
[Federal Register Volume 76, Number 164 (Wednesday, August 24, 2011)]
[Proposed Rules]
[Pages 52901-52905]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-21668]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0724; Directorate Identifier 2010-NM-181-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Model 757-200, -
200PF, and -200CB Series 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 the products listed above. The existing AD 
currently requires repetitive inspections of the shim installation 
between the engine strut vertical flange and bulkhead, and repair if 
necessary. The existing AD also requires, for certain airplanes, an 
inspection for cracking of the four critical fastener holes in the 
horizontal flange, and repair if necessary. Additionally, the existing 
AD requires that the existing action be performed on airplanes without 
conclusive records of previous inspections. Since we issued that AD, we 
have received reports of loose fasteners and cracks at the joint common 
to the aft torque bulkhead and strut-to-diagonal brace fitting and one 
report of such damage occurring less than 3,000 flight cycles after the 
last inspection. This proposed AD would reduce the repetitive 
inspection interval, and add repetitive detailed inspections for 
cracking of the bulkhead, and repair if necessary. This proposed AD 
would also provide an option, for certain airplanes, to extend the 
repetitive intervals by also doing repetitive ultrasonic inspections 
for cracking of the bulkhead, and repair if necessary. This proposed AD 
would also add an option for the high frequency eddy current inspection 
for cracking of the critical fastener holes, and repair if necessary. 
We are proposing this AD to detect and correct cracks, loose and broken 
bolts, and shim migration in the joint between the aft torque bulkhead 
and the strut-to-diagonal brace fitting, which could result in damage 
to the strut and consequent separation of the strut and engine from the 
airplane.

DATES: We must receive comments on this proposed AD by October 11, 
2011.

ADDRESSES: 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: 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 AD, contact Boeing 
Commercial Airplanes, Attention: Data & Services Management, P.O. Box 
3707, MC 2H-65, Seattle, Washington 98124-2207; phone: 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 (phone: 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: Nancy Marsh, Aerospace Engineer, 
Airframe Branch, ANM-120S, Seattle Aircraft Certification Office (ACO), 
FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; phone: 425-
917-6440; fax: 425-917-6590; e-mail: Nancy.Marsh@faa.gov.

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-2011-0724; 
Directorate Identifier 2010-NM-181-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 February 22, 2008, we issued AD 2008-05-10, Amendment 39-15404 
(73 FR 11347, March 3, 2008), for certain Boeing Model 757-200, -200PF, 
and -200CB series airplanes powered by Rolls-Royce engines. That AD 
requires repetitive inspections of the shim installation between the 
engine strut vertical flange and bulkhead, and repair if necessary. 
That AD also requires, for certain airplanes, an inspection for 
cracking of the four critical fastener holes in the horizontal flange, 
and repair if necessary. That AD resulted from reports of cracking in 
the pylon under bolts that appear to be undamaged during the existing 
AD inspections. That AD also resulted from our determination that 
operators did not maintain records of previous inspections that are 
necessary to determine the appropriate corrective actions. We issued 
that AD to detect and correct cracks, loose and broken bolts, and shim 
migration in the joint between the aft torque bulkhead and the strut-
to-diagonal brace fitting, which could result in damage to the strut 
and consequent separation of the strut and engine from the airplane.

Actions Since Existing AD Was Issued

    Since we issued AD 2008-05-10, we have received reports of loose 
fasteners and cracks at the joint common to the aft torque bulkhead and 
strut-to-diagonal brace fitting and one report of

[[Page 52902]]

such damage found fewer than 3,000 flight cycles after the last 
inspection.

Related Service Information

    We reviewed Boeing Alert Service Bulletin 757-54A0047, Revision 4, 
dated June 24, 2010. This service information reduces the repetitive 
inspection interval to between 1,800 flight cycles and 3,000 flight 
cycles, depending on the airplane group and configuration. This service 
information also adds an optional ultrasonic inspection for the high 
frequency eddy current inspection to detect cracking of the critical 
fastener holes, and repairs if necessary. This service information adds 
procedures for repetitive detailed inspections for cracking of the 
bulkhead around the access door cutout and around the critical 
fasteners in the horizontal flange, and repair if necessary. This 
service information also provides an option, for certain airplanes, to 
extend the repetitive intervals by also doing repetitive ultrasonic 
inspections for cracking of the bulkhead around the fasteners in the 
horizontal flange, and repairs if necessary.

