Document ID: FAA-2013-0694-0007
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2014-03-04T05:00Z

[Federal Register Volume 79, Number 42 (Tuesday, March 4, 2014)]
[Rules and Regulations]
[Pages 12045-12049]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-04546]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0694; Directorate Identifier 2013-NM-097-AD; 
Amendment 39-17775; AD 2014-05-02]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2002-10-11, 
which applied to certain The Boeing Company Model 737-100, -200, -200C, 
-300, -400, and -500 series airplanes. AD 2002-10-11 required 
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. This new AD specifies a drain path inspection for 
all airplanes. For certain airplanes, this new AD reduces the 
repetitive inspection interval; and adds repetitive inspections of the 
frame chord drain path for obstructions and debris, and corrective 
actions if necessary. This AD was prompted by three reports of severe 
corrosion in the area affected by AD 2002-10-11. 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 April 8, 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).

ADDRESSES: 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.

[[Page 12046]]

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2013-
0694; 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 address for the Docket Office (phone: 800-647-
5527) is Docket Management Facility, U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE., Washington, DC 20590.

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

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2002-10-11, Amendment 39-12757 (67 FR 36085, 
May 23, 2002). AD 2002-10-11 applied to certain The Boeing Company 
Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. The 
NPRM published in the Federal Register on August 16, 2013 (78 FR 
49978). The NPRM was prompted by three reports of severe corrosion in 
the area affected by AD 2002-10-11. The NPRM proposed to continue to 
require 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. The NPRM also proposed to specify 
a drain path inspection for all airplanes. For certain airplanes, the 
NPRM also proposed to reduce the repetitive inspection interval; and 
add repetitive inspections of the frame chord drain path for 
obstructions and debris, and corrective actions if necessary. 
Additionally, the NPRM proposed to limit corrosion and cracking repairs 
of the aft pressure bulkhead accomplished after the effective date of 
this AD to those approved by the FAA. 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
(78 FR 49978, August 16, 2013) and the FAA's response to each comment.

Support for the NPRM (78 FR 49978, August 16, 2013)

    Boeing stated that it concurs with the contents of the proposed 
rule (78 FR 49978, August 16, 2013).

Clarification of Effect of Winglet Installation

    Aviation Partners Boeing (the commenter) stated that the 
installation of winglets per STC ST01219SE does not affect the 
accomplishment of the manufacturer's service instructions.
    We concur with the commenter. We have re-designated paragraph (c) 
as paragraph (c)(1) and added paragraph (c)(2) to this final rule to 
state that installation of STC ST01219SE (http://rgl.faa.gov/
Regulatory--and--Guidance--Library/rgstc.nsf/0/
be866b732f6cf31086257b9700692796/$FILE/ST01219SE.pdf) does not affect 
the ability to accomplish the actions required by this final rule.

Request To Clarify Corrosion Inhibiting Compound (CIC) Replacement

    Alaska Airlines requested that we clarify whether the intent of 
paragraph (n) of the NPRM (78 FR 49978, August 16, 2013) is to require 
CIC removal and replacement following every inspection, or only when 
the CIC is deteriorated.
    We agree to clarify. CIC removal is not required at each 
inspection. This was not the intent of paragraph (n) of the NPRM (78 FR 
49978, August 16, 2013). The Accomplishment Instructions in Boeing 
Alert Service Bulletin 737-53A1075, Revision 3, dated June 8, 2000, 
specify when removal and replacement of CIC is required. We have 
revised paragraph (n) of this final rule to specify performing the CIC 
treatment as specified in the Accomplishment Instructions of Boeing 
Alert Service Bulletin 737-53A1075, Revision 3, dated June 8, 2000.

Request To Delay Issuance of the Final Rule

    All Nippon Airways (ANA) requested we consider issuing this final 
rule after Revision 4 to Boeing Service Bulletin 737-53A1075 is 
released, or include required repair methods in this final rule. ANA 
stated that paragraph (m) of the NPRM (78 FR 49978, August 16, 2013) 
would require approval of an alternative method of compliance (AMOC) if 
corrosion or cracking is found. ANA commented that having to request 
repair methods with an AMOC for any damage will burden operators during 
any new inspection.
    We disagree with ANA's request. We do not consider that delaying 
this final rule while waiting for additional service information is 
warranted due to the history and severity of corrosion reports from the 
fleet. Boeing Commercial Airplanes has received an Organization 
Designation Authorization (ODA). This authorization allows delegation 
of the authority to approve an AMOC for any repair required by this AD 
to the Boeing Commercial Airplanes ODA. We have not changed this final 
rule in this regard.

