[Federal Register Volume 74, Number 158 (Tuesday, August 18, 2009)]
[Rules and Regulations]
[Pages 41607-41611]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E9-19180]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1143; Directorate Identifier 2008-NM-136-AD; 
Amendment 39-15990; AD 2009-16-07]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 737-600, -700, -700C, -
800, and -900 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD), which applies to certain Boeing Model 737-600, -700, -700C, -800, 
and -900 series airplanes. That AD currently requires replacing 
brackets that hold the P5 panel to the airplane structure, the standby 
compass bracket assembly, the generator drive and standby power module, 
and the air conditioning module, as applicable. The existing AD also 
currently requires, among other actions, inspecting for wire length and 
for damage of the connectors and the wire bundles, and doing applicable 
corrective actions if necessary. This new AD requires an additional 
operational test of the P5-14 panel. This AD results from a report of 
an electrical burning smell in the flight compartment. We are issuing 
this AD to prevent wire bundles from contacting the overhead dripshield 
panel and modules in the P5 overhead panel, which could result in 
electrical arcing and shorting of the electrical connector and 
consequent loss of several critical systems essential for safe flight; 
and to ensure proper operation of the passenger oxygen system. If an 
improperly functioning passenger oxygen system goes undetected, the 
passenger oxygen mask could fail to deploy and result in possible 
incapacitation of passengers during a depressurization event.

DATES: This AD becomes effective September 22, 2009.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of September 22, 
2009.
    On June 22, 2006 (71 FR 28766, May 18, 2006), the Director of the 
Federal Register approved the incorporation by reference of certain 
other publications listed in the AD.

ADDRESSES: For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-
544-5000, extension 1; fax 206-766-5680; e-mail <a href="/cdn-cgi/l/email-protection#3c5159125e53595f53517c5e535955525b125f5351"><span class="__cf_email__" data-cfemail="dbb6bef5b9b4beb8b4b69bb9b4beb2b5bcf5b8b4b6">[email protected]</span></a>; 
Internet https://www.myboeingfleet.com.

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 AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (telephone 800-647-5527) is the Document 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: Binh Tran, Systems and Equipment 
Branch, ANM-130S, FAA, Seattle Aircraft Certification Office, 1601 Lind 
Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6485; 
fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that supersedes AD 2006-10-17, amendment 
39-14601 (71 FR 28766, May 18, 2006). The existing AD applies to 
certain Boeing Model 737-600, -700, -700C, -800, and -900 series 
airplanes. That NPRM was published in the Federal Register on October 
31, 2008 (73 FR 64894). That NPRM proposed to continue to require 
replacing brackets that hold the P5 panel to the airplane structure, 
the standby compass bracket assembly, the generator drive and

[[Page 41608]]

standby power module, and the air conditioning module. That NPRM also 
proposed to continue to require, among other actions, inspecting for 
wire length and for damage of the connectors and the wire bundles and 
doing applicable corrective actions if necessary. That NPRM also 
proposed to require an additional operational test of the P5-14 panel.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments that have been 
received on the NPRM.

Request To Align AD Action With Related Service Bulletin

    One commenter, Boeing, requests that the NPRM wording for paragraph 
(f)(4) be revised to align with Boeing Service Bulletin 737-24A1141, 
Revision 3, dated February 20, 2008. Boeing states that the current 
wording in the NPRM indicates that the standby compass bracket assembly 
must be replaced with a new assembly. Boeing states that Boeing Service 
Bulletin 737-24A1141, Revision 3, dated February 20, 2008, states that 
the standby compass bracket assembly need not be replaced for all 
groups of airplanes. Boeing Service Bulletin 737-24A1141, Revision 3, 
dated February 20, 2008, also states to replace the standby compass 
bracket if necessary.
    We agree that clarification may be necessary. Paragraph (f)(4) is a 
restatement of actions required by AD 2006-10-17, and is retained in 
this supersedure. Paragraph (f) of this AD states that the corrective 
actions (including replacing the standby compass bracket assembly as 
required by paragraph (f)(4) of this AD) must be done, as applicable. 
In addition, we note that a new requirement of this AD, paragraph (i) 
of this AD, requires that after the effective date of this AD, only 
Revision 3 of Boeing Service Bulletin 737-24A1141, dated February 20, 
2008, be used to do all applicable actions. We have not made any 
changes to the AD in this regard.