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 2008-05-
10.
    This proposed AD would reduce the repetitive inspection interval, 
and add repetitive detailed inspections for cracking of the bulkhead, 
and repair if necessary. This proposed AD would also provide an option, 
for certain airplanes, to extend the repetitive intervals by also doing 
repetitive ultrasonic inspections for cracking of the bulkhead, and 
repair if necessary. This proposed AD would also add an option for the 
high frequency eddy current inspection for cracking of the critical 
fastener holes, and repair if necessary.

Differences Between the Proposed AD and the Service Information

    Boeing Alert Service Bulletin 757-54A0047, Revision 4, dated June 
24, 2010, 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.

Change to Existing AD

    We have removed the ``Service Bulletin Reference'' paragraph from 
this proposed AD. That paragraph was identified as paragraph (f) in AD 
2008-05-10. Instead, we have provided the full service bulletin 
citations throughout this proposed AD and re-identified subsequent 
paragraphs accordingly.

Costs of Compliance

    We estimate that this proposed AD affects 309 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                                     Estimated costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
                Action                         Labor cost          Parts cost      Cost per product                   Cost on U.S. operators
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Part I Inspection on fasteners and      28 work-hours x $85 per            $0  $2,380 per inspection     $735,420 per inspection cycle.
 shims--vertical flange [retained        hour = $2,380 per                      cycle.
 actions from existing AD].              inspection cycle.
Part II Inspection on fasteners--       6 work-hours x $85 per              0  $510 per inspection       $157,590 per inspection cycle.
 horizontal flange [retained actions     hour = $510 per                        cycle.
 from existing AD].                      inspection cycle.
Part IV inspection on critical          6 work-hours x $85 per              0  $510 per inspection       $157,590 per inspection cycle.
 fasteners--horizontal flange            hour = $510 per                        cycle.
 [retained actions from existing AD].    inspection cycle.
Part II Additional inspection actions   10 work-hours x $85 per             0  $850 per inspection       $262,650 per inspection cycle.
 on fasteners--horizontal flange [new    hour = $850 per                        cycle.
 proposed action].                       inspection cycle.
Part IV inspection on critical          8 to 22 work-hours x $85            0  $680 to $1,870 per        $210,120 to $577,830 per inspection cycle.
 fasteners--horizontal flange [new       per hour = $680 to                     inspection cycle.
 proposed action].                       $1,870 per 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

[[Page 52903]]

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

    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 airworthiness directive 
(AD) 2008-05-10, Amendment 39-15404 (73 FR 11347, March 3, 2008), and 
adding the following new AD:
The Boeing Company: Docket No. FAA-2011-0724; Directorate Identifier 
2010-NM-181-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by October 
11, 2011.

Affected ADs

    (b) This AD supersedes AD 2008-05-10, Amendment 39-15404.

Applicability

    (c) This AD applies to Boeing Model 757-200, -200PF, and -200CB 
series airplanes; certificated in any category; line numbers 1 
through 1048 inclusive; powered by Rolls-Royce engines.

Subject

    (d) Joint Aircraft System Component (JASC)/Air Transport 
Association (ATA) of America Code 54, Nacelles/Pylons.

Unsafe Condition

    (e) This AD was prompted by reports of loose fasteners and 
cracks at the joint common to the aft torque bulkhead and strut-to-
diagonal brace fitting and one report of such damage occurring less 
than 3,000 flight cycles after the last inspection. We are issuing 
this AD to detect and correct cracks, loose and broken bolts, and 
shim migration in the joint between the aft torque bulkhead and the 
strut-to-diagonal brace fitting, which could result in damage to the 
strut and consequent separation of the strut and engine from the 
airplane.

