[Federal Register Volume 78, Number 73 (Tuesday, April 16, 2013)]
[Proposed Rules]
[Pages 22439-22442]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-08908]



[[Page 22439]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0327; Directorate Identifier 2011-NM-161-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede an existing airworthiness directive 
(AD) that applies to all The Boeing Company Model 737-100, -200, -200C, 
-300, -400, and -500 series airplanes. The existing AD currently 
requires repetitive inspections for cracking in and around the upper 
and lower hinge cutouts of the forward entry and forward galley service 
doorways, and corrective actions if necessary. Since we issued that AD, 
we have received multiple reports of cracks in the skin and/or bear 
strap at the forward galley service doorway hinge cutouts, and multiple 
reports of cracking under the repairs installed at the hinge cutouts. 
This proposed AD would reduce the inspection threshold for cracking in 
and around the galley service doorway hinge cutouts, add inspections of 
certain repaired structure at the forward entry and galley service 
doorway upper and lower hinge cutouts, expand the inspection area at 
the forward entry and galley service doorway upper and lower hinge 
cutouts, and remove certain airplanes from the applicability. We are 
proposing this AD to detect and correct such cracking, which could 
result in rapid decompression of the airplane.

DATES: We must receive comments on this proposed AD by May 31, 2013.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, P. 
O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; phone: 206-544-5000, 
extension 1; fax: 206-766-5680; Internet: https://www.myboeingfleet.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: Alan Pohl, Aerospace Engineer, 
Airframe Branch, ANM-120S, Seattle Aircraft Certification Office (ACO), 
FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6450; 
fax: 425-917-6590; email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-0327; 
Directorate Identifier 2011-NM-161-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On May 9, 2008, we issued AD 2008-11-04, Amendment 39-15526 (73 FR 
29421, May 21, 2008), for all The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes. That AD requires 
repetitive inspections for cracking in and around the upper and lower 
hinge cutouts of the forward entry and forward galley service doorways, 
and corrective actions if necessary. That AD resulted from multiple 
reports of cracks found in the skin, bearstrap, and/or frame outer 
chord in the hinge cutout areas of the forward entry and forward galley 
service doorways. We issued that AD to detect and correct cracking, 
which could result in rapid decompression of the airplane.

Actions Since Existing AD (73 FR 29421, May 21, 2008) Was Issued

    Since we issued AD 2008-11-04, Amendment 39-15526 (73 FR 29421, May 
21, 2008), we have received 15 reports of cracks in the skin and/or 
bear strap at the forward galley service doorway hinge cutouts found on 
airplanes that had accumulated fewer than 40,000 total flight cycles 
(the inspection compliance time required by the existing AD). The 
lowest reported total flight cycles on an airplane with a crack were 
24,423; this airplane had a 0.55-inch crack in the skin and no cracks 
in the bear strap. We have also received four reports of cracking under 
the repairs installed at the hinge cutouts as specified in the 
structural repair manual (SRM).

Relevant Service Information

    We reviewed Boeing Service Bulletin 737-53A1200, Revision 2, dated 
September 12, 2012. For information on the procedures and compliance 
times, see this service information at http://www.regulations.gov by 
searching for Docket No. FAA-2013-0327.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would retain all the requirements of AD 2008-11-
04, Amendment 39-15526 (73 FR 29421, May 21, 2008), and would reduce 
the inspection threshold for cracking in and around the galley service 
doorway hinge cutouts, add inspections of certain repaired structure at 
the forward entry and galley service doorway upper and lower hinge 
cutouts, expand the inspection area at the forward entry and galley 
service doorway upper and lower hinge cutouts, and remove certain 
airplanes from the applicability.
    The phrase ``related investigative actions'' might be used in this 
proposed

[[Page 22440]]

AD. ``Related investigative actions'' are follow-on actions that (1) 
are related to the primary action, and (2) are actions that further 
investigate the nature of any condition found. Related investigative 
actions in an AD could include, for example, inspections.
    In addition, the phrase ``corrective actions'' might be used in 
this proposed AD. ``Corrective actions'' are actions that correct or 
address any condition found. Corrective actions in an AD could include, 
for example, repairs.

