AD 2010-15-08

[Federal Register Volume 75, Number 143 (Tuesday, July 27, 2010)]
[Rules and Regulations]
[Pages 43803-43807]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2010-18009]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0173; Directorate Identifier 2009-NM-076-AD; 
Amendment 39-16374; AD 2010-15-08]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Model 737-100, -200, 
-200C, -300, -400, and -500 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 all Model 737-100, -200, -200C, -300, -400, and 
-500 series airplanes. That AD currently requires repetitive 
inspections to find cracks, fractures, or corrosion of each carriage 
spindle of the left and right outboard mid-flaps, and corrective action 
if necessary. That AD also currently requires repetitive gap checks of 
the inboard and outboard carriage of the outboard mid-flaps to detect 
fractured carriage spindles, and corrective actions if necessary. This 
new AD requires any new or serviceable carriage spindle installed per 
the requirements of the existing AD to meet minimum allowable diameter 
measurements taken at three locations. This AD also requires new 
repetitive inspections, measurements, and overhaul of the carriage 
spindles, and applicable corrective actions. In addition, this AD 
requires replacing any carriage spindle when it has reached its maximum 
life limit. This AD results from reports of fractures that resulted 
from stress corrosion and pitting along the length of the spindle and 
spindle diameter, and additional reports of corrosion on the outboard 
flap carriage spindles. We are issuing this AD to detect and correct 
cracked, corroded, or fractured carriage spindles, and to prevent 
severe flap asymmetry, which could result in reduced control or loss of 
controllability of the airplane.

DATES: This AD becomes effective August 31, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of August 31, 
2010.
    On December 4, 2003 (68 FR 67027, December 1, 2003), the Director 
of the Federal Register approved the incorporation by reference of a 
certain other publication 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#f09d95de929f95939f9db0929f95999e97de939f9d"><span class="__cf_email__" data-cfemail="1479713a767b71777b7954767b717d7a733a777b79">[email&#160;protected]</span></a>; 
Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a>; 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: Nancy Marsh, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
917-6440; 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 2003-24-08, Amendment 
39-13377 (68 FR 67027, December 1, 2003). The existing AD applies to 
all Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. 
That NPRM was published in the Federal Register on March 1, 2010 (75 FR 
9137). That NPRM proposed to continue to require repetitive gap checks 
of the inboard and outboard carriage of the outboard mid-flaps to 
detect fractured carriage spindles, and corrective actions if 
necessary, and continue to require repetitive inspections to find 
cracks, factures, or corrosion of each carriage spindle of the left and 
right outboard mid-flaps. That NPRM also proposed to require any new or 
serviceable carriage spindle installed per the requirements of the 
existing AD to meet minimum allowable diameter measurements taken at 
three locations. That NPRM proposed to require new repetitive 
inspections, measurements, and overhaul of the carriage spindles, and 
applicable corrective actions. In addition, that NPRM also proposed to 
require replacing any carriage spindle

[[Page 43804]]

when it has reached its maximum life limit.

Actions Since Original NPRM Was Issued

    Since we issued the original NPRM, there has been an in-service 
event of a dual fracture of the outboard flap carriages. This event is 
currently under investigation. As a result, we consider this AD to be 
interim action. If final action is later identified, we might consider 
further rulemaking then.

Explanation of Changes to AD

    We have added paragraph (t)(4) to this final rule to provide credit 
for actions done in accordance with previously issued AMOCs for 
individual repairs. In paragraph (m) of this AD, we have also 
referenced the most current issue of the Boeing (737) Standard Overhaul 
Practices Manual for actions done as of the effective date of this AD.

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.

Support for the NPRM

    Boeing supports the intent of the NPRM.

Request for Stricter Inspection and Overhaul Limits in Lieu of Life 
Limits

    Safair states that it has experienced only one flap carriage 
spindle failure before AD 2003-24-08 was issued. Safair states that its 
main concern is scrapping serviceable carriages in order to enforce the 
life limits on the flap carriages. Safair states that stricter 
inspections and overhaul requirements would ensure that stress and 
pitting corrosion are detected and corrected, which would avoid 
failures and would extend the life of the flap carriages.
    We do not agree that substituting stricter inspection and overhaul 
limits for life limits would address the unsafe condition. Since AD 
2003-24-08 was issued, we have received many additional reports of 
carriage spindle fractures, including fractures caused by fatigue. 
Because of the difficulty in detecting small cracks and the rapid crack 
growth in these parts, in combination with the concerns with reduced 
fatigue life of reworked and overhauled parts, the most effective way 
to maintain the continued operational safety of the fleet is to mandate 
life limits. We have not changed the AD in regard to this issue.