Compliance

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

Restatement of the Requirements of AD 2007-16-13 With Reduced 
Repetitive Intervals and New Optional Inspection Method

One-Time Inspection and Repair With Optional Inspection Method

    (g) For airplanes identified in paragraphs (g)(1) and (g)(2) of 
this AD: Within 90 days after August 24, 2007 (the effective date of 
AD 2007-16-13), do a high frequency eddy current (HFEC) inspection 
for cracking of the four critical fastener holes in the horizontal 
flange and, before further flight, do all applicable repairs, in 
accordance with Part IV of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 757-54A0047, Revision 3, dated June 27, 2007; 
or Revision 4, dated June 24, 2010; except as required by paragraph 
(k) of this AD. As of the effective date of this AD, only Boeing 
Alert Service Bulletin 757-54A0047, Revision 4, dated June 24, 2010, 
may be used. Doing an ultrasonic inspection for cracking of the 
fasteners, in accordance with Part IV of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-54A0047, Revision 
4, dated June 24, 2010, is an acceptable method for compliance with 
the HFEC inspection requirement of this paragraph.
    (1) Airplanes on which findings on the horizontal or vertical 
fasteners or the shims led to a rejection of any fastener during the 
actions specified in Boeing Alert Service Bulletin 757-54A0047, 
dated November 13, 2003; or Boeing Service Bulletin 757-54A0047, 
Revision 1, dated March 24, 2005.
    (2) Airplanes that had equivalent findings prior to Boeing Alert 
Service Bulletin 757-54A0047, dated November 13, 2003, except for 
findings on airplanes identified as Group 1, Configuration 2, in 
Boeing Alert Service Bulletin 757-54A0047, Revision 3, dated June 
27, 2007, that were prior to the incorporation of Boeing Service 
Bulletin 757-54-0035.

Repetitive Inspection and Repair

    (h) At the applicable initial times specified in paragraph 1.E., 
``Compliance'' of Boeing Alert Service Bulletin 757-54A0047, 
Revision 3, dated June 27, 2007, except as required by paragraphs 
(i) and (j) of this AD: Do the inspections specified in paragraphs 
(h)(1), (h)(2), and (h)(3) of this AD, and before further flight, do 
all the applicable related investigative actions and repairs, by 
doing all the actions specified in Parts I and II of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 757-
54A0047, Revision 3, dated June 27, 2007; or by doing all the 
actions in Part I and in Step 2 of Part II of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-54A0047, Revision 
4, dated June 24, 2010; except as required by paragraph (k) of this 
AD. As of the effective date of this AD, only Boeing Alert Service 
Bulletin 757-54A0047, Revision 4, dated June 24, 2010, may be used. 
Repeat the inspections required by this paragraph at the times 
specified in paragraph (h)(4) of this AD.
    (1) Do detailed inspections of the shim installations between 
the vertical flange and bulkhead to determine if there are signs of 
movement.
    (2) Do detailed inspections of the four fasteners in the 
vertical flange to determine if there are signs of movement or if 
there are gaps under the head or collar.
    (3) Do detailed inspections of the fasteners that hold the strut 
to the horizontal flange of the strut-to-diagonal brace fitting to 
determine if there are signs of movement or if there are gaps under 
the head or collar.
    (4) Repeat the inspections required by paragraph (h) of this AD 
at the earlier of the times specified in paragraphs (h)(4)(i) and 
(h)(4)(ii) of this AD. Thereafter, repeat the inspections at 
intervals not to exceed the applicable intervals specified in 
paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 
757-54A0047, Revision 4, dated June 24, 2010.
    (i) At intervals not to exceed the applicable intervals 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 757-54A0047, Revision 3, dated June 27, 2007.
    (ii) At intervals not to exceed the applicable intervals 
specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service 
Bulletin 757-54A0047, Revision 4, dated June 24, 2010; or within 90 
days after the effective date of this AD, whichever occurs later.