Change to Existing AD (73 FR 29421, May 21, 2008)

    This proposed AD would retain all the requirements of AD 2008-11-
04, Amendment 39-15526 (73 FR 29421, May 21, 2008). Since AD 2008-11-04 
was issued, the AD format has been revised, and certain paragraphs have 
been rearranged. As a result, the corresponding paragraph identifiers 
have changed in this proposed AD, as listed in the following table:

                      Revised Paragraph Identifiers
------------------------------------------------------------------------
  Requirement in AD 2008-11-04,
 Amendment 39-15526 (73 FR 29421,    Corresponding  requirement in this
          May 21, 2008)                         proposed AD
------------------------------------------------------------------------
 paragraph (f)                      paragraph (g)
 paragraph (g)                      paragraph (h)(1)
 paragraph (h)                      paragraph (h)(2)
------------------------------------------------------------------------

    We have revised paragraph (i) of AD 2008-11-04, Amendment 39-15526 
(73 FR 29421, May 21, 2008) (paragraph (i) of this proposed AD), by 
removing reference to Boeing 737-100/-200 SRM 53-30-1, Figures 20, 21, 
31, or 32; and Boeing 737-300/-400/-500 SRM 53-10-01, Repair 5, 6, or 
8. Instead, we have added Note 1 to paragraph (i) of this proposed AD 
to specify that guidance on repairs may be found in Boeing 737-100/-200 
SRM 53-30-1, Figure 20, 21, 31, or 32; or Boeing 737-300/-400/-500 SRM 
53-10-01, Repair 5, 6, or 8; as applicable.

Differences Between the Proposed AD and the Service Information

    Boeing Service Bulletin 737-53A1200, Revision 2, dated September 
12, 2012, specifies to contact the manufacturer for instructions on how 
to repair certain conditions, but this proposed AD would require 
repairing those conditions in one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Costs of Compliance

    We estimate that this proposed AD affects 547 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspections [retained actions      Up to 73 work-hours              $0  Up to $6,205 per     Up to $3,394,135
 from AD 2008-11-04, Amendment 39-  x $85 per hour =                     inspection cycle.    per inspection
 15526 (73 FR 29421, May 21,        $6,205 per                                                cycle.
 2008)].                            inspection cycle.
Inspection [new proposed action].  Up to 34 work-hours              $0  Up to $2,890 per     Up to $1,580,830
                                    x $85 per hour =                     inspection cycle.    per inspection
                                    $2,890 per                                                cycle.
                                    inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing airworthiness directive (AD) 
2008-11-04, Amendment 39-15526 (73 FR 29421, May 21, 2008), and adding 
the following new AD:

The Boeing Company: Docket No. FAA-2013-0327; Directorate Identifier 
2011-NM-161-AD.

[[Page 22441]]

(a) Comments Due Date

    The FAA must receive comments on this AD action by May 31, 2013.

(b) Affected ADs

    This AD supersedes AD 2008-11-04, Amendment 39-15526 (73 FR 
29421, May 21, 2008).

(c) Applicability

    This AD applies to The Boeing Company Model 737-100, -200, -
200C, -300, -400, and -500 series airplanes, certificated in any 
category, as identified in Boeing Service Bulletin 737-53A1200, 
Revision 2, dated September 12, 2012.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

    This AD was prompted by multiple reports of cracks in the skin 
and/or bear strap at the forward galley service doorway hinge 
cutouts, and multiple reports of cracking under the repairs 
installed at the hinge cutouts. We are issuing this AD to detect and 
correct such cracking, which could result in rapid decompression of 
the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

 (g) Retained Repetitive Inspections

    This paragraph restates the requirements of paragraph (f) of AD 
2008-11-04, Amendment 39-15526 (73 FR 29421, May 21, 2008). Except 
as provided by paragraph (h)(1) of this AD, at the applicable times 
specified in paragraph 1.E. ``Compliance,'' of Boeing Alert Service 
Bulletin 737-53A1200, dated April 13, 2006, do external detailed, 
low frequency eddy current (LFEC), high frequency eddy current 
(HFEC), and HFEC rotary probe inspections, as applicable, for cracks 
in and around the upper and lower hinge cutouts of the forward entry 
and forward galley service doorways, in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
53A1200, dated April 13, 2006, except as provided by paragraphs 
(h)(2) and (i) of this AD. Do not exceed the applicable repetitive 
interval for the previous inspection, as specified in Boeing Alert 
Service Bulletin 737-53A1200, dated April 13, 2006, as Option A or 
Option B. Repair any crack before further flight using a method 
approved in accordance with the procedures specified in paragraph 
(o) of this AD. Accomplishment of the actions required by paragraph 
(j) of this AD terminates the requirements of this paragraph.

