16,777.
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation
in Alaska, and
(4) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends part 39 of the Federal
Aviation Regulations (14 CFR part 39) as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2014–05–02, Amendment 39–17775 (79
FR 12045, March 4, 2014), and adding
the following new AD:
■
2014–18–02 The Boeing Company:
Amendment 39–17966; Docket No.
FAA–2014–0623; Directorate Identifier
2014–NM–139–AD.
(a) Effective Date
This AD is effective September 22, 2014.
(b) Affected ADs
This AD replaces AD 2014–05–02,
Amendment 39–17775 (79 FR 12045, March
4, 2014).
(c) Applicability
(1) This AD applies to The Boeing
Company Model 737–100, –200, –200C,
–300, –400, and –500 series airplanes,
certificated in any category, line numbers
(LNs) 1 through 3132 inclusive.
(2) Installation of Supplemental Type
Certificate (STC) ST01219SE (https://
rgl.faa.govRegulatory_and_Guidance
_Libraryrgstc.nsf0be866b732f
6cf31086257b9700692796
$FILEST01219SE.pdf) does not affect the
ability to accomplish the actions required by
this AD. Therefore, for airplanes on which
STC ST01219SE is installed, a ’’change in
product’’ alternative method of compliance
(AMOC) approval request is not necessary to
comply with the requirements of 14 CFR
39.17.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
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(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.
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(g) Retained Initial Aft Pressure Bulkhead
Inspection
This paragraph restates the requirements of
paragraph (g) of AD 2014–05–02,
Amendment 39–17775 (79 FR 12045, March
4, 2014), with no changes. For Model 737
series airplanes having LNs 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 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 Boeing Material
Specification (BMS) 3–23, or equivalent.
After June 8, 2000 (the effective date of AD
2014–05–02), 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 (h) of AD 2014–05–02,
Amendment 39–17775 (79 FR 12045, March
4, 2014), with no changes. 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 April
8, 2014 (the effective date of AD 2014–05–
02), 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
This paragraph restates the requirements of
paragraph (i) of AD 2014–05–02, Amendment
39–17775 (79 FR 12045, March 4, 2014), with
no changes. 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 April
8, 2014 (the effective date of AD 2014–05–02,
Amendment 39–17775 (79 FR 12045, March
4, 2014)): 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; or according to a method approved by
the Manager, Seattle Aircraft Certification
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52955
Office (ACO), FAA; or per data meeting the
type certification basis of the airplane
approved by a Boeing Company Designated
Engineering Representative (DER) 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) If the inspection was done on or after
April 8, 2014 (the effective date of AD 2014–
05–02, Amendment 39–17775 (79 FR 12045,
March 4, 2014)): Repair using a method
approved in accordance with the procedures
specified in paragraph (p) of this AD.
(j) Retained Repetitive Visual Inspections of
Aft Pressure Bulkhead
This paragraph restates the requirements of
paragraph (j) of AD 2014–05–02, Amendment
39–17775 (79 FR 12045, March 4, 2014), with
no changes. 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 Pressure Bulkhead Detailed
Inspection
This paragraph restates the requirements of
paragraph (k) of AD 2014–05–02,
Amendment 39–17775 (79 FR 12045, March
4, 2014), with clarification for repaired areas.
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,
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.
For repaired areas, this inspection may be
accomplished without removal of the repairs.
(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
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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 Detailed Inspections
of Aft Pressure Bulkhead
This paragraph restates the requirements of
paragraph (l) of AD 2014–05–02, Amendment
39–17775 (79 FR 12045, March 4, 2014), with
revised compliance times in paragraph (l)(2)
of this AD. 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 within
2 years since the last inspection or within
120 days after April 8, 2014 (the effective
date of AD 2014–05–02, Amendment 39–
17775 (79 FR 12045, March 4, 2014)),
whichever occurs later. Repeat the inspection
thereafter at intervals not to exceed 2 years.