Exceptions to Alert Service Bulletin Procedures

    (i) Where Boeing Alert Service Bulletin 757-54A0047, Revision 3, 
dated June 27, 2007, specifies a compliance time relative to ``the 
date on this service bulletin,'' this AD requires compliance within 
the corresponding specified time relative to the effective date of 
AD 2007-16-13.
    (j) Where Boeing Alert Service Bulletin 757-54A0047, Revision 3, 
dated June 27, 2007, specifies a compliance time relative to the 
``date of issuance of airworthiness certificate,'' this AD requires 
compliance within the corresponding time relative to the date of 
issuance of the original standard airworthiness certificate or the 
date of issuance of the original export certificate of 
airworthiness.
    (k) If any crack is found during any inspection required by this 
AD, and Boeing Alert Service Bulletin 757-54A0047, Revision 3, dated 
June 27, 2007; or Revision 4, dated June 24, 2010; specifies to 
contact Boeing for appropriate action: Before further flight, repair 
the crack using a method approved in accordance with the procedures 
specified in paragraph (s) of this AD.

[[Page 52904]]

Restatement of the Requirements of AD 2008-05-10

Inspection/Repair for Airplanes for Which There Are No Conclusive 
Inspection Records

    (l) For airplanes for which there are no conclusive records 
showing no loose or missing fasteners during previous inspections 
done in accordance with the requirements of AD 2007-16-13, Amendment 
39-15152 (72 FR 44753, August 9, 2007); or AD 2005-12-04, Amendment 
39-14120 (70 FR 34313 June 14, 2005): Do the actions specified in 
paragraphs (l)(1) and (l)(2) of this AD, at the times specified in 
those paragraphs, as applicable.
    (1) Within 90 days after March 18, 2008 (the effective date of 
AD 2008-05-10), do the actions specified in paragraph (g) of this 
AD, except as required by paragraph (k) of this AD.
    (2) At the applicable initial times specified in paragraph 1.E., 
``Compliance,'' of Boeing Alert Service Bulletin 757-54A0047, 
Revision 3, dated June 27, 2007, do the actions specified in 
paragraph (h) of this AD, except as required by paragraphs (j) and 
(m) of this AD. And, before further flight, do all applicable 
related investigative actions and repairs, by doing all the actions 
specified in Parts I and II of the Accomplishment Instructions of 
Boeing Alert Service Bulletin 757-54A0047, Revision 3, dated June 
27, 2007; or in Part 1 and in Step 2 of Part II of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 757-
54A0047, Revision 4, dated June 24, 2010; except as required by 
paragraph (k) of this AD. As of the effective date of this AD, only 
Boeing Alert Service Bulletin 757-54A0047, Revision 4, dated June 
24, 2010, may be used. Repeat the actions specified in paragraph (h) 
of this AD at the times specified in paragraph (h)(4) of this AD.

Exception to Alert Service Bulletin Procedures

    (m) Where Boeing Alert Service Bulletin 757-54A0047, Revision 3, 
dated June 27, 2007, specifies a compliance time relative to ``the 
date on this service bulletin,'' this AD requires compliance within 
the corresponding specified time relative to the effective date of 
AD 2008-05-10.

Credit for Actions Done in Accordance With Previous Service Information

    (n) Except for the actions specified in paragraph (l) of this 
AD, actions done before March 18, 2008, in accordance with Boeing 
Service Bulletin 757-54A0047, Revision 1, dated March 24, 2005; or 
Boeing Alert Service Bulletin 757-54A0047, Revision 2, dated January 
31, 2007; are considered acceptable for compliance with the 
corresponding actions specified in this AD.
    (o) An inspection and corrective actions done before June 29, 
2005 (the effective date of AD 2005-12-04), in accordance with 
paragraph (b) or (c), as applicable, of AD 2004-12-07, are 
acceptable for compliance with the initial inspection requirement of 
paragraph (h) of this AD.

An Acceptable Method of Compliance With Certain Requirements of AD 
2004-12-07

    (p) Accomplishing the actions specified in paragraphs (g) and 
(h) of this AD terminates the requirements specified in paragraphs 
(b) and (c) of AD 2004-12-07.

