[Federal Register Volume 77, Number 120 (Thursday, June 21, 2012)]
[Proposed Rules]
[Pages 37332-37337]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-15181]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
 
 ========================================================================
 

  Federal Register / Vol. 77, No. 120 / Thursday, June 21, 2012 / 
Proposed Rules  

[[Page 37332]]



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 Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

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

-----------------------------------------------------------------------

SUMMARY: We are revising an earlier proposed airworthiness directive 
(AD) for certain The Boeing Company Model 757-200, -200PF, and -200CB 
series airplanes powered by Rolls-Royce engines. That NPRM proposed to 
supersede an existing AD that requires repetitive inspections of the 
shim installation between the drag brace fitting vertical flange and 
bulkhead, and repair if necessary; for certain airplanes, an inspection 
for cracking of the four critical fastener holes in the horizontal 
flange, and repair if necessary; and, for airplanes without conclusive 
records of previous inspections, performing the existing actions. That 
NPRM proposed to reduce the repetitive inspection interval, add 
repetitive detailed inspections for cracking of the bulkhead, and 
repair if necessary; extend the repetitive intervals for certain 
airplanes by also doing repetitive ultrasonic inspections for cracking 
of the bulkhead, and repair if necessary; and an option for the high 
frequency eddy current inspection for cracking of the critical fastener 
holes, and repair if necessary. That NPRM 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. This action revises that NPRM by adding a terminating 
action for certain repetitive inspections. We are proposing the 
supplemental NPRM 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. Since these actions impose an additional burden over that 
proposed in the NPRM, we are reopening the comment period to allow the 
public the chance to comment on these proposed changes.

DATES: We must receive comments on the supplemental NPRM by August 6, 
2012.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: 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, WA 98124-2207; phone: 206-544-5000, 
extension 1; fax: 206-766-5680; Internet: https://www.myboeingfleet.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

Examining the AD Docket

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

FOR FURTHER INFORMATION CONTACT: 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; email: [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-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

    We issued an NPRM to amend 14 CFR part 39 to supersede AD 2008-05-
10, Amendment 39-15404 (73 FR 11347, March 3, 2008), to include an AD 
applies to certain The Boeing Company Model 757-200, -200PF, and -200CB 
series airplanes powered by Rolls-Royce engines. That NPRM was 
published in the Federal Register on August 24, 2011 (76 FR 52901). 
That NPRM proposed to continue to repetitive inspections of the shim 
installation between the drag brace fitting vertical flange and 
bulkhead, and repair if necessary; for certain airplanes, an inspection 
for cracking of the four critical fastener holes in the horizontal 
flange, and repair if necessary; and, for airplanes without conclusive 
records of previous inspections, performing the existing actions. 
Additionally, the existing AD requires that the existing

[[Page 37333]]

action be performed on airplanes without conclusive records of previous 
inspections. That NPRM proposed to reduce the repetitive inspection 
interval, and add repetitive detailed inspections for cracking of the 
bulkhead, and repair if necessary. That NPRM proposed 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; and proposed an option to the high frequency eddy 
current inspection for cracking of the critical fastener holes, and 
repair if necessary.

Actions Since Previous NPRM (76 FR 52901, August 24, 2011) Was Issued

    Since we issued the previous NPRM (76 FR 52901, August 24, 2011), 
new service information has been issued that specifies additional 
actions that are necessary to address the identified unsafe condition, 
and also describes a terminating action for the repetitive inspections 
on certain airplanes.

Comments

    We gave the public the opportunity to comment on the previous NPRM 
(76 FR 52901, August 24, 2011). The following presents the comments 
received on the NPRM and the FAA's response to each comment.

Agreement With the Previous NPRM (76 FR 52901, August 24, 2011)

    Continental Airlines (Continental) stated it concurs in general 
with previous NPRM (76 FR 52901, August 24, 2011) to mandate Boeing 
Alert Service Bulletin 757-54A0047, Revision 4, dated June 24, 2010, 
inspections.

