Document ID: FAA-2008-1118-0008
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Boeing Co. Model 737-600, -700, -700C, -800,  -900, and -900ER Series Airplanes
Posted Date: 2011-01-11T05:00Z

[Federal Register: January 11, 2011 (Volume 76, Number 7)]
[Proposed Rules]               
[Page 1552-1556]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr11ja11-19]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1118; Directorate Identifier 2007-NM-318-AD]
RIN 2120-AA64

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

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

ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

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SUMMARY: The FAA is revising an earlier NPRM for an airworthiness 
directive (AD) that applies to all Boeing Model 737-600, -700, -700C, -
800, and -900 series airplanes. The original NPRM would have superseded 
an existing AD that currently requires reviewing the airplane 
maintenance records to determine whether an engine has been removed 
from the airplane since the airplane was manufactured. For airplanes on 
which an engine has been removed, the existing AD also requires an 
inspection of the aft engine mount to determine if the center link 
assembly is correctly installed, and follow-on actions if necessary. 
The original NPRM proposed to require the same actions for airplanes on 
which the engine has not been previously removed. The original NPRM 
resulted from reports indicating that operators found that the center 
link assembly for the aft engine mount was reversed on several 
airplanes that had not had an engine removed since delivery. This new 
action revises the original NPRM by expanding the applicability to 
include Model 737-900ER airplanes. We are proposing this supplemental 
NPRM to prevent increased structural loads on the aft engine mount, 
which could result in failure of the aft engine mount and consequent 
separation of the engine from the airplane.

ADDRESSES: We must receive comments on this supplemental NPRM by 
February 25, 2011.

DATES: You may send comments 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 proposed 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 me.boecom@boeing.com; 
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, Washington. 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 (telephone 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, Washington 98057-3356; telephone (425) 
917-6450; fax (425) 917-6590.

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-2008-1118; 
Directorate Identifier 2007-NM-318-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

    We proposed to amend part 39 of the Federal Aviation Regulations 
(14 CFR part 39) with a notice of proposed rulemaking (NPRM) for an AD 
(the ``original NPRM'') to supersede AD 2003-03-01, Amendment 39-13025 
(68 FR 4367, January 29, 2003). The original NPRM applied to all Model 
737-600, -700, -700C, -800, and -900 series airplanes. The original 
NPRM was published in the Federal Register on October 30, 2008 (73 FR 
64568). The original NPRM would have superseded an existing AD that 
currently requires reviewing the airplane maintenance records to 
determine whether an engine has been removed from the airplane since 
the airplane was manufactured. For airplanes on which an engine has 
been removed, the existing AD also requires an inspection of the aft 
engine mount to determine if the center link assembly is correctly 
installed, and follow-on actions if necessary. The original NPRM 
proposed to require the same actions for airplanes on which the engine 
has not been previously removed.

Actions Since Original NPRM Was Issued

    Since we issued the original NPRM, the manufacturer has informed us 
that Model 737-900ER airplanes should be included in the applicability 
of the supplemental NPRM. Model 737-900ER airplanes were not being 
produced in May 2004 when Revision 3, dated May 20, 2004, of Boeing 
Alert Service Bulletin 737-71A1462, was issued. (Revision 3 was 
referred to as an appropriate source of service information for 
accomplishing the proposed actions in the original NPRM.) Following 
production it was determined that the affected aft engine mount is 
interchangeable with Model 737-900ER airplanes; however, those 
airplanes

[[Page 1553]]

were inspected in production to ensure that the center link was 
properly installed. Therefore, the requirements in the existing AD do 
not apply to those airplanes. However, since we are including airplanes 
on which the engines have been removed since production, we have added 
Model 737-900ER airplanes to the applicability section of this 
supplemental NPRM.

Comments

    We have considered the following comments on the original NPRM.

Request for Exemption From AD Requirements

    American Airlines (AA) asks that all operators that have performed 
the actions specified in Boeing Alert Service Bulletin 737-71A1462, 
Revision 3, dated May 20, 2004, be exempt from repeating maintenance 
actions in accordance with the original NPRM for a maintenance program 
that is already in place and proven effective. AA states that it has 
exceeded the requirements of AD 2003-03-01 by inspecting both engine 
aft mount center link assemblies, regardless of the stipulation in the 
existing AD, which limited the inspection requirement to engines 
removed since the airplane date of manufacture. AA adds that the 
inspections revealed that none of its installed or spare engines had 
incorrectly installed aft mount center link assemblies. AA notes that 
it is doing Part 2 of the Accomplishment Instructions of the service 
bulletin at every engine shop visit, and has implemented maintenance 
task documentation to verify the proper aft mount center link 
configuration at every engine change. AA concludes that it has not 
accepted delivery of any additional Model 737 airplanes since the 
release of the existing AD and Boeing Alert Service Bulletin 737-
71A1462, Revision 3, dated May 20, 2004.
    We acknowledge the commenter's request. Actions done in accordance 
with Boeing Alert Service Bulletin 737-71A1462, Revision 3, before the 
effective date of this AD are acceptable for compliance with the AD, as 
indicated by the phrase ``unless the actions have already been done'' 
in paragraph (f) of this AD. We have made no change to the supplemental 
NPRM in this regard.