Request for Clarification of Requirements to Remove Flap Carriage

    KLM requests clarification concerning the requirements to remove 
the carriage spindle in order to perform a detailed inspection for 
corrosion, pitting, cracking, and measurement of some minimal allowable 
spindle diameters. KLM points out that the times specified for this 
action are the same as for the initial gap check and the nondestructive 
test for new carriage spindles. KLM asks whether the removal of the 
carriage spindle is required at 12,000 flight cycles, if the initial or 
repetitive gap check and the non-destructive test (NDT) at the same 
time are still useful. KLM further states that carriage spindles that 
receive a thorough detailed inspection and have been found to be 
serviceable do not require a gap check or an NDT inspection at the 
times specified in the 12,000- to 20,000-flight-cycle range as 
specified in Table 1 and Table 2 of Boeing Alert Service Bulletin 737-
57A1277, Revision 1, dated November 25, 2003. KLM states that the gap 
checks and NDTs are still required, although at a different time 
interval after completing the requirements of paragraph (o) of the 
NPRM.
    We agree that clarification might be necessary. Paragraph (o) of 
this final rule requires the overhaul to be performed on the new 
carriage spindle before the accumulation of 12,000 flight cycles. 
Therefore, the new carriage spindle should not accumulate more than 
11,999 flight cycles before being overhauled in order to comply with 
this requirement. Paragraph (g) of this AD refers to Boeing Alert 
Service Bulletin 737-57A1277, Revision 1, dated November 25, 2003, for 
the compliance times for the gap checks and NDT inspections. Boeing 
Alert Service Bulletin 737-57A1277, Revision 1, dated November 25, 
2003, states that the gap check and NDT inspections are not required 
for a new flap carriage spindle that has accumulated fewer than 12,000 
flight cycles without being overhauled.
    Boeing Alert Service Bulletin 737-57A1277, Revision 1, dated 
November 25, 2003, requires relatively stringent gap checks and NDT 
inspections for flap carriage spindles that have accumulated 12,000 or 
more flight cycles on them since being overhauled. This requirement 
should become obsolete as this AD requires that all spindles be 
overhauled before accumulating 12,000 flight cycles since new or 
overhauled.
    We have not changed the AD in regard to this issue.

Conclusion

    We have carefully reviewed the available data, including the 
comments that have been received, and determined that air safety and 
the public interest require adopting the AD with the changes described 
previously. We have determined that these changes will neither increase 
the economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    There are about 2,852 airplanes of the affected design in the 
worldwide fleet. The following table provides the estimated costs for 
U.S. operators to comply with this AD.

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                                                     Number of
                                                    Average                                            U.S.-
               Action                 Work hours   labor rate     Parts        Cost per airplane     registered                 Fleet cost
                                                    per hour                                         airplanes
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspections (required by AD 2003-24-          12          $85         None  $1,020 per inspection           652  $665,040 per inspection cycle.
 08).                                                                        cycle.
Inspections and measurements (new              2           85         None  $170 per inspection             652  $110,840 per inspection and measurement
 actions).                                                                   and measurement cycle.               cycle.
Overhauls (new actions)............           16           85   \1\ 28,000  $29,360 per overhaul            652  $19,142,720 per overhaul cycle.
                                                                             cycle.
Replacements (new actions).........           16           85   \2\ 60,000  $61,360 per                     652  $40,006,720 per replacement cycle.
                                                                             replacement cycle....
--------------------------------------------------------------------------------------------------------------------------------------------------------
\1\ $7,000 per spindle; 4 spindles per airplane.
\2\ $15,000 per spindle; 4 spindles per airplane.


[[Page 43805]]

    The cost impact figures discussed above are based on assumptions 
that no operator has yet accomplished any of the actions required by 
this AD, and that no operator would accomplish those actions in the 
future if this AD were not adopted. However, we have been advised that 
the carriage spindles are already being overhauled and replaced on some 
affected airplanes. In addition, the replacement cycle is approximately 
every 20 years. Therefore, the future economic cost impact of this rule 
on U.S. operators is expected to be less than the cost impact figures 
indicated above.