Request To Reference Revised Service Information

    Continental, UPS, European Air Transport Leipzig GmbH (EATL), and 
FedEx requested that the previous NPRM (76 FR 52901, August 24, 2011) 
be changed to include Boeing Alert Service Bulletin 757-54A0047, 
Revision 5, dated June 9, 2011. The commenters stated this revised 
service information includes a terminating action for the repetitive 
inspections.
    We agree because Boeing Alert Service Bulletin 757-54A0047, 
Revision 5, dated June 9, 2011, includes terminating action to address 
the unsafe condition. Boeing Alert Service Bulletin 757-54A0047, 
Revision 5, dated June 9, 2011, describes procedures for certain 
airplanes for replacing the horizontal and vertical flange fasteners in 
the strut-to-diagonal brace fitting on the number 1 and number 2 struts 
with new fasteners, and doing related investigative and corrective 
actions if necessary. The related investigative action is an eddy 
current inspection for cracking of the critical fastener holes in the 
horizontal and vertical flange. The corrective action is contacting 
Boeing for repair instructions and doing the repair. We have changed 
this supplemental NPRM to refer to Boeing Alert Service Bulletin 757-
54A0047, Revision 5, dated June 9, 2011, and have made the terminating 
action specified in this service information mandatory. We have also 
added paragraph (p) in this supplemental NPRM to provide credit for 
actions accomplished before the effective date of the AD using Boeing 
Alert Service Bulletin 757-54A0047, Revision 4, dated June 24, 2010.

Request To Include Alternative Method of Compliance (AMOC) in Previous 
NPRM (76 FR 52901, August 24, 2011)

    Continental requested a paragraph be added to the previous NPRM (76 
FR 52901, August 24, 2011) that approves accomplishment of the 
terminating modification specified in Boeing Alert Service Bulletin 
757-54A0047, Revision 5, dated June 9, 2011, as an AMOC with the 
actions specified in paragraphs (g), (h), (l), (q), and (r) of the 
previous NPRM. The commenter did not provide any justification for this 
request.
    We disagree with adding an AMOC provision to the supplemental NPRM. 
As previously stated, we are changing the supplemental NPRM to mandate 
the terminating action specified in Boeing Alert Service Bulletin 757-
54A0047, Revision 5, dated June 9, 2011, which would terminate the 
inspections specified in paragraphs (g), (h), (j), and (m) of the 
supplemental NPRM for Group 1, Configuration 2 airplanes; and Group 2 
airplanes; as identified in Boeing Alert Service Bulletin 757-54A0047, 
Revision 5, dated June 9, 2011. These supplemental NPRM paragraphs are 
the same paragraphs specified by the commenter (paragraphs (j) and (m) 
of the supplemental NPRM correspond to paragraphs (l) and (q) in the 
previous NPRM (76 FR 52901, August 24, 2011)). The commenter also 
included paragraph (r) of the previous NPRM (which is paragraph (n) in 
the supplemental NPRM); however, that paragraph is not pertinent since 
it provides the compliance times for paragraph (m) in the supplemental 
NPRM. Termination of the inspections specified in paragraphs (g), (h), 
(j), and (m) of this supplemental NPRM, through accomplishment of the 
modification required by paragraph (o) of this supplemental NPRM, has 
the same result as the AMOC requested by the commenter, since use of 
Boeing Alert Service Bulletin 757-54A0047, Revision 5, dated June 9, 
2011, is being proposed. We have not changed the supplemental NPRM in 
this regard.