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(m) Retained Repair
This paragraph restates the requirements of
paragraph (m) of AD 2014–05–02,
Amendment 39–17775 (79 FR 12045, March
4, 2014), with no changes. 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
April 8, 2014 (the effective date of AD 2014–
05–02, Amendment 39–17775 (79 FR 12045,
March 4, 2014)): 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
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) On or after April 8, 2014 (the effective
date of AD 2014–05–02, Amendment 39–
17775 (79 FR 12045, March 4, 2014)), 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.
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(n) Retained Repetitive Drain Path
Inspections
This paragraph restates the requirements of
paragraph (n) of AD 2014–05–02,
Amendment 39–17775 (79 FR 12045, March
4, 2014), with no changes. 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 April 8, 2014 (the
effective date of AD 2014–05–02), whichever
occurs later: Do a general visual inspection
of the drain path in the chord frame for
debris, in accordance with Figure 2, Steps 1
through 6, of the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–53A1075, Revision 3, dated June 8,
2000. 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, as specified in the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1075, Revision 3,
dated June 8, 2000. 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) Retained Optional Repetitive Aft
Pressure Bulkhead Inspections and
Corrective Action
This paragraph restates the requirements of
paragraph (o) of AD 2014–05–02,
Amendment 39–17775 (79 FR 12045, March
4, 2014), with clarification for repaired areas.
For airplanes having L/Ns 1043 through 3132
inclusive: In lieu of performing the first
inspection after April 8, 2014 (the effective
date of AD 2014–05–02), required by
paragraph (l)(2) 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 the service information
identified in paragraph (o)(1), (o)(2), or (o)(3)
of this AD, or within 120 days after April 8,
2014, 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,
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dated June 8, 2000. For repaired areas, this
inspection may be accomplished without
removal of the repairs. 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 for a period not to exceed 2
years, until the actions required by paragraph
(l)(2) of this AD are accomplished.
(1) Boeing Alert Service Bulletin 737–
53A1075, Revision 1, dated September 2,
1983.
(2) Boeing Alert Service Bulletin 737–
53A1075, Revision 2, dated July 13, 1984.
(3) Boeing Alert Service Bulletin 737–
53A1075, Revision 3, dated June 8, 2000.
(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
paragraph (q) of this AD. Information may be
emailed to 9–ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
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.
(5) AMOCs approved previously in
accordance with AD 2014–05–02,
Amendment 39–17775 (79 FR 12045, March
4, 2014)), are approved as AMOCs for the
corresponding provisions of this AD.
(q) Related Information
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, WA 98057–3356;
phone: 425–917–6450; fax: 425–917–6590;
email: alan.pohl@faa.gov.
(r) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
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05SER1
Federal Register / Vol. 79, No. 172 / Friday, September 5, 2014 / Rules and Regulations
(3) The following service information was
approved for IBR on June 27, 2002 (67 FR
36085, May 23, 2002).
(i) Boeing Alert Service Bulletin 737–
53A1075, Revision 1, dated September 2,
1983.
(ii) Boeing Alert Service Bulletin 737–
53A1075, Revision 2, dated July 13, 1984.
(iii) Boeing Alert Service Bulletin 737–
53A1075, Revision 3, dated June 8, 2000.
(4) For Boeing 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.
(5) You may view this service information
at 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.
(6) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on August
22, 2014.
Kevin Hull,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
1 CFR Part 51, subject to the annual
revision of FAA Order 7400.9 and
publication of conforming amendments.
ADDRESSES: FAA Order 7400.9X,
Airspace Designations and Reporting
Points, and subsequent amendments can
be viewed online at https://www.faa.gov/
air_traffic/publications/. The Order is
also available for inspection at the
National Archives and Records
Administration (NARA). For
information on the availability of this
material at NARA, call (202) 741–6030,
or go to https://www.archives.gov/
federal_register/code_of_federalregulations/ibr_locations.html.
FAA Order 7400.9, Airspace
Designations and Reporting Points, is
published yearly and effective on
September 15. For further information,
you can contact the Airspace Policy and
Regulations Group, Federal Aviation
Administration, 800 Independence
Avenue SW., Washington, DC, 20591;
telephone: (202) 267–8783.