(h) Retained Exceptions to Service Bulletin Specifications

    This paragraph restates the requirements of paragraphs (g) and 
(h) of AD 2008-11-04, Amendment 39-15526 (73 FR 29421, May 21, 
2008).
    (1) Where Boeing Alert Service Bulletin 737-53A1200, dated April 
13, 2006, specifies a compliance time after the release date of that 
service bulletin, this AD requires compliance within the specified 
compliance time after June 25, 2008 (the effective date of AD 2008-
11-04, Amendment 39-15526 (73 FR 29421, May 21, 2008)).
    (2) Although Boeing Alert Service Bulletin 737-53A1200, dated 
April 13, 2006, specifies contacting Boeing for information about 
installing an optional preventive modification that would terminate 
the repetitive inspections specified in paragraph (g) of this AD, 
this AD requires that any terminating action be done by using a 
method approved in accordance with the procedures specified in 
paragraph (o) of this AD.

(i) Retained Optional Terminating Action

    This paragraph restates the optional terminating action 
specified paragraph (i) of AD 2008-11-04, Amendment 39-15526 (73 FR 
29421, May 21, 2008), with revised method of compliance language. 
The inspections specified in paragraph (g) of this AD may be 
terminated at areas repaired using a method approved in accordance 
with the procedures specified in paragraph (o) of this AD.

    Note 1 to paragraph (i) of this AD:  Guidance on repairs can be 
found in Boeing 737-100/-200 SRM 53-30-1, Figure 20, 21, 31, or 32; 
or Boeing 737-300/-400/-500 SRM 53-10-01, Repair 5, 6, or 8; as 
applicable.

(j) New Repetitive Inspections and Repair

    Except as required by paragraph (l)(1) of this AD, at the 
applicable times specified in Paragraph 1.E., ``Compliance,'' of 
Boeing Service Bulletin 737-53A1200, Revision 2, dated September 12, 
2012: Do an external and internal detailed inspection, HFEC 
inspection, and HFEC hole probe inspection, at the forward entry and 
galley service doorway upper and lower hinge cutouts for cracking in 
the skin, bonded doubler, bearstrap, and frame outer chord, in 
accordance with the Accomplishment Instructions of Boeing Service 
Bulletin 737-53A1200, Revision 2, dated September 12, 2012, except 
as required by paragraph (m) of this AD. Options provided in Boeing 
Service Bulletin 737-53A1200, Revision 2, dated September 12, 2012, 
for accomplishing the inspections are acceptable for compliance with 
the corresponding requirements of this paragraph. Repeat the 
applicable inspections thereafter at the applicable times specified 
in paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 737-
53A1200, Revision 2, dated September 12, 2012. If any crack is 
found, before further flight, repair using a method approved in 
accordance with the procedures specified in paragraph (o) of this 
AD. Accomplishment of the initial inspections terminates the 
requirements of paragraph (g) of this AD.