Request To Add Actions Specified in Revised Service Information

    Boeing proposed language for three new paragraphs to the previous 
NPRM (76 FR 52901, August 24, 2011), which correspond to paragraphs 
(s), (t), and (u) of the previous NPRM, that would require certain 
actions specified in Boeing Alert Service Bulletin 757-54A0047, 
Revision 5, dated June 9, 2011. The actions in Boeing's proposed 
paragraphs included installation of larger diameter fasteners, as 
specified in Boeing Alert Service Bulletin 757-54A0047, Revision 5, 
dated June 9, 2011, ``within 9,000 flight cycles or 54 months, 
whichever is earlier, after the effective date of the AD;'' crack 
repair instructions for cracking found during the fastener 
modification; and termination of inspections required in paragraphs 
(h), (l)(2), and (q) of the previous NPRM.
    We partially agree. We agree to refer to Boeing Alert Service 
Bulletin 757-54A0047, Revision 5, dated June 9, 2011, because it 
provides additional actions and a modification to address the unsafe 
condition for certain airplanes. We disagree with adding the specific 
paragraphs proposed by Boeing because we are issuing a supplemental 
NPRM that proposes to mandate Boeing Alert Service Bulletin 757-
54A0047, Revision 5, dated June 9, 2011. Therefore, the paragraphs 
proposed by Boeing that specify installing larger diameter fasteners 
and the compliance time are unnecessary. We have not changed the 
supplemental NPRM in this regard.
    Boeing also proposed a paragraph that defines the terminating 
action for the repetitive inspections required by paragraphs (h), 
(l)(2), and (q) of the previous NPRM (76 FR 52901, August 24, 2011). 
Part of the commenter's proposed terminating action paragraph for Group 
1, Configuration 1 airplanes; and Group 2 airplanes; is unnecessary. 
Boeing Alert Service Bulletin 757-54A0047, Revision 5, dated June 9, 
2011, specified in the supplemental NPRM, already includes this 
information. Additionally, the commenter's proposed terminating action 
paragraph stated that modification of the strut, in accordance with 
Boeing Alert Service Bulletin 757-54A0047, Revision 5, dated June 9, 
2011, terminates the repetitive inspections of paragraphs (h), (l)(2), 
and (q) of the previous NPRM for Group 1, Configuration 1 airplanes.

[[Page 37334]]

    We disagree with changing the supplemental NPRM to include this 
information as it is redundant to the information included in Boeing 
Alert Service Bulletin 757-54A0047, Revision 5, dated June 9, 2011. 
This service information defines Group 1, Configuration 1 airplanes, as 
airplanes that have not accomplished the modifiction described in 
Boeing Service Bulletin 757-54-0035, thus the signficance of the strut 
modification accomplishment is clearly specified. We have not changed 
the supplemental NPRM in this regard.

Request To Add an AMOC Into the Previous NPRM (76 FR 52901, August 24, 
2011)

    Boeing requested we add a paragraph to the previous NPRM (76 FR 
52901, August 24, 2011) stating that inspections and repairs done in 
accordance with Boeing Alert Service Bulletin 757-54A0047, Revision 5, 
dated June 9, 2011, are an AMOC for the corresponding requirements of 
the AD. Boeing stated that the inspections and repairs for Boeing Alert 
Service Bulletin 757-54A0047, Revision 5, dated June 9, 2011, are 
equivalent to the corresponding inspections and repairs specified in 
Boeing Alert Service Bulletin 757-54A0047, Revision 4, dated June 24, 
2010, and since Boeing Alert Service Bulletin 757-54A0047, Revision 5, 
dated June 9, 2011, is already published and in use by the operators, 
this would eliminate the need for a separate global AMOC for Boeing 
Alert Service Bulletin 757-54A0047, Revision 5, dated June 9, 2011, 
relative to this AD.
    We partially agree. The previous NPRM (76 FR 52901, August 24, 
2011) did reference Boeing Alert Service Bulletin 757-54A0047, Revision 
4, dated June 24, 2010. We agree that the actions specified in Boeing 
Alert Service Bulletin 757-54A0047, Revision 5, dated June 9, 2011, are 
equivalent to the corresponding actions specified in Boeing Alert 
Service Bulletin 757-54A0047, Revision 4, dated June 24, 2010. However, 
as stated previously, the supplemental NPRM references Boeing Alert 
Service Bulletin 757-54A0047, Revision 5, dated June 9, 2011, 
eliminating the need for an AMOC. We have not changed the supplemental 
NPRM in this regard.