Request To Change Paragraph (d)

    Boeing asks that paragraph (d) of the original NPRM be changed to 
indicate that the center link assembly for the aft engine mount was 
reversed on one airplane that had not had an engine removed since 
delivery. Boeing is aware of only one such report.
    We do not agree with the commenter. We have received another report 
indicating that some airplanes were found with the engine mounts 
installed incorrectly on engines that had not been removed since 
airplane delivery. Therefore, we have not changed paragraph (d) of the 
NPRM (paragraph (e) of the supplemental NPRM).

Request To Change Paragraph (n)

    Boeing asks that paragraph (n) of the original NPRM be changed to 
clarify parts not affected by the ``Parts Installation'' paragraph by 
including the permanent part marking on the center link assembly, as 
specified in Part 2 of the Work Instructions of Boeing Alert Service 
Bulletin 737-71A1462, Revision 3, dated May 20, 2004. Boeing states 
that this change would be equivalent to an existing alternative method 
of compliance (AMOC) for AD 2003-03-01, requiring the installation of 
marked engine mounts, as specified in the approved section of Boeing 
Alert Service Bulletin 737-71A1462, Revision 3, dated May 20, 2004.
    We agree with the commenter for the reasons provided. We have 
changed paragraph (n) of the supplemental NPRM to include permanent 
part marking on the center link assembly, as specified in Part 2 of the 
Work Instructions of Boeing Alert Service Bulletin 737-71A1462, 
Revision 3, dated May 20, 2004.

Request To Clarify Requirements in Paragraph (n)

    Japan Airlines (JAL) asks for clarification whether the requirement 
in paragraph (n) of the original NPRM applies only to airplanes 
affected by Boeing Alert Service Bulletin 737-71A1462, Revision 3, 
dated May 20, 2004; or to all Model 737-600, -700, -700C, -800, and -
900 series airplanes. JAL states that if the requirement in paragraph 
(n) applies to all Model 737NG (next generation) airplanes then a 
change should be made to paragraph (n) of the supplemental NPRM for 
clarification.
    We acknowledge the commenter's concern and provide the following 
clarification. As noted under ``Actions Since Original NPRM Was 
Issued,'' we have added Model 737-900ER airplanes to the applicability 
section of this supplemental NPRM; therefore, the requirement in 
paragraph (n) of the supplemental NPRM applies to all Model 737NG 
airplanes. No change to paragraph (n) of the supplemental NPRM is 
necessary.

Request To Change Paragraphs (i) and (o)

    CFM International states that the acronym CFMI is not accurate and 
recommends using CFM International (CFM) throughout the NPRM.
    We agree that the correct acronym should be used in the 
supplemental NPRM and in future rulemaking. However, CFMI is not 
referred to anywhere in this supplemental NPRM; therefore, no change is 
necessary.
    CFM also asks that paragraphs (i) and (o) of the original NPRM be 
changed to include the Engine and Propeller Directorate, Engine 
Certification Office (ECO), as an approved source for obtaining repair 
procedures. CFM states that the engine mounting lugs and adjacent 
engine turbine rear frame are under the responsibility of CFM as part 
of the engine type certificate. CFM notes that it is in charge of 
approval of repairs by delegation of both engine authorities, which are 
the FAA and European Aviation Safety Agency (EASA); CFM is a joint 
certification. CFM adds that for any part problems it contacts the ECO, 
in Burlington, Massachusetts, and the EASA Engine Certification Office, 
in Cologne, Germany. In light of this, CFM does not recommend the parts 
be repaired under approval of a Boeing Representative.
    We partially agree with the commenter for the reasons provided. We 
agree that the appropriate office for approval of certain repairs 
specified in the original NPRM is the ECO. Paragraph (i) of the 
original NPRM is a restatement of the requirements in AD 2003-03-01. 
However, paragraph (i) of the supplemental NPRM does refer to paragraph 
(o) of the supplemental NPRM for AMOC approval. We have changed 
paragraph (o) of this supplemental NPRM to allow for certain AMOC 
approvals by the ECO.