FOR FURTHER INFORMATION CONTACT:
Richard Roberts, Federal Aviation
Administration, Operations Support
Group, Western Service Center, 1601
Lind Avenue SW., Renton, WA 98057;
telephone (425) 203–4517.
SUPPLEMENTARY INFORMATION:
[FR Doc. 2014–21019 Filed 9–4–14; 8:45 am]
History
BILLING CODE 4910–13–P
On December 27, 2013, the FAA
published in the Federal Register a
notice of proposed rulemaking (NPRM)
to establish controlled airspace at
Flagstaff, AZ (78 FR 78794). Interested
parties were invited to participate in
this rulemaking effort by submitting
written comments on the proposal to the
FAA. One comment was received from
the National Business Aviation
Association in support of the
recommended change.
Class E airspace designations are
published in paragraph 6006, of FAA
Order 7400.9X dated August 7, 2013,
and effective September 15, 2013, which
is incorporated by reference in 14 CFR
71.1. The Class E airspace designations
listed in this document will be
published subsequently in that Order.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2013–0957; Airspace
Docket No. 13–AWP–18]
Establishment of Class E Airspace;
Flagstaff, AZ
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
This action establishes Class
E airspace at the Flagstaff VHF OmniDirectional Radio Range/Distance
Measuring Equipment (VOR/DME)
navigation aid, Flagstaff, AZ, to
facilitate vectoring of Instrument Flight
Rules (IFR) aircraft under control of
Albuquerque Air Route Traffic Control
Center (ARTCC). This improves the
safety and management of IFR
operations within the National Airspace
System.
DATES: Effective date, 0901 UTC,
November 13, 2014. The Director of the
Federal Register approves this
incorporation by reference action under
tkelley on DSK3SPTVN1PROD with RULES
SUMMARY:
VerDate Mar<15>2010
17:04 Sep 04, 2014
Jkt 232001
The Rule
This action amends Title 14 Code of
Federal Regulations (14 CFR) Part 71 by
establishing Class E en route domestic
airspace extending upward from 1,200
feet above the surface, at the Flagstaff
VOR/DME navigation aid, Flagstaff, AZ,
to accommodate IFR aircraft under
control of Albuquerque Air Route
Traffic Control Center (ARTCC) by
vectoring aircraft from en route airspace
to terminal areas. This action is
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
52957
necessary for the safety and
management of IFR operations.
The FAA has determined this
regulation only involves an established
body of technical regulations for which
frequent and routine amendments are
necessary to keep them operationally
current. Therefore, this regulation: (1) Is
not a ‘‘significant regulatory action’’
under Executive Order 12866; (2) is not
a ‘‘significant rule’’ under DOT
Regulatory Policies and Procedures (44
FR 11034; February 26, 1979); and (3)
does not warrant preparation of a
regulatory evaluation as the anticipated
impact is so minimal. Since this is a
routine matter that only affects air traffic
procedures and air navigation, it is
certified this rule, when promulgated,
does not have a significant economic
impact on a substantial number of small
entities under the criteria of the
Regulatory Flexibility Act. The FAA’s
authority to issue rules regarding
aviation safety is found in Title 49 of the
U.S. Code. Subtitle 1, Section 106
discusses the authority of the FAA
Administrator. Subtitle VII, Aviation
Programs, describes in more detail the
scope of the agency’s authority. This
rulemaking is promulgated under the
authority described in Subtitle VII, Part
A, Subpart I, Section 40103. Under that
section, the FAA is charged with
prescribing regulations to assign the use
of airspace necessary to ensure the
safety of aircraft and the efficient use of
airspace. This regulation is within the
scope of that authority as it establishes
controlled airspace at the Flagstaff VOR/
DME navigation aid, Flagstaff, AZ.
Environmental Review
The FAA has determined that this
action qualifies for categorical exclusion
under the National Environmental
Policy Act in accordance with FAA
Order 1050.1E, ‘‘Environmental
Impacts: Policies and Procedures,’’
paragraph 311a. This airspace action is
not expected to cause any potentially
significant environmental impacts, and
no extraordinary circumstances exist
that warrant preparation of an
environmental assessment.