Explanation of Additional Changes Made to This Supplemental NPRM

    We have revised certain headings throughout this supplemental NPRM.
    The credit for previous accomplishment of the actions required by 
AD 2008-05-10, Amendment 39-15404 (73 FR 11347, March 3, 2008), 
specified in paragraphs (n) and (o) of the previous NPRM (76 FR 52901, 
August 24, 2011), has been moved to paragraph (p) of the supplemental 
NPRM.
    We have revised the heading and wording for paragraphs (n) and (o) 
of this AD. This change does not affect the intent of those paragraphs.
    We revised paragraph (l) of this supplemental NPRM to refer to 
paragraphs (b) and (d) of AD 2004-12-07, Amendment 39-13666 (69 FR 
33561, June 16, 2004), instead of paragraphs (b) and (c) of AD 2004-12-
07, because paragraph (d) of AD 2004-12-07 contains the inspection of 
the fastener holes and inspection of the fasteners common to the lower 
spar fitting and strut aft bulkhead. Paragraph (c) of AD 2004-12-07 is 
a preliminary inspection of the middle gusset of the inboard side load 
fitting. We also revised paragraph (p) of this supplemental NPRM to 
reference paragraph (d) of AD 2004-12-07, instead of paragraph (c) of 
AD 2004-12-07.

FAA's Determination

    We are proposing this supplemental NPRM 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. Certain changes described above expand the scope of the 
original NPRM (76 FR 52901, August 24, 2011). As a result, we have 
determined that it is necessary to reopen the comment period to provide 
additional opportunity for the public to comment on this supplemental 
NPRM.

Proposed Requirements of the Supplemental NPRM

    This supplemental NPRM would retain all the requirements of AD 
2008-05-10, Amendment 39-15404 (73 FR 11347, March 3, 2008); reduce the 
repetitive inspection interval for cracking, and add repetitive 
detailed inspections for cracking of the bulkhead, and repair if 
necessary. This supplemental NPRM would also, for certain airplanes, 
add an option to extend the repetitive intervals by also doing 
repetitive ultrasonic inspections for cracking of the bulkhead, and 
repair if necessary; and add an option to the high frequency eddy 
current inspection for cracking of the critical fastener holes, and 
repair if necessary. This supplemental NPRM would also require 
replacing certain horizontal and vertical flange fasteners in the 
strut-to-diagonal brace fittings and accomplishing the actions 
specified in the service information described previously, except as 
discussed under ``Differences Between the Supplemental NPRM and the 
Service Information.''

Differences Between the Supplemental NPRM and the Service Information

    Boeing Alert Service Bulletin 757-54A0047, Revision 5, dated June 
9, 2011, specifies to contact the manufacturer for instructions on how 
to repair certain conditions, but this supplemental NPRM 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.
    Accomplishment of the actions required in paragraph (o) of this 
supplemental NPRM would terminate the inspection requirements of 
paragraphs (g), (h), (j), and (m) of this supplemental NPRM for Group 
1, Configuration 2 airplanes; and Group 2 airplanes; as identified in 
Boeing Alert Service Bulletin 757-54A0047, Revision 5, dated June 9, 
2011.

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
----------------------------------------------------------------------------------------------------------------
                                                                                                Cost on U.S.
              Action                    Labor cost        Parts cost    Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Part I Inspection on fasteners     28 work-hours x $85            $0  $2,380 per            $735,420 per
 and shims--vertical flange         per hour = $2,380                  inspection cycle      inspection cycle
 [retained actions from AD 2008-    per inspection
 05-10, Amendment 39-15404 (73 FR   cycle
 11347, March 3, 2008)]

[[Page 37335]]