New Requirements of This AD

Repetitive Inspections and Repair

    (q) At the applicable initial compliance times specified in 
paragraph (r) of this AD: Do the applicable actions specified in 
paragraph (q)(1) or (q)(2) of this AD, in accordance with Step 3 of 
Part II of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 757-54A0047, Revision 4, dated June 24, 2010. If no 
cracking is found, repeat the inspections thereafter at intervals 
not to exceed the applicable intervals specified in paragraph 1.E., 
``Compliance,'' of the Boeing Alert Service Bulletin 757-54A0047, 
Revision 4, dated June 24, 2010. If any crack is found during any 
inspection required by this paragraph, before further flight, repair 
the crack using a method approved in accordance with the procedures 
specified in paragraph (s) of this AD.
    (1) For Group 1, Configuration 1 airplanes identified in Boeing 
Alert Service Bulletin 757-54A0047, Revision 4, dated June 24, 2010: 
Do the actions specified in paragraph (q)(1)(i) or (q)(1)(ii) of 
this AD.
    (i) Do a detailed inspection for cracking of the bulkhead and in 
the area around the access door cutout and around the critical 
fasteners in the horizontal flange.
    (ii) Do detailed inspection for cracking of the bulkhead and in 
the area around the access door cutout and around the critical 
fasteners in the horizontal flange, and do an ultrasonic inspection 
for cracking of the bulkhead around the fasteners in the horizontal 
flange. Doing the actions in this paragraph extends the repetitive 
intervals of the inspections required by paragraph (q) of this AD.
    (2) For Group 1, Configuration 2 airplanes; and Group 2 
airplanes; identified in Boeing Alert Service Bulletin 757-54A0047, 
Revision 4, dated June 24, 2010: Do a detailed inspection for 
cracking of the bulkhead and in the area around the access door 
cutout and around the critical fasteners in the horizontal flange.
    (r) At the applicable times specified in paragraphs (r)(1) and 
(r)(2) of this AD, do the actions required by paragraph (q) of this 
AD.
    (1) For Group 1, Configuration 1 airplanes identified in Boeing 
Alert Service Bulletin 757-54A0047, Revision 4, dated June 24, 2010: 
At the later of the times specified in paragraph (r)(1)(i) or 
(r)(1)(ii) of this AD.
    (i) Within 1,800 flight cycles after accomplishing the most 
recent inspection required by paragraph (h) of this AD.
    (ii) Within 90 days after the effective date of this AD.
    (2) For Group 1, Configuration 2 airplanes; and Group 2 
airplanes; identified in Boeing Alert Service Bulletin 757-54A0047, 
Revision 4, dated June 24, 2010: At the later of the times specified 
in paragraph (r)(2)(i) or (r)(2)(ii) of this AD.
    (i) Within 3,000 flight cycles after accomplishing the most 
recent inspection required by paragraph (h) of this AD.
    (ii) Within 90 days after the effective date of this AD.

Alternative Methods of Compliance (AMOCs)

    (s)(1) The Manager, Seattle Certification Office (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 e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by the 
Boeing Commercial Airplanes 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 AD 2004-12-07 
are approved as AMOCs for the corresponding provisions of this AD.
    (5) AMOCs approved previously in accordance with AD 2005-12-04 
are approved as AMOCs for the corresponding provisions of this AD.
    (6) AMOCs approved previously in accordance with AD 2007-16-13 
are approved as AMOCs for the corresponding provisions of this AD.
    (7) AMOCs approved previously in accordance with AD 2008-05-10 
are approved as AMOCs for the corresponding provisions of this AD.

Related Information

    (t) For more information about this AD, contact Nancy Marsh, 
Aerospace Engineer, Airframe Branch, ANM-120S, Seattle Aircraft 
Certification Office (ACO), FAA, 1601 Lind Avenue, SW., Renton, 
Washington 98057-3356; phone 425-917-6440; fax 425-917-6590; e-mail: 
Nancy.Marsh@faa.gov.
    (u) 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; phone: 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.


[[Page 52905]]


    Issued in Renton, Washington, on August 12, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-21668 Filed 8-23-11; 8:45 am]
BILLING CODE 4910-13-P