List of Subjects in 14 CFR Part 71
Airspace, Incorporation by reference,
Navigation (air).
Adoption of the Amendment
In consideration of the foregoing, the
Federal Aviation Administration
amends 14 CFR Part 71 as follows:
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]]>Agencies
[Federal Register Volume 79, Number 172 (Friday, September 5, 2014)]
[Rules and Regulations]
[Pages 52953-52957]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-21019]
========================================================================
Rules and Regulations
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains regulatory documents
having general applicability and legal effect, most of which are keyed
to and codified in the Code of Federal Regulations, which is published
under 50 titles pursuant to 44 U.S.C. 1510.
The Code of Federal Regulations is sold by the Superintendent of Documents.
Prices of new books are listed in the first FEDERAL REGISTER issue of each
week.
========================================================================
Federal Register / Vol. 79, No. 172 / Friday, September 5, 2014 /
Rules and Regulations
[[Page 52953]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2014-0623; Directorate Identifier 2014-NM-139-AD;
Amendment 39-17966; AD 2014-18-02]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2014-05-02 for
certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and
-500 series airplanes. AD 2014-05-02 required repetitive inspections
for cracking and corrosion of the aft pressure bulkhead, repetitive
inspections of the frame chord drain path for debris, and corrective
actions if necessary; and, for certain airplanes, enlargement of frame
chord drain holes. This AD requires the same actions as AD 2014-05-02,
but revises a certain repetitive inspection interval to avoid a
misunderstanding of the repetitive inspection interval for the aft
pressure bulkhead. This AD was prompted by reports from operators
expressing confusion regarding a certain repetitive inspection interval
for the aft pressure bulkhead. 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.
DATES: This AD is effective September 22, 2014.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of June 27, 2002
(67 FR 36085, May 23, 2002).
We must receive any comments on this AD by October 20, 2014.
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: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590, 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 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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0623; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The street address for the Docket Office (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:
Discussion
On February 18, 2014, we issued AD 2014-05-02, Amendment 39-17775
(79 FR 12045, March 4, 2014), for certain The Boeing Company Model 737-
100, -200, -200C, -300, -400, and -500 series airplanes. AD 2014-05-02
required repetitive inspections for cracking and corrosion of the aft
pressure bulkhead, repetitive inspections of the frame chord drain path
for debris, and corrective actions if necessary; and, for certain
airplanes, enlargement of frame chord drain holes. AD 2014-05-02
resulted from three reports of severe corrosion in the area affected by
AD 2002-10-11, Amendment 39-12757 (67 FR 36085, May 23, 2002), which AD
2014-05-02 superseded. We issued AD 2014-05-02 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.
Actions Since AD 2014-05-02, Amendment 39-17775 (79 FR 12045, March 4,
2014) Was Issued
Since we issued AD 2014-05-02, Amendment 39-17775 (79 FR 12045,
March 4, 2014), we have received reports from operators expressing
confusion regarding the repetitive inspection interval for the aft
pressure bulkhead inspection that was required by paragraph (l)(2) of
AD 2014-05-02. 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.
FAA's Determination
We are issuing 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.
AD Requirements
This AD requires the same actions that were required by AD 2014-05-
02, Amendment 39-17775 (79 FR 12045, March 4, 2014), but we have
revised the
[[Page 52954]]
wording of the repetitive inspection interval for the aft pressure
bulkhead specified in paragraph (l)(2) of this AD to clarify the
required action. We have stated that the repetitive inspection interval
must be repeated at intervals not to exceed 2 years.
Additional Change to AD 2014-05-02, Amendment 39-17775 (79 FR 12045,
March 4, 2014)
We have corrected a typographical error in the supplemental type
certificate number that is in paragraph (c)(2) of AD 2014-05-02,
Amendment 39-17775 (79 FR 12045, March 4, 2014).
We have also added a statement to paragraphs (k) and (o) of this AD
that for repaired areas, the required inspection may be accomplished
without removal of the repairs. This change will not increase the
economic burden on any operator, nor will it increase the scope of this
AD.