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 39-13377 (68 FR 67027, December 1, 2003) and by 
adding the following new airworthiness directive (AD):

2010-15-08 The Boeing Company: Amendment 39-16374. Docket No. FAA-
2010-0173; Directorate Identifier 2010-NM-076-AD.

Effective Date

    (a) This AD becomes effective August 31, 2010.

Affected ADs

    (b) This AD supersedes AD 2003-24-08, Amendment 39-13377.

Applicability

    (c) This AD applies to all The Boeing Company Model 737-100, -
200, -200C, -300, -400, and -500 series airplanes, certificated in 
any category.

Subject

    (d) Air Transport Association (ATA) of America Code 57: Wings.

Unsafe Condition

    (e) This AD results from a report indicating that the inboard 
and outboard carriage spindles were fractured on the right outboard 
flap during approach to landing. We are issuing this AD to detect 
and correct cracked, corroded, or fractured carriage spindles and to 
prevent severe flap asymmetry, which could result in reduced control 
or loss of controllability of the airplane.

Compliance

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

RESTATEMENT OF CERTAIN REQUIREMENTS OF AD 2003-24-08, WITH UPDATED 
SERVICE INFORMATION

Compliance Times

    (g) The tables in paragraph 1.E., ``Compliance'' of Boeing Alert 
Service Bulletin 737-57A1277, Revision 1, dated November 25, 2003, 
specify the compliance times for paragraphs (g) through (k) of this 
AD. For carriage spindles that have accumulated the number of flight 
cycles or years in service specified in the ``Threshold'' column of 
the tables, accomplish the gap check and nondestructive test (NDT) 
and general visual inspections specified in paragraphs (h) and (j) 
of this AD within the corresponding interval after December 4, 2003 
(the effective date AD 2003-24-08), as specified in the ``Interval'' 
column. Repeat the gap check and NDT and general visual inspections 
at the same intervals, except:
    (1) The gap check does not have to be done at the same time as 
an NDT inspection; after doing an NDT inspection, the interval for 
doing the next gap check can be measured from the NDT inspection; 
and
    (2) As carriage spindles gain flight cycles or years in service 
and move from one category in the ``Threshold'' column to another, 
they are subject to the repetitive inspection intervals 
corresponding to the new threshold category.

Work Package 2: Gap Check

    (h) Perform a gap check of the inboard and outboard carriage of 
the left and right outboard mid-flaps to determine if there is a 
positive indication of a severed carriage spindle, in accordance 
with Work Package 2 of paragraph 3.B., ``Work Instructions'' of 
Boeing Alert Service Bulletin 737-57A1277, Revision 1, dated 
November 25, 2003.

Work Package 2: Corrective Actions

    (i) If there is a positive indication of a severed carriage 
spindle during the gap check required by paragraph (h) of this AD, 
before further flight, remove the carriage spindle and install a new 
or serviceable carriage spindle in accordance with the ``Work 
Instructions'' of Boeing Alert Service Bulletin 737-57A1277, 
Revision 1, dated November 25, 2003; or Boeing Alert Service 
Bulletin 737-57A1218, Revision 5, dated February 9, 2009. If, as a 
result of the detailed inspection described in paragraph 4.b. of 
Work Package 2 of Boeing Alert Service Bulletin 737-57A1277, 
Revision 1, dated November 25, 2003, a carriage spindle is found not 
to be severed and no corrosion and no cracking is present, it can be 
reinstalled on the mid-flap in accordance with Boeing Alert Service 
Bulletin 737-57A1277, Revision 1, dated November 25, 2003; or Boeing 
Alert Service Bulletin 737-57A1218, Revision 5, dated February 9, 
2009. After the effective date of this AD, use only Boeing Alert 
Service Bulletin 737-57A1218, Revision 5, dated February 9, 2009.

Work Package 1: Inspections

    (j) Perform a NDT inspection and general visual inspection for 
each carriage spindle of the left and right outboard mid-flaps to 
detect cracks, corrosion, or severed carriage spindles, in 
accordance with the ``Work Instructions'' of Boeing Alert Service 
Bulletin 737-57A1277, Revision 1, dated November 25, 2003.