Request To Clarify Terminology

    One commenter, the Air Transport Association (ATA), on behalf of 
its member Delta Airlines, requests that the terminology in Boeing 
Service Bulletin 737-24A1141 be clarified. In its comment, Delta states 
that it believes that Boeing Service Bulletin 737-24A1141 contains 
material that is vague in nature, which would leave information subject 
to interpretation.
    Delta states that Boeing Service Bulletin 737-24A1141 includes 
figures that contain statements such as, ``Some airplanes may have 
different wires, panels or connectors'' (e.g., in Figures 6-11 and 94 
of the service bulletin). Delta is concerned that statements such as 
these, when dealing with compliance situations in which many different 
individuals are left to determine the intent and method prescribed by 
such instructions, can lead to problems determining the state of 
compliance of aircraft that have had work accomplished per the required 
accomplishment instructions. In the past, this has led to the grounding 
of airplanes at significant expense to the airlines, while confusion 
over the interpretation of said instructions is determined and 
resolved. Therefore, Delta believes that either Boeing Service Bulletin 
737-24A1141 should be revised to clarify the meaning of vague terms 
(e.g., ``typical''), or the AD should include notes to accomplish the 
same intent.
    Delta states that failure to clarify the vague terms will likely 
lead to the same compliance issues that operators previously 
experienced with the B737 Rudder System Enhancement Program (AD 2007-
03-07, Amendment 39-14918, 72 FR 4625, February 1, 2007) and MD88 
auxiliary hydraulic pump feeder wire inspection/modification (AD 2006-
15-15, Amendment 39-14696, 71 FR 43035, July 31, 2006).
    We find that clarification of certain material contained in Boeing 
Service Bulletin 737-24A1141, Revision 3, dated February 20, 2008, is 
necessary. We discussed the material referenced by the commenter as 
``vague'' with Boeing to clarify the intended meaning.
    Boeing noted that Boeing Service Bulletin 737-24A1141, Revision 3, 
dated February 20, 2008, was initially released in January 2004, and 
since then has been revised three times (December 2004, December 2005, 
and February 2008) to update and correct information. As specified in 
Boeing Service Bulletin 737-24A1141, Revision 3, dated February 20, 
2008, required actions include: replacing brackets to lower the P5 
overhead panel to increase the space between the wire bundles and the 
dripshield panel and modules; inspecting to determine if unwanted wire 
length or damage exists; retying the wire bundle or reterminating the 
wire bundle into the connector to eliminate the unwanted wire; and 
repairing damaged wire and using teflon tape, nylon sheet, and lacing 
tape to give greater protection to the wire bundles. Also, depending on 
airplane configuration, the service bulletin specifies replacing the 
standby compass bracket assembly with a new assembly, and replacing the 
stud assemblies with new assemblies.
    Boeing clarified that the P5 overhead panel varies from customer to 
customer, as indicated in the 98 figures contained in Boeing Service 
Bulletin 737-24A1141, Revision 3, dated February 20, 2008. Boeing 
explains that the phrase questioned by the commenter--i.e., ``Some 
airplanes may have different wires, panels or connectors''--was used in 
the illustrations in the figures to indicate that the configuration on 
any given customer's airplane may be different from that shown in the 
illustrations. The illustrations simply provide examples of various 
configurations an operator might find; therefore, the information 
provided in the illustrations of the figures is for reference. Boeing 
explained further that the word ``typical'' is intended to represent a 
configuration that is in more than one location within an illustration. 
Additionally, while accomplishment of the steps specified in the tables 
of the figures is required, the illustrations are simply examples of 
the wiring configuration.
    In addition, we find that the word ``unwanted'' requires 
clarification. That term is used in various locations in the service 
bulletin in conjunction with wire length conditions--e.g., paragraph 
3.B.9. of the Accomplishment Instructions states to ``Inspect the 
connectors and the wire bundles in the rear, P5 aft panel to determine 
if unwanted wire length exists in Group 1-22 airplanes. See Figure 6.'' 
We clarify that the General Information section of the Accomplishment 
Instructions of Boeing Service Bulletin 737-24A1141, Revision 3, dated 
February 20, 2008, references Boeing Standard Wiring Practices Manual 
(SWPM) 20-10-11 for wire installation procedures, including defining 
the amount of slack and making sure that all wire slack is securely 
tied into the parent harness or clamped. Additionally, it should be 
noted that tables found in certain figures of Boeing Service Bulletin 
737-24A1141, Revision 3, dated February 20, 2008 (Figure 6, for 
example), refer operators to the SWPM for general conditions for wire 
installation.
    We have revised this final rule to include new Note 2 and Note 3 to 
clarify the meaning of the terminology discussed previously.

[[Page 41609]]

Updated Contact Information for Alternative Methods of Compliance 
(AMOCs)

    We have updated the contact information for paragraph (k) 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 
the AD with the change described previously. We also determined that 
this change will not increase the economic burden on any operator or 
increase the scope of the AD.

