```

[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 
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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 http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: 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 http://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 http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this 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 (http://
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: http://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
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