(k) New Actions for Airplanes With Certain Repairs Installed

    (1) For airplanes with any SRM repair specified in paragraphs 
(k)(1)(i) though (k)(1)(vii) of this AD installed, at the applicable 
times specified in paragraph 1.E., ``Compliance,'' of Boeing Service 
Bulletin 737-53A1200, Revision 2, dated September 12, 2012: Do an 
external and internal detailed inspection, HFEC inspection, and LFEC 
inspection, at the forward entry and galley service doorway upper 
and lower hinge cutouts for cracking in the skin, bearstrap, and 
frame outer chord, in accordance with the Accomplishment 
Instructions of Boeing Service Bulletin 737-53A1200, Revision 2, 
dated September 12, 2012, except as required by paragraph (l)(2) of 
this AD. Repeat the inspection thereafter at the applicable times 
specified in paragraph 1.E., ``Compliance,'' of Boeing Service 
Bulletin 737-53A1200, Revision 2, dated September 12, 2012. If any 
crack is found, before further flight, repair using a method 
approved in accordance with the procedures specified in paragraph 
(o) of this AD.
    (i) Repair specified in Boeing 737-100/-200 SRM 53-30-03, Figure 
21.
    (ii) Repair specified in Boeing 737-100/200 SRM 53-30-03, Figure 
31.
    (iii) Repair 5 specified in Boeing 737-300 SRM 53-10-01; Repair 
5 specified in Boeing 737-400 SRM 53-10-01; or Repair 5 specified in 
Boeing 737-500 SRM 53-10-01; installed at the upper or lower hinge 
cutout.
    (iv) Repair specified in Boeing 737-100/200 SRM 53-30-03, Figure 
20.
    (v) Repair 6 specified in Boeing 737-300 SRM 53-10-01; Repair 6 
specified in Boeing 737-400 SRM 53-10-01; or Repair 6 specified in 
Boeing 737-500 SRM 53-10-01.
    (vi) Repair 8 specified in Boeing 737-300 SRM 53-10-01; Repair 8 
specified in Boeing 737-400 SRM 53-10-01; or Repair 8 specified in 
Boeing 737-500 SRM 53-10-01.
    (vii) Repair specified in Boeing 737-100/200 SRM 53-30-03, 
Figure 32.
    (2) For airplanes with any repair installed at the forward entry 
doorway or forward galley doorway, upper or lower hinge cutout, that 
does not meet the conditions specified in paragraph 3.A.10. of the 
Accomplishment Instructions of Boeing Service Bulletin 737-53A1200, 
Revision 2, dated September 12, 20012: Except as required by 
paragraph (l) of this AD, at the applicable times specified in 
paragraph 1.E., ``Compliance,'' of Boeing Service Bulletin 737-
53A1200, Revision 2, dated September 12, 2012, contact the Manager, 
Seattle ACO, FAA, for instructions using the procedures specified in 
paragraph (o) of this AD and do the actions required by the FAA.

(l) New Exception to Service Bulletin Specifications

    (1) Where Boeing Service Bulletin 737-53A1200, Revision 2, dated 
September 12, 2012, specifies a compliance time after the issue date 
of Boeing Service Bulletin 737-53A1200, Revision 1, dated July 7, 
2011, this AD requires compliance within the specified compliance 
time after the effective date of this AD.
    (2) Where Boeing Service Bulletin 737-53A1200, Revision 2, dated 
September 12, 2012, specifies to contact Boeing for further 
instructions, this AD requires contacting the Manager, Seattle 
Aircraft Certification Office (ACO), FAA, for instructions and doing 
the actions required by the FAA, using the procedures specified in 
paragraph (o) of this AD

(m) Exception for Group 5 Airplanes

    For Group 5 airplanes identified in Boeing Service Bulletin 737-
53A1200, Revision 2,

[[Page 22442]]

dated September 12, 2012: Before further flight, contact the 
Manager, Seattle ACO, FAA, for instructions using the procedures 
specified in paragraph (o) of this AD and do the actions required by 
the FAA.

(n) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraphs (j) and (k) of this AD, if those actions were performed 
before the effective date of this AD using Boeing Alert Service 
Bulletin 737-53A1200, Revision 1, dated July 7, 2011, which is not 
incorporated by reference in this AD.

(o) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Seattle ACO, FAA, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. In accordance with 14 CFR 39.19, send your request to your 
principal inspector or local Flight Standards District Office, as 
appropriate. If sending information directly to the manager of the 
ACO, send it to the attention of the person identified in the 
Related Information section of this AD. Information may be emailed 
to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, Seattle ACO to make 
those findings. For a repair method to be approved, the repair must 
meet the certification basis of the airplane and the approval must 
specifically refer to this AD.
    (4) AMOCs approved previously in accordance with paragraphs (f) 
and (i) of AD 2008-11-04, Amendment 39-15526 (73 FR 29421, May 21, 
2008), are approved as AMOCs for the corresponding provisions of 
paragraphs (g) and (i) of this AD.

(p) Related Information

    (1) For more information about this AD, contact Alan Pohl, 
Aerospace Engineer, Airframe Branch, ANM-120S, Seattle Aircraft 
Certification Office (ACO), FAA, 1601 Lind Avenue SW., Renton, WA 
98057-3356; phone: 425-917-6450; fax: 425-917-6590; email: 
[email protected].
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P. O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; phone: 206-544-
5000, extension 1; fax: 206-766-5680; Internet: https://www.myboeingfleet.com. You may review copies of the referenced 
service information at the FAA, Transport Airplane Directorate, 1601 
Lind Avenue SW., Renton, WA. For information on the availability of 
this material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on April 4, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-08908 Filed 4-15-13; 8:45 am]
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