Work Package 1: Corrective Actions

    (k) If any corroded, cracked, or severed carriage spindle is 
found during any inspection required by paragraph (j) of this AD, 
before further flight, remove the carriage

[[Page 43806]]

spindle and install a new or serviceable carriage spindle in 
accordance with the ``Work Instructions'' of Boeing Alert Service 
Bulletin 737-57A1277, Revision 1, dated November 25, 2003; or Boeing 
Alert Service Bulletin 737-57A1218, Revision 5, dated February 9, 
2009. After the effective date of this AD, use only Boeing Alert 
Service Bulletin 737-57A1218, Revision 5, dated February 9, 2009.

Parts Installation

    (l) Except as provided in paragraph (i) of this AD: As of 
December 4, 2003, no person may install on any airplane a carriage 
spindle that has been removed as required by paragraph (i) or (k) of 
this AD, unless it has been overhauled in accordance with the ``Work 
Instructions'' of Boeing Alert Service Bulletin 737-57A1277, 
Revision 1, dated November 25, 2003; or Boeing Alert Service 
Bulletin 737-57A1218, Revision 5, dated February 9, 2009. After the 
effective date of this AD, use only Boeing Alert Service Bulletin 
737-57A1218, Revision 5, dated February 9, 2009. To be eligible for 
installation under this paragraph, the carriage spindle must have 
been overhauled in accordance with the requirements of paragraph (m) 
of this AD.
    (m) During accomplishment of any overhaul specified in paragraph 
(l) of this AD, use the procedures specified in paragraphs (m)(1) 
and (m)(2) of this AD during application of the nickel plating to 
the carriage spindle in addition to those specified in Chapter 20-
42-09, Electrodeposited Nickel Plating, of the Boeing (737) Standard 
Overhaul Practices Manual. As of the effective date of this AD, use 
only Chapter 20-42-09, Electrodeposited Nickel Plating, of the 
Boeing (737) Standard Overhaul Practices Manual, Revision 25, dated 
July 1, 2009.
    (1) The maximum deposition rate of the nickel plating in any one 
plating/baking cycle must not exceed 0.002-inches-per-hour.
    (2) Begin the hydrogen embrittlement relief bake within 10 hours 
after application of the plating, or less than 24 hours after the 
current was first applied to the part, whichever is first.

Exception to Reporting Recommendations in Certain Service Bulletins

    (n) Although Boeing Alert Service Bulletin 737-57A1277, Revision 
1, dated November 25, 2003, recommends that operators report 
inspection findings to the manufacturer, this AD does not contain 
such a reporting requirement.

NEW ACTIONS REQUIRED BY THIS AD

Inspections, Measurements, and Overhauls of the Carriage Spindle

    (o) At the applicable times specified in paragraph (o)(1) or 
(o)(2) of this AD: Do the detailed inspection for corrosion, 
pitting, and cracking of the carriage spindle, the magnetic particle 
inspection for cracking of the carriage spindle, measurements of the 
spindle to determine if it meets the allowable minimum diameter, and 
overhauls, and applicable corrective actions by accomplishing all 
the applicable actions specified in the Accomplishment Instructions 
of Boeing Alert Service Bulletin 737-57A1218, Revision 5, dated 
February 9, 2009. The applicable corrective actions must be done 
before further flight. Repeat these actions thereafter at intervals 
not to exceed 12,000 flight cycles on the carriage spindle or 8 
years, whichever comes first.
    (1) For Model 737-100, -200, -200C series airplanes, at the 
later of the times specified in paragraph (o)(1)(i) or (o)(1)(ii) of 
this AD:
    (i) Before the accumulation of 12,000 total flight cycles on the 
carriage spindle since new or overhauled, or within 8 years after 
the installation of the new or overhauled part, whichever comes 
first.
    (ii) Within 1 year after the effective date of this AD.
    (2) For Model -300, -400, and -500 series airplanes, at the 
later of the times specified in paragraph (o)(2)(i) or (o)(2)(ii) of 
this AD:
    (i) Before the accumulation of 12,000 total flight cycles on the 
carriage spindle since new or overhauled, or within 8 years after 
the installation of the new or overhauled part, whichever comes 
first.
    (ii) Within 2 years after the effective date of this AD.