 
Part II Inspection on fasteners--  6 work-hours x $85              0  $510 per inspection   $157,590 per
 horizontal flange [retained        per hour = $510 per                cycle                 inspection cycle.
 actions from AD 2008-05-10,        inspection cycle
 Amendment 39-15404 (73 FR 11347,
 March 3, 2008)]
Part IV inspection on critical     6 work-hours x $85              0  $510 per inspection   $157,590 per
 fasteners--horizontal flange       per hour = $510 per                cycle                 inspection cycle.
 [retained actions from AD 2008-    inspection cycle
 05-10, Amendment 39-15404 (73 FR
 11347, March 3, 2008)]
Part II Additional inspection      10 work-hours x $85             0  $850 per inspection   $262,650 per
 actions on fasteners--horizontal   per hour = $850 per                cycle                 inspection cycle.
 flange [new proposed action]       inspection cycle
Part IV inspection on critical     8 to 22 work-hours x            0  $680 to $1,870 per    $210,120 to $577,830
 fasteners--horizontal flange       $85 per hour = $680                inspection cycle      per inspection
 [new proposed action]              to $1,870 per                                            cycle.
                                    inspection cycle
Part V fastener replacement        Up to 37 work-hours           750  Up to $3,895 per      Up to $1,203,555 per
 flange [new proposed action]       x $85 per hour =                   strut                 strut.
                                    $3,145 per strut
----------------------------------------------------------------------------------------------------------------

    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 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 this 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.

(a) Comments Due Date

    The FAA must receive comments on this AD action by August 6, 
2012.

(b) Affected ADs

    This AD supersedes AD 2008-05-10, Amendment 39-15404 (73 FR 
11347, March 3, 2008).

(c) Applicability

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

(d) Subject

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

(e) Unsafe Condition

    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.

(f) Compliance

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

(g) Retained One-Time Inspection and Repair With Optional Inspection 
Method, With Reduced Repetitive Intervals and New Optional Inspection 
Method

    This paragraph restates the one-time inspection and repair with 
optional inspection method required by paragraph (g) of AD 2008-05-
10, Amendment 39-15404 (73 FR 11347, March 3, 2008), with reduced 
repetitive intervals, and a new optional inspection method, with 
revised service information. 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, Amendment 39-15152 (72 FR 
44753, August 9, 2007)), 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

[[Page 37336]]

repairs, in accordance with Part IV of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-54A0047, Revision 
3, dated June 27, 2007; Boeing Alert Service Bulletin 757-54A0047, 
Revision 4, dated June 24, 2010; or Boeing Alert Service Bulletin 
757-54A0047, Revision 5, dated June 9, 2011; except as required by 
paragraph (i)(3) of this AD. As of the effective date of this AD, 
only Boeing Alert Service Bulletin 757-54A0047, Revision 5, dated 
June 9, 2011, may be used to accomplish the actions required by this 
paragraph. 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; or Boeing Alert Service Bulletin 757-
54A0047, Revision 5, dated June 9, 2011; 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.

(h) Retained Repetitive Inspection and Repair, With Reduced Interval

    This paragraph restates the repetitive inspection and repair 
required by paragraph (h) of AD 2008-05-10, Amendment 39-15404 (73 
FR 11347, March 3, 2008), with reduced repetitive intervals and 
revised service information. 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)(1) and (i)(2) 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, or Boeing 
Alert Service Bulletin 757-54A0047, Revision 5, dated June 9, 2011, 
except as required by paragraph (i)(3) of this AD. As of the 
effective date of this AD, only Boeing Alert Service Bulletin 757-
54A0047, Revision 5, dated June 9, 2011, may be used to accomplish 
the actions required by this paragraph. 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 5, dated June 9, 2011.
    (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 5, dated June 9, 2011; or within 90 
days after the effective date of this AD; whichever occurs later.

(i) Retained Exceptions to Alert Service Bulletin Procedures

    This paragraph restates the exceptions to alert service bulletin 
procedures required by paragraphs (i), (j), and (k) of AD 2008-05-
10, Amendment 39-15404 (73 FR 11347, March 3, 2008), with revised 
service information.
    (1) 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, Amendment 39-15152 (72 FR 44753, August 9, 2007).
    (2) 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.
    (3) 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; Boeing Alert Service Bulletin 757-54A0047, Revision 
4, dated June 24, 2010; or Boeing Alert Service Bulletin 757-
54A0047, Revision 5, dated June 9, 2011; 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 (q) of this AD.