FAA's Justification and Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because
operators have been uncertain of the correct repetitive inspection
interval for the aft pressure bulkhead inspection. Therefore, we find
that notice and opportunity for prior public comment are impracticable
and that good cause exists for making this amendment effective in less
than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments before it becomes effective. However, we invite
you to send any written data, views, or arguments about this AD. Send
your comments to an address listed under the ADDRESSES section. Include
the docket number FAA-2014-0623, and directorate identifier 2014-NM-
139-AD at the beginning of your comments. We specifically invite
comments on the overall regulatory, economic, environmental, and energy
aspects of this AD. We will consider all comments received by the
closing date and may amend this 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 AD.
Costs of Compliance
We estimate that this AD affects 419 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspection [actions retained from 4 work-hours x $85 $0 $340 per inspection $142,460 per
AD 2014-05-02, Amendment 39- per hour = $ 340 cycle. inspection cycle.
17775 (79 FR 12045, March 4, per inspection
2014)]. cycle.
----------------------------------------------------------------------------------------------------------------
The requirements of this 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 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 [actions retained from AD 2014- Up to 136 work-hours x $5,217 Up to $16,777.
05-02, Amendment 39-17775 (79 FR $85 per hour = Up to
12045, March 4, 2014)]. $11,560.
----------------------------------------------------------------------------------------------------------------
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
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
[[Page 52955]]
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends part 39 of the Federal Aviation
Regulations (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)
2014-05-02, Amendment 39-17775 (79 FR 12045, March 4, 2014), and adding
the following new AD:
2014-18-02 The Boeing Company: Amendment 39-17966; Docket No. FAA-
2014-0623; Directorate Identifier 2014-NM-139-AD.
(a) Effective Date
This AD is effective September 22, 2014.
(b) Affected ADs
This AD replaces AD 2014-05-02, Amendment 39-17775 (79 FR 12045,
March 4, 2014).
(c) Applicability
(1) This AD applies to The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any
category, line numbers (LNs) 1 through 3132 inclusive.
(2) Installation of Supplemental Type Certificate (STC)
ST01219SE (https://
rgl.faa.govRegulatoryandGuidanceLibraryrgs
tc.nsf0be866b732f6cf31086257b9700692796$FILEST01219SE.pdf) does not
affect the ability to accomplish the actions required by this AD.
Therefore, for airplanes on which STC ST01219SE is installed, a
''change in product'' alternative method of compliance (AMOC)
approval request is not necessary to comply with the requirements of
14 CFR 39.17.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by 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 (g) of AD
2014-05-02, Amendment 39-17775 (79 FR 12045, March 4, 2014), with no
changes. For Model 737 series airplanes having LNs 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 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 Boeing
Material Specification (BMS) 3-23, or equivalent. After June 8, 2000
(the effective date of AD 2014-05-02), 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 (h) of AD
2014-05-02, Amendment 39-17775 (79 FR 12045, March 4, 2014), with no
changes. 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 April 8, 2014 (the effective date of AD 2014-05-02), 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
This paragraph restates the requirements of paragraph (i) of AD
2014-05-02, Amendment 39-17775 (79 FR 12045, March 4, 2014), with no
changes. 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 April 8, 2014 (the
effective date of AD 2014-05-02, Amendment 39-17775 (79 FR 12045,
March 4, 2014)): 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; or according to a
method approved by the Manager, Seattle Aircraft Certification
Office (ACO), FAA; or per data meeting the type certification basis
of the airplane approved by a Boeing Company Designated Engineering
Representative (DER) 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) If the inspection was done on or after April 8, 2014 (the
effective date of AD 2014-05-02, Amendment 39-17775 (79 FR 12045,
March 4, 2014)): Repair using a method approved in accordance with
the procedures specified in paragraph (p) of this AD.
(j) Retained Repetitive Visual Inspections of Aft Pressure Bulkhead
This paragraph restates the requirements of paragraph (j) of AD
2014-05-02, Amendment 39-17775 (79 FR 12045, March 4, 2014), with no
changes. 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 Pressure Bulkhead Detailed Inspection
This paragraph restates the requirements of paragraph (k) of AD
2014-05-02, Amendment 39-17775 (79 FR 12045, March 4, 2014), with
clarification for repaired areas. 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, 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. For repaired areas,
this inspection may be accomplished without removal of the repairs.