Replacement of the Carriage Spindle

    (p) For Model 737-100, -200, -200C series airplanes: Replace the 
carriage spindle with a new or documented (for which the service 
life, in total flight cycles, is known) carriage spindle, in 
accordance with Boeing Alert Service Bulletin 737-57A1218, Revision 
5, dated February 9, 2009, at the later of the times specified in 
paragraphs (p)(1) and (p)(2) of this AD, except as required by 
paragraph (r) of this AD. Overhauling the carriage spindles does not 
zero-out the flight cycles. Total flight cycles accumulate since 
new.
    (1) Before the accumulation of 48,000 total flight cycles on the 
new or overhauled carriage.
    (2) Within three years or 7,500 flight cycles after the 
effective date of this AD, whichever occurs first.
    (q) For Model 737-300, -400, and -500 series airplanes: Replace 
the carriage spindle with a new or documented (for which the service 
life, in flight cycles, is known) carriage spindle, in accordance 
with Boeing Alert Service Bulletin 737-57A1218, Revision 5, dated 
February 9, 2009, at the later of the times specified in paragraphs 
(q)(1) and (q)(2) of this AD, except as required by paragraph (r) of 
this AD. Overhauling the carriage spindles does not zero-out the 
flight cycles. Total flight cycles accumulate since new.
    (1) Before the accumulation of 48,000 total flight cycles on the 
new or overhauled carriage.
    (2) Within six years or 15,000 flight cycles after the effective 
date of this AD, whichever occurs first.
    (r) For airplanes with an undocumented carriage: Do the 
applicable actions specified in paragraph (p) or (q) of this AD at 
the applicable time specified in paragraph (r)(1) or (r)(2) of this 
AD.
    (1) For Model 737-100, -200, -200C series airplanes: Do the 
actions specified in paragraph (p) of this AD at the time specified 
in paragraph (p)(2) of this AD.
    (2) For Model -300, -400, and -500 series airplanes: Do the 
actions specified in paragraph (q) of this AD at the time specified 
in paragraph (q)(2) of this AD.

Repetitive Replacements of Carriage Spindle

    (s) For all airplanes: Repeat the replacement of the carriage 
spindle specified by paragraph (p) or (q) of this AD, as applicable, 
thereafter at intervals not to exceed 48,000 total flight cycles on 
the new or overhauled carriage spindle.

Alternative Methods of Compliance (AMOCs)

    (t)(1) The Manager, Seattle Aircraft Certification Office (ACO), 
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: Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM-120S, 
FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., 
Renton, Washington 98057-3356; telephone (425) 917-6440; fax (425) 
917-6590. Or, e-mail information to <a href="/cdn-cgi/l/email-protection#c3faee828d8eee90a6a2b7b7afa6ee82808cee828e8c80ee91a6b2b6a6b0b7b083a5a2a2eda4acb5"><span class="__cf_email__" data-cfemail="380115797675156b5d594c4c545d15797b77157975777b156a5d494d5d4b4c4b785e5959165f574e">[email&#160;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) 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 previously approved in accordance with AD 2003-24-08, 
Amendment 39-13377, for individual repairs are acceptable for 
compliance with the corresponding provisions of this AD. All other 
existing AMOCs are not acceptable.

Material Incorporated by Reference

    (u) You must use Boeing Alert Service Bulletin 737-57A1218, 
Revision 5, dated February 9, 2009; Boeing Alert Service Bulletin 
737-57A1277, Revision 1, dated November 25, 2003; and Chapter 20-42-
09, Electrodeposited Nickel Plating, of the Boeing (737) Standard 
Overhaul Practices Manual, Revision 25, dated July 1, 2009, to do 
the actions required by this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of Boeing Alert Service Bulletin 737-
57A1218, Revision 5, dated February 9, 2009; and Chapter 20-42-09, 
Electrodeposited Nickel Plating, of the Boeing (737) Standard 
Overhaul Practices Manual, Revision 25, dated July 1, 2009; under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) The Director of the Federal Register previously approved the 
incorporation by

[[Page 43807]]

reference of Boeing Alert Service Bulletin 737-57A1277, Revision 1, 
dated November 25, 2003, on December 4, 2003 (68 FR 67027, December 
1, 2003).
    (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#f19c94df939e94929e9cb1939e94989f96df929e9c"><span class="__cf_email__" data-cfemail="87eae2a9e5e8e2e4e8eac7e5e8e2eee9e0a9e4e8ea">[email&#160;protected]</span></a>; Internet <a href="https://www.myboeingfleet.com">https://www.myboeingfleet.com</a>.
    (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.
    (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: <a href="http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html">http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html</a>.

    Issued in Renton, Washington, on July 14, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-18009 Filed 7-26-10; 8:45 am]
BILLING CODE 4910-13-P