(j) Retained Inspection/Repair for Airplanes for Which There Are No 
Conclusive Inspection Records

    This paragraph restates the inspection/repair requirements for 
airplanes for which there are no conclusive inspection records, as 
required by paragraph (l) of AD 2008-05-10, Amendment 39-15404 (73 
FR 11347, March 3, 2008), with revised service information. 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 (j)(1) 
and (j)(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, Amendment 39-15404 (73 FR 11347, March 3, 2008)), do 
the actions specified in paragraph (g) of this AD, except as 
required by paragraph (i)(3) 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 (i)(2) 
and (k) 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, or Boeing Alert Service 
Bulletin 757-54A0047, Revision 5, dated June 9, 2011, except as 
required by paragraph (i)(3) of this AD. As of the effective date of 
this AD, only Boeing Alert Service Bulletin 757-54A0047, Revision 5, 
dated June 9, 2011, may be used to accomplish the actions required 
by this paragraph. Repeat the actions specified in paragraph (h) of 
this AD at the times specified in paragraph (h)(4) of this AD.

(k) Retained Exception to Alert Service Bulletin Procedures

    This paragraph restates the exception to alert service bulletin 
procedures required by paragraph (m) of AD 2008-05-10, Amendment 39-
15404 (73 FR 11347, March 3, 2008). 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.

(l) Retained Acceptable Method of Compliance With Certain Requirements 
of AD 2004-12-07, Amendment 39-13666 (69 FR 33561 June 16, 2004)

    This paragraph restates an acceptable method of compliance with 
certain requirements of AD 2004-12-07, Amendment 39-13666 (69 FR 
33561 June 16, 2004), specified by paragraph (p) of AD 2008-05-10, 
Amendment 39-15404 (73 FR 11347, March 3, 2008). Accomplishing the 
actions specified in paragraphs (g) and (h) of this AD terminates 
the requirements specified in paragraphs (b) and (d) of AD 2004-12-
07.

[[Page 37337]]

(m) New Repetitive Inspections and Repair

    At the applicable initial compliance times specified in 
paragraph (n) of this AD: Do the applicable actions specified in 
paragraph (m)(1) or (m)(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; or Boeing 
Alert Service Bulletin 757-54A0047, Revision 5, dated June 9, 2011. 
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 Accomplishment Instructions 
of Boeing Alert Service Bulletin 757-54A0047, Revision 5, dated June 
9, 2011. 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 (q) of this AD.
    (1) For Group 1, Configuration 1 airplanes identified in Boeing 
Alert Service Bulletin 757-54A0047, Revision 5, dated June 9, 2011: 
Do the actions specified in paragraph (m)(1)(i) or (m)(1)(ii) of 
this AD.
    (i) Do a detailed inspection for cracking of the bulkhead in the 
area around the access door cutout and around the critical fasteners 
in the horizontal flange.
    (ii) Do a detailed inspection for cracking of the bulkhead 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 (n) of this AD.
    (2) For Group 1, Configuration 2 airplanes; and Group 2 
airplanes; identified in Boeing Alert Service Bulletin 757-54A0047, 
Revision 5, dated June 9, 2011: Do a detailed inspection for 
cracking of the bulkhead in the area around the access door cutout 
and around the critical fasteners in the horizontal flange.

(n) New Compliance Times for Paragraph (m) of This AD

    At the applicable times specified in paragraphs (n)(1) and 
(n)(2) of this AD, do the actions required by paragraph (m) of this 
AD.
    (1) For Group 1, Configuration 1 airplanes identified in Boeing 
Alert Service Bulletin 757-54A0047, Revision 5, dated June 9, 2011: 
At the later of the times specified in paragraph (n)(1)(i) or 
(n)(1)(ii) of this AD.
    (i) Within 1,800 flight cycles after accomplishing the most 
recent inspection required by paragraph (h) or (j) 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 5, dated June 9, 2011: At the later of the times specified 
in paragraph (n)(2)(i) or (n)(2)(ii) of this AD.
    (i) Within 3,000 flight cycles after accomplishing the most 
recent inspection required by paragraph (h) or (j) of this AD.
    (ii) Within 90 days after the effective date of this AD.