Costs of Compliance

    There are about 740 airplanes of the affected design in the 
worldwide fleet. This AD affects about 333 airplanes of U.S. registry.
    For all airplanes, the required inspection, replacements, and 
wiring change that are required by AD 2006-10-17 and retained in this 
AD take about 16 or 18 work hours per airplane (depending on airplane 
configuration), at an average labor rate of $80 per work hour. Required 
parts cost about $10,231 or $11,139 per airplane (depending on the 
kit). Based on these figures, the estimated cost of the replacements 
and inspections required by this AD for U.S. operators is between 
$3,833,163 and $4,188,807, or between $11,511 and $12,579 per airplane.
    For certain airplanes, the modification of the generator drive and 
standby power module assembly that is required by AD 2006-10-17 and 
retained in this AD takes about 2 work hours per airplane, at an 
average labor rate of $80 per work hour. The airplane manufacturer 
states that it will supply required parts to operators at no cost. 
Based on these figures, the estimated cost of this modification 
required by this AD is $160 per airplane.
    For certain other airplanes, the modification of the air 
conditioning module assembly that is required by AD 2006-10-17 and 
retained in this AD takes about 1 work hour per airplane, at an average 
labor rate of $80 per work hour. The airplane manufacturer states that 
it will supply required parts to operators at no cost. Based on these 
figures, the estimated cost of this modification required by this AD is 
$80 per airplane.
    For certain airplanes, the new action takes about 21 or 23 work 
hours per airplane depending on the airplane configuration, at an 
average labor rate of $80 per work hour. Based on these figures, the 
estimated cost of the new actions required by this AD for U.S. 
operators is $1,680 or $1,840 per airplane, depending on the airplane 
configuration.

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); and
    (3) 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
removing amendment 39-14601 (71 FR 28766, May 18, 2006) and by adding 
the following new airworthiness directive (AD):

2009-16-07 Boeing: Amendment 39-15990. Docket No. FAA-2008-1143; 
Directorate Identifier 2008-NM-136-AD.

Effective Date

    (a) This AD becomes effective September 22, 2009.

Affected ADs

    (b) This AD supersedes AD 2006-10-17.

Applicability

    (c) This AD applies to Boeing Model 737-600, -700, -700C, -800, 
and -900 series airplanes, certificated in any category; as 
identified in Boeing Service Bulletin 737-24A1141, Revision 3, dated 
February 20, 2008.

Unsafe Condition

    (d) This AD results from a report of an electrical burning smell 
in the flight compartment. We are issuing this AD to prevent wire 
bundles from contacting the overhead dripshield panel and modules in 
the P5 overhead panel, which could result in electrical arcing and 
shorting of the electrical connector and consequent loss of several 
critical systems essential for safe flight; and to ensure proper 
operation of the passenger oxygen system. If an improperly 
functioning passenger oxygen system goes undetected, the passenger 
oxygen mask could fail to deploy and result in possible 
incapacitation of passengers during a depressurization event.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Requirements of AD 2006-10-17

Inspection/Replacements/Wiring Changes/Corrective Actions

    (f) Within 36 months after June 22, 2006 (the effective date of 
AD 2006-10-17), do the applicable actions in paragraphs (f)(1) 
through (f)(5) of this AD by accomplishing all the applicable 
actions specified in the Accomplishment Instructions of Boeing 
Service Bulletin 737-24A1141, Revision 2, dated December 1, 2005, 
except as provided by paragraph (i) of this AD. Any applicable 
corrective actions must be done before further flight.
    (1) Replace the five brackets that hold the P5 panel to the 
airplane structure with new brackets;

[[Page 41610]]

    (2) Do a general visual inspection for wire length and damage of 
the connectors and the wire bundles, and applicable corrective 
actions;
    (3) Make wiring changes;
    (4) Replace the standby compass bracket assembly with a new 
assembly; and
    (5) Replace the stud assemblies with new assemblies.

    Note 1:  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.''

    (g) Actions done before June 22, 2006, in accordance with Boeing 
Alert Service Bulletin 737-24A1141, Revision 1, dated December 23, 
2004, are acceptable for compliance with the requirements of 
paragraph (f) of this AD.

Concurrent Requirements

    (h) Before or concurrently with the requirements of paragraph 
(f) of this AD, do the applicable action specified in Table 1 of 
this AD.

                    Table 1--Concurrent Requirements
------------------------------------------------------------------------
 For airplanes identified in
   Boeing component Service                      Action
          Bulletin--
------------------------------------------------------------------------
(1) 233A3205-24-01, dated      Modify the generator drive and standby
 July 26, 2001.                 power module assembly in accordance with
                                the Accomplishment Instructions of
                                Boeing Component Service Bulletin
                                233A3205-24-01, dated July 26, 2001.
(2) 69-37319-21-02, Revision   Modify the air conditioning module
 1, dated August 30, 2001.      assembly in accordance with the
                                Accomplishment Instructions of Boeing
                                Component Service Bulletin 69[dash]37319-
                                21-02, Revision 1, dated August 30,
                                2001.
------------------------------------------------------------------------

New Actions Required by This AD

New Service Bulletin Revision

    (i) As of the effective date of this AD, use only the 
Accomplishment Instructions of Boeing Service Bulletin 737-24A1141, 
Revision 3, dated February 20, 2008, to do all the applicable 
actions required by paragraph (f) of this AD.