Request To Clarify Drain Path Inspection Requirements

    ANA requested we clarify the inspection requirements for the drain 
path in the chord frame. ANA stated that the inspection area is not 
clear because the NPRM (78 FR 49978, August 16, 2013) has no figure of 
the inspection area.
    We agree to clarify. We have revised paragraph (n) of this final 
rule to specify a figure in the Accomplishment Instructions of Boeing 
Alert Service Bulletin 737-53A1075, Revision 3, dated June 8, 2000, for 
doing the drain path inspection.

Request To Clarify Aft Pressure Bulkhead Inspection

    ANA requested that we clarify paragraph (o) of the NPRM (78 FR 
49978, August 16, 2013) for the optional aft pressure bulkhead 
inspection, to specify whether the actions terminate the requirements 
of paragraph (l) of the NPRM. ANA also stated that the last sentence of 
paragraph (o) of the NPRM incorrectly refers to paragraph (k) of the 
NPRM instead of paragraph (l) of the NPRM.
    We agree to clarify paragraph (o) of this final rule. We have 
revised paragraph (o) of this final rule to clarify that the 
requirement for the first inspection done after the effective date of 
this final rule that is required by paragraph (l)(2) of this final rule 
may be satisfied by doing the actions specified in paragraph (o) of 
this final rule. We have also revised paragraph (o) in this final rule 
to clarify that the repetitive inspection requirements are required 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 final rule are 
accomplished.

[[Page 12047]]

Changes to This Final Rule

    We have revised paragraph (i)(1) of this final rule to clarify that 
contacting the FAA or a Boeing Company Designated Engineering 
Representative for repairs, as specified in AD 2002-10-11, Amendment 
39-12757 (67 FR 36085, May 23, 2002), is still acceptable.
    We have also revised paragraph (m)(2) of this final rule to clarify 
that the compliance time is on or after the effective date of this 
final rule.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described and minor editorial changes. We have 
determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 49978, August 16, 2013) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 49978, August 16, 2013).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of 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......................  4 work-hours x $85               $0   $340 per inspection  $142,460 per
                                   per hour = $340                       cycle.               inspection cycle.
                                   per inspection
                                   cycle.
----------------------------------------------------------------------------------------------------------------

    The new 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................................  Up to 136 work-hours x            $5,217   Up to $16,777.
                                         $85 per hour = Up to
                                         $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

    We have determined that 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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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:

2014-05-02 The Boeing Company: Amendment 39-17775 ; Docket No. FAA-
2013-0694; Directorate Identifier 2013-NM-097-AD.

(a) Effective Date

    This AD is effective April 8, 2014.

(b) Affected ADs

    This AD supersedes AD 2002-10-11, Amendment 39-12757 (67 FR 
36085, May 23, 2002).

(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 1 through 3132 inclusive.
    (2) Installation of Supplemental Type Certificate (STC) 
ST01920SE (http://rgl.faa.gov/Regulatory--and--Guidance--Library/
rgstc.nsf/0/be866b732f6cf31086257b9700692796/$FILE/ST01219SE.pdf) 
does not affect the ability to accomplish the actions required by 
this AD. Therefore, for airplanes on which STC ST01920SE is 
installed, a ''change in product'' alternative method of compliance 
(AMOC) approval request is not necessary to

[[Page 12048]]

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 (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 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

    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; 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 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 Visual Inspections of Aft Pressure Bulkhead

    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 Pressure 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, 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 Detailed Inspections of Aft Pressure Bulkhead

    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 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

[[Page 12049]]

approval letter must specifically reference this AD.
    (2) On or 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 Repetitive Drain Path Inspections

    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, 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) New Optional Repetitive Aft Pressure Bulkhead Inspections and 
Corrective Action

    For airplanes having L/Ns 1043 through 3132 inclusive: In lieu 
of performing the first inspection after the effective date of this 
AD 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 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 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.

(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.
    (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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on February 18, 2014.
Ross Landes,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-04546 Filed 3-3-14; 8:45 am]
BILLING CODE 4910-13-P