(o) New Terminating Action for Certain Airplanes: Fastener Replacement

    For Group 1, Configuration 2 airplanes; and Group 2 airplanes; 
as identified in Boeing Alert Service Bulletin 757-54A0047, Revision 
5, dated June 9, 2011: Within 9,000 flight cycles or 54 months after 
the effective date of this AD, whichever occurs first, replace the 
horizontal and vertical flange fasteners in the strut-to-diagonal 
brace fitting on the number 1 and number 2 struts with new fasteners 
and do all related investigative and applicable corrective actions, 
in accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 757-54A0047, Revision 5, dated June 9, 2011, except 
where Boeing Alert Service Bulletin 757-54A0047, Revision 5, dated 
June 9, 2011, specifies to contact Boeing for repair instructions, 
before further flight, repair using a method approved in accordance 
with the procedures specified in paragraph (q) of this AD. Do all 
related investigative and corrective actions before further flight. 
Accomplishment of the actions required in paragraph (o) of this AD 
terminates the inspection requirements of paragraphs (g), (h), (j), 
and (m) of this AD for Group 1, Configuration 2 airplanes; and Group 
2 airplanes; as identified in Boeing Alert Service Bulletin 757-
54A0047, Revision 5, dated June 9, 2011.

(p) Credit for Previous Actions

    (1) Except for the actions specified in paragraphs (j), (m), and 
(o) of this AD, this paragraph provides credit for the actions 
required by paragraphs (g) and (h) of this AD, if those actions were 
done before March 18, 2008 (the effective date of AD 2008-05-10, 
Amendment 39-15404 (73 FR 11347, March 3, 2008), using Boeing 
Service Bulletin 757-54A0047, Revision 1, dated March 24, 2005; or 
Boeing Alert Service Bulletin 757-54A0047, Revision 2, dated January 
31, 2007.
    (2) This paragraph provides credit for the initial inspection 
required by paragraph (h) of this AD, if that inspection was done 
before June 29, 2005 (the effective date of AD 2005-12-04, Amendment 
39-14120 (70 FR 34313, June 14, 2005)), using the actions required 
by paragraph (b) or (d), as applicable, of AD 2004-12-07, Amendment 
39-13666 (69 FR 33561, June 16, 2004).

(q) Alternative Methods of Compliance (AMOCs)

    (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. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in the Related Information 
section of this AD. Information may be emailed to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD if it is approved by the 
Boeing Commercial Airplanes Organization Designation Authorization 
(ODA) that has been authorized by the Manager, Seattle ACO, to make 
those findings. For a repair method to be approved, the repair must 
meet the certification basis of the airplane and the approval must 
specifically refer to this AD.
    (4) AMOCs approved previously in accordance with AD 2004-12-07, 
Amendment 39-13666 (69 FR 33561, June 16, 2004), are approved as 
AMOCs for the corresponding provisions of this AD.
    (5) AMOCs approved previously in accordance with AD 2005-12-04, 
Amendment 39-14120 (70 FR 34313, June 14, 2005), are approved as 
AMOCs for the corresponding provisions of this AD.
    (6) AMOCs approved previously in accordance with AD 2007-16-13, 
Amendment 39-15152 (72 FR 44753, August 9, 2007), are approved as 
AMOCs for the corresponding provisions of this AD.
    (7) AMOCs approved previously in accordance with AD 2008-05-10, 
Amendment 39-15404 (73 FR 11347, March 3, 2008), are approved as 
AMOCs for the corresponding provisions of this AD.

(r) Related Information

    (1) 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; email: 
[email protected].
    (2) For service information identified in this AD, contact 
Boeing Commercial Airplanes, Attention: Data & Services Management, 
P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; phone: 206-
544-5000, extension 1; fax: 206-766-5680; Internet: https://www.myboeingfleet.com. You may review copies of the referenced 
service information at the FAA, Transport Airplane Directorate, 1601 
Lind Avenue SW., Renton, Washington. For information on the 
availability of this material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on June 14, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-15181 Filed 6-20-12; 8:45 am]
BILLING CODE 4910-13-P