Explanation of Additional Changes Made to This Supplemental NPRM

    We have changed this supplemental NPRM to identify the legal name 
of the manufacturer as published in the most recent type certificate 
data sheet for the affected airplane models.
    We have added a new paragraph (d) to this supplemental NPRM to 
provide the Air Transport Association (ATA) of America subject code 71: 
Powerplant. This code is added to make this supplemental NPRM parallel 
with other new AD actions. We have reidentified subsequent paragraphs 
accordingly.

[[Page 1554]]

FAA's Determination and Proposed Requirements of the Supplemental NPRM

    Certain changes discussed above expand the scope of the original 
NPRM; therefore, we have determined that it is necessary to reopen the 
comment period to provide additional opportunity for public comment on 
this supplemental NPRM.

Explanation of Change to Costs of Compliance

    Since issuance of the original NPRM, we have increased the labor 
rate in the Costs of Compliance from $80 per work hour to $85 per work 
hour. The Costs of Compliance information, below, reflects this 
increase in the specified hourly labor rate.

Costs of Compliance

    There are about 1,846 airplanes of the affected design in the 
worldwide fleet. We estimate that 854 airplanes of U.S. registry would 
be affected by this proposed AD. There are no new requirements in this 
proposed AD; however, we have expanded the applicability as noted under 
``Actions Since Original NPRM Was Issued.'' The current costs for this 
proposed AD are recalculated for the convenience of affected operators, 
as follows:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                          Cost per
                           Action                              Work hours     Parts       airplane    Fleet cost
----------------------------------------------------------------------------------------------------------------
Maintenance records review (required by AD 2003-03-01)......            1           $0          $85      $72,590
Inspection for correct installation of center link assembly             1            0           85       72,590
 (new proposed action)......................................
----------------------------------------------------------------------------------------------------------------

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); 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 supplemental NPRM 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.

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

    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]

    2. The FAA amends Sec.  39.13 by removing amendment 39-13025 (68 FR 
4367, January 29, 2003) and adding the following new AD:

The Boeing Company: Docket No. FAA-2008-1118; Directorate Identifier 
2007-NM-318-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by February 
25, 2011.

Affected ADs

    (b) This AD supersedes AD 2003-03-01, Amendment 39-13025.

Applicability

    (c) This AD applies to all The Boeing Company Model 737 -600, -
700, -700C, -800, -900, and -900ER series airplanes, certificated in 
any category.

Subject

    (d) Air Transport Association (ATA) of America Code 71: 
Powerplant.

Unsafe Condition

    (e) This AD results from reports indicating that operators found 
that the center link assembly for the aft engine mount was reversed 
on several airplanes that had not had an engine removed since 
delivery. We are issuing this AD to prevent increased structural 
loads on the aft engine mount, which could result in failure of the 
aft engine mount and consequent separation of the engine from 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 the Requirements of AD 2003-03-01

Review of Maintenance Records

    (g) For Model 737-600, -700, -700C, -800, and -900 series 
airplanes: Within 90 days after February 13, 2003 (the effective 
date of AD 2003-03-01), review the airplane maintenance records to 
determine whether either engine has been removed since the 
airplane's date of manufacture. If neither engine has been removed 
since the airplane's date of manufacture, no further action is 
required by this paragraph.

Inspection of Engines That Have Been Removed to Determine if Center 
Link Assembly is Installed Correctly

    (h) For Model 737-600, -700, -700C, -800, and -900 series 
airplanes on which any installed engine has been removed from the 
airplane since the airplane's date of manufacture: Within 90 days 
after February 13, 2003, do a one-time general visual inspection to 
determine if the center link assembly of the aft engine mount is 
installed correctly, in accordance with the

[[Page 1555]]

Accomplishment Instructions of Boeing Alert Service Bulletin 737-
71A1462, Revision 1, dated November 7, 2002; or Revision 3, dated 
May 20, 2004. If the center link assembly is installed correctly, no 
further action is required by paragraph (h) or (i) of this AD for 
that engine. As of the effective date of this AD, use only Boeing 
Alert Service Bulletin 737-71A1462, Revision 3.

    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, hanger 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.''

Follow-on and Corrective Actions

    (i) For airplanes on which any center link assembly is found 
installed incorrectly during any inspection required by paragraph 
(h), (k), or (l) of this AD: Before further flight, do the actions 
specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-71A1462, Revision 1, dated November 7, 2002; or 
Revision 3, dated May 20, 2004; except that it is not necessary to 
submit a report of findings to the airplane manufacturer. As of the 
effective date of this AD, use only Boeing Alert Service Bulletin 
737-71A1462, Revision 3.
    (1) Remove the center link assembly and install it correctly.
    (2) Perform a detailed inspection of the engine mounting lugs 
and engine turbine rear frame for cracking, yielding, buckling, or 
wear damage.
    (3) Perform a detailed inspection of the hardware for the aft 
engine mount; including the center link assembly, right link 
assembly, aft mount hanger assembly, and link pins; for cracking, 
yielding, buckling, or wear damage.