(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
[[Page 52956]]
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 Detailed Inspections of Aft Pressure Bulkhead
This paragraph restates the requirements of paragraph (l) of AD
2014-05-02, Amendment 39-17775 (79 FR 12045, March 4, 2014), with
revised compliance times in paragraph (l)(2) of this AD. 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 within 2 years since the last inspection or
within 120 days after April 8, 2014 (the effective date of AD 2014-
05-02, Amendment 39-17775 (79 FR 12045, March 4, 2014)), whichever
occurs later. Repeat the inspection thereafter at intervals not to
exceed 2 years.
(m) Retained Repair
This paragraph restates the requirements of paragraph (m) of AD
2014-05-02, Amendment 39-17775 (79 FR 12045, March 4, 2014), with no
changes. 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 April 8, 2014 (the
effective date of AD 2014-05-02, Amendment 39-17775 (79 FR 12045,
March 4, 2014)): 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 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) On or after April 8, 2014 (the effective date of AD 2014-05-
02, Amendment 39-17775 (79 FR 12045, March 4, 2014)), 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) Retained Repetitive Drain Path Inspections
This paragraph restates the requirements of paragraph (n) of AD
2014-05-02, Amendment 39-17775 (79 FR 12045, March 4, 2014), with no
changes. 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 April 8, 2014 (the effective date of
AD 2014-05-02), whichever occurs later: Do a general visual
inspection of the drain path in the chord frame for debris, in
accordance with Figure 2, Steps 1 through 6, of the Accomplishment
Instructions of Boeing Alert Service Bulletin 737-53A1075, Revision
3, dated June 8, 2000. 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, as specified in the Accomplishment Instructions of
Boeing Alert Service Bulletin 737-53A1075, Revision 3, dated June 8,
2000. 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) Retained Optional Repetitive Aft Pressure Bulkhead Inspections and
Corrective Action
This paragraph restates the requirements of paragraph (o) of AD
2014-05-02, Amendment 39-17775 (79 FR 12045, March 4, 2014), with
clarification for repaired areas. For airplanes having L/Ns 1043
through 3132 inclusive: In lieu of performing the first inspection
after April 8, 2014 (the effective date of AD 2014-05-02), required
by paragraph (l)(2) 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 the service
information identified in paragraph (o)(1), (o)(2), or (o)(3) of
this AD, or within 120 days after April 8, 2014, 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.
For repaired areas, this inspection may be accomplished without
removal of the repairs. 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 for a period not to exceed 2 years,
until the actions required by paragraph (l)(2) of this AD are
accomplished.
(1) Boeing Alert Service Bulletin 737-53A1075, Revision 1, dated
September 2, 1983.
(2) Boeing Alert Service Bulletin 737-53A1075, Revision 2, dated
July 13, 1984.
(3) Boeing Alert Service Bulletin 737-53A1075, Revision 3, dated
June 8, 2000.
(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 paragraph
(q) 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.
(5) AMOCs approved previously in accordance with AD 2014-05-02,
Amendment 39-17775 (79 FR 12045, March 4, 2014)), are approved as
AMOCs for the corresponding provisions of this AD.
(q) Related Information
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, WA 98057-3356;
phone: 425-917-6450; fax: 425-917-6590; email: alan.pohl@faa.gov.
(r) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
[[Page 52957]]
(3) The following service information was approved for IBR on
June 27, 2002 (67 FR 36085, May 23, 2002).
(i) Boeing Alert Service Bulletin 737-53A1075, Revision 1, dated
September 2, 1983.
(ii) Boeing Alert Service Bulletin 737-53A1075, Revision 2,
dated July 13, 1984.
(iii) Boeing Alert Service Bulletin 737-53A1075, Revision 3,
dated June 8, 2000.
(4) For Boeing 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.
(5) You may view this service information at 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.
(6) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on August 22, 2014.
Kevin Hull,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-21019 Filed 9-4-14; 8:45 am]
BILLING CODE 4910-13-P