    Note 2: Accomplishment of the steps specified in the tables of 
the figures of Boeing Service Bulletin 737-24A1141, Revision 3, 
dated February 20, 2008, is required. Due to the variability of 
airplane configurations, the illustrations in the figures are 
provided as examples.


    Note 3:  Boeing Service Bulletin 737-24A1141, Revision 3, dated 
February 20, 2008, refers to ``unwanted'' wire length. ``Unwanted'' 
wire length is any wire length that does not meet the wire length 
requirements specified in the Standard Wiring Practices Manual 
(SWPM).

Additional Operational Test

    (j) For airplanes on which the actions required by paragraph (f) 
of this AD have been done in accordance with Boeing Service Bulletin 
737-24A1141, Revision 2, dated December 1, 2005, before the 
effective date of this AD: Within 12 months after the effective date 
of this AD, do an operational test of the P5-14 panel in accordance 
with paragraphs 3.B.92. and 3.B.93., as applicable, of the 
Accomplishment Instructions of Boeing Service Bulletin 737-24A1141, 
Revision 3, dated February 20, 2008.

Alternative Methods of Compliance (AMOCs)

    (k)(1) The Manager, Seattle Aircraft Certification Office, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. Send information to Attn: Binh 
Tran, Aerospace Engineer, Systems and Equipment Branch, ANM-130S, 
FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., 
Renton, Washington 98057-3356; telephone (425) 917-6485; fax (425) 
917-6590. Or, e-mail information to <a href="/cdn-cgi/l/email-protection#c6ffeb87888beb95a3a7b2b2aaa3eb878589eb878b8985eb94a3b7b3a3b5b2b586a0a7a7e8a1a9b0"><span class="__cf_email__" data-cfemail="526b7f131c1f7f01373326263e377f13111d7f131f1d117f0037232737212621123433337c353d24">[email protected]</span></a>.
    (2) To request a different method of compliance or a different 
compliance time for this AD, follow the procedures in 14 CFR 39.19. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards District Office. 
The AMOC approval letter must specifically reference this AD.
    (3) AMOCs approved previously in accordance with AD 2006-10-17 
are approved as AMOCs for the corresponding provisions of this AD.

Material Incorporated by Reference

    (l) You must use the service information contained in Table 2 of 
this AD to do the actions required by this AD, unless the AD 
specifies otherwise.

                                 Table 2--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
                 Document                         Revision level                           Date
----------------------------------------------------------------------------------------------------------------
Boeing Component Service Bulletin          Original....................  July 26, 2001.
 233A3205-24-01.
Boeing Component Service Bulletin 69-      1...........................  August 30, 2001.
 37319-21-02.
Boeing Service Bulletin 737-24A1141......  3...........................  February 20, 2008.
----------------------------------------------------------------------------------------------------------------

     (1) The Director of the Federal Register approved the 
incorporation by reference of the service information contained in 
Table 3 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51.

                                 Table 3--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
                 Document                         Revision level                           Date
----------------------------------------------------------------------------------------------------------------
Boeing Service Bulletin 737-24A1141......  3...........................  February 20, 2008.
----------------------------------------------------------------------------------------------------------------


[[Page 41611]]

     (2) The Director of the Federal Register previously approved 
the incorporation by reference of the service information contained 
in Table 4 of this AD on June 22, 2006 (71 FR 28766, May 18, 2006).

                             Table 4--Material Previously Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
                 Document                         Revision level                           Date
----------------------------------------------------------------------------------------------------------------
Boeing Component Service Bulletin          Original....................  July 26, 2001.
 233A3205-24-01.
Boeing Component Service Bulletin 69-      1...........................  August 30, 2001.
 37319-21-02.
----------------------------------------------------------------------------------------------------------------

    (3) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P. O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 
206-544-5000, extension 1; fax 206-766-5680; e-mail 
<a href="/cdn-cgi/l/email-protection#066b632864696365696b466469636f68612865696b"><span class="__cf_email__" data-cfemail="aec3cb80ccc1cbcdc1c3eeccc1cbc7c0c980cdc1c3">[email protected]</span></a>; Internet https://www.myboeingfleet.com.
    (4) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221 or 425-227-1152.
    (5) You may also review copies of the 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/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on August 7, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-19180 Filed 8-17-09; 8:45 am]
BILLING CODE 4910-13-P


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