    Note 2:  For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''

Repair

    (j) If any cracking, yielding, buckling, or wear damage is found 
during the inspections required by paragraphs (i)(2) and (i)(3) of 
this AD: Before further flight, replace the discrepant part with a 
new or serviceable part, or repair in accordance with a method 
approved in accordance with the procedures specified in paragraph 
(o) of this AD.

New Requirements of This AD

Inspection of Engines That Have Not Been Removed To Determine if Center 
Link Assembly Is Installed Correctly

    (k) For airplanes identified in Boeing Alert Service Bulletin 
737-71A1462, Revision 3, dated May 20, 2004, on which any installed 
engine has not been removed from the airplane since the airplane's 
date of manufacture: Within 90 days after the effective date of this 
AD, do a detailed inspection to determine if the center link 
assembly of the aft engine mount is installed correctly, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 737-71A1462, Revision 3, dated May 20, 2004. If the 
center link is installed correctly, no further action is required by 
this paragraph for that engine.

Follow-on and Corrective Actions

    (l) For airplanes on which any center link assembly is found 
installed incorrectly during the inspection required by paragraph 
(k) of this AD: Before further flight, do the follow-on and 
corrective actions required by paragraph (i) of this AD.

Credit for Actions Done Using Previous Service Information

    (m) Inspections and corrective actions done before the effective 
date of this AD in accordance with a Boeing service bulletin listed 
in Table 1 of this AD are acceptable for compliance with the 
corresponding requirements of this AD.

                                       Table 1--Previous Service Bulletins
----------------------------------------------------------------------------------------------------------------
       Boeing service bulletin                     Revision--                              Dated--
----------------------------------------------------------------------------------------------------------------
737-71A1462.........................  Original............................  August 29, 2002.
737-71A1462.........................  1...................................  November 7, 2002.
737-71A1462.........................  2...................................  May 29, 2003.
----------------------------------------------------------------------------------------------------------------

Parts Installation

    (n) As of the effective date of this AD, no person may install 
an engine on any airplane identified in paragraph (c) of this AD 
unless the actions required by paragraph (n)(1) or (n)(2) of this AD 
are accomplished.
    (1) The inspection is accomplished in accordance with the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
71A1462, Revision 3, dated May 20, 2004, and the center link 
assembly of the aft engine mount is found to be installed correctly.
    (2) The hanger fitting and center link assembly are marked and 
part marked in accordance with Part 2 of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 737-71A1462, Revision 
3, dated May 20, 2004.

    Note 3:  For hanger fittings and center link assemblies marked 
and part marked in production, as specified in Part 2 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 737-
71A1462, Revision 3, dated May 20, 2004, the actions specified in 
paragraph (n)(2) of this AD do not apply.

Alternative Methods of Compliance (AMOCs)

    (o) The certification office specified in paragraph (o)(1) or 
(o)(2) of this AD, as applicable, has the authority to approve AMOCs 
for paragraphs (i) and (j) of this AD, if requested using the 
procedures found in 14 CFR 39.19.
    (1) For the structure identified in paragraph (i)(2) of this AD: 
The Manager, Engine Certification Office (ECO), FAA. Send 
information to ATTN: Antonio Cancelliere, Aerospace Engineer, ANE-
141, FAA, ECO, 12 New England Executive Park, Burlington, MA 01803-
5299; telephone 781-238-7751; fax 781-238-7199.
    (2) For the structure identified in paragraph (i)(3) of this AD: 
The Manager, Seattle Aircraft Certification Office (ACO), FAA. Send 
information to ATTN: Alan Pohl, Aerospace Engineer, Airframe Branch, 
ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; telephone (425) 917-6450; fax (425) 917-6590. 
Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-
Requests@faa.gov.
    (3) 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.
    (4) An AMOC that provides an acceptable level of safety may be 
used for any repair required by paragraph (i)(3) of this AD if it is 
approved by 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.

[[Page 1556]]

    Issued in Renton, Washington, on December 17, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
Peter A. White,
Assistant Directorate Manager, Engine and Propeller Directorate, 
Aircraft Certification Service.
[FR Doc. 2011-367 Filed 1-10-11; 8:45 am]
BILLING CODE 4910-13-P