Airworthiness Directives; The Boeing Company Airplanes

[Federal Register Volume 78, Number 13 (Friday, January 18, 2013)]
[Rules and Regulations]
[Pages 4042-4047]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-00897]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0724; Directorate Identifier 2010-NM-181-AD; 
Amendment 39-17299; AD 2012-26-04]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are superseding an existing airworthiness directive (AD) 
for certain The Boeing Company Model 757-200, -200PF, and -200CB series 
airplanes powered by Rolls-Royce engines. That AD currently 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. This new AD reduces the repetitive 
inspection interval; adds repetitive detailed inspections for cracking 
of the bulkhead, and repair if necessary; allows an extension of the 
repetitive intervals for certain airplanes by also doing repetitive 
ultrasonic inspections for cracking of the bulkhead, and repair if 
necessary; and provides an option for a high frequency eddy current 
inspection for cracking of the critical fastener holes, and repair if 
necessary. This action also adds a terminating action for certain 
repetitive inspections. 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.

DATES: This AD is effective February 22, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of February 22, 
2013.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of August 
24, 2007 (72 FR 44753, August 9, 2007).

ADDRESSES: For service information identified in this 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 AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (phone: 800-647-5527) is Document Management Facility, 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Nancy Marsh, Aerospace Engineer, 
Airframe Branch, ANM-120S, 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:

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 to supersede airworthiness directive (AD) 2008-05-
10, Amendment 39-15404 (73 FR 11347, March 3, 2008). (AD 2008-05-10 
superseded AD 2007-16-13, Amendment 39-15152 (72 FR 44753, August 9, 
2007); and AD 2007-16-13 superseded AD 2005-12-04, Amendment 39-14120 
(70 FR 34313, June 14, 2005).) AD 2008-05-10 applies to the specified 
products. The SNPRM published in the Federal Register on June 21, 2012 
(77 FR 37332). The original NPRM (76 FR 52901, August 24, 2011) 
proposed to continue to require repetitive inspections of the shim 
installation between the engine strut vertical flange and bulkhead, and 
repair if necessary. That NPRM also proposed to continue to require, 
for certain airplanes, inspecting 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, 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 add an option for a high frequency eddy 
current inspection for cracking of the critical fastener holes, and 
repair if necessary. The SNPRM proposed to add a terminating action for 
certain repetitive inspections.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
(77 FR 37332, June 21, 2012) and the FAA's response to each comment.

[[Page 4043]]

Support for the SNPRM (77 FR 37332, June 21, 2012)

    United Airlines (United) stated that it has 41 Model 757-200 
airplanes affected by the SNPRM (77 FR 37332, June 21, 2012). United 
stated that, in general, it concurs with the SNPRM to mandate the 
inspections and modifications described in Boeing Alert Service 
Bulletin 757-54A0047, Revision 5, dated June 9, 2011.
    UPS stated that it concurs with the reduced inspection interval 
specified in the SNPRM (77 FR 37332, June 21, 2012), as it provides 
additional opportunity beyond that required by AD 2008-05-10, Amendment 
39-15404 (73 FR 11347, March 3, 2008), to find and correct any damage.

Request To Change Compliance Time

    United requested that we remove the 54-month compliance time in 
favor of only a 9,000 airplane-cycle limit for the modification 
specified in paragraph (o) of the SNPRM (77 FR 37332, June 21, 2012). 
United stated that the 54-month compliance time does not align with 
current 72-month heavy check intervals at United. United stated that it 
understands the related bulkhead cracking to be a fatigue related 
failure, thus negating the need for a calendar driven modification 
limit. United stated it believes that the currently mandated repetitive 
inspection limits, in conjunction with a 9,000-airplane-cycle mandated 
modification limit only, would provide a safe program that would allow 
for a controlled implementation that minimizes the negative financial 
impact to operators.
    We disagree with the request to change the specified compliance 
time. We have determined that the 54-month compliance time (grace 
period), as specified in Boeing Alert Service Bulletin 757-54A0047, 
Revision 5, dated June 9, 2011, is necessary to adequately address the 
identified unsafe condition. This structure has been the subject of AD 
2008-05-10, Amendment 39-15404 (73 FR 11347, March 3, 2008); which 
superseded AD 2007-16-13, Amendment 39-15152 (72 FR 44753, August 9, 
2007); which superseded AD 2005-12-04, Amendment 39-14120 (70 FR 34313, 
June 14, 2005). In each of these ADs, the results from the new 
inspection found more damage than anticipated, and more frequent and 
complicated inspections were needed.
    In developing an appropriate compliance time for the modification 
specified in paragraph (o) of this AD, we considered the safety 
implications, the time necessary to design an acceptable modification, 
and normal maintenance schedules for timely accomplishment of the 
modification. In light of these items, we have determined that a 54-
month compliance time (grace period) is appropriate. However, under the 
provisions of paragraph (q) of this AD, we will consider requests for 
approval of an extension of the compliance time if sufficient data are 
submitted to substantiate that the extension would provide an 
acceptable level of safety. We have not changed the AD in this regard.

Request To Change Terminating Action

    UPS requested that the terminating action proposed in the SNPRM (77 
FR 37332, June 21, 2012) be optional in lieu of continued reduced 
interval inspections, and the terminating action be required only if 
the reduced interval inspections find cracks or other damage at the 
fitting.
    We do not agree to change the required terminating action specified 
in this AD because this portion of the Model 757 pylon has been the 
subject of AD 2008-05-10, Amendment 39-15404 (73 FR 11347, March 3, 
2008); which superseded AD 2007-16-13, Amendment 39-15152 (72 FR 44753, 
August 9, 2007); which superseded AD 2005-12-04, Amendment 39-14120 (70 
FR 34313, June 14, 2005). In each of these ADs, results from the new, 
more frequent, and more complicated inspections showed more damage than 
anticipated. Under the provisions of paragraph (q) of this AD, we will 
consider requests for approval of alternative methods of compliance 
(AMOC) if sufficient data are submitted to substantiate that continued 
inspections without the terminating action can mitigate the identified 
unsafe condition. We have not changed the AD in this regard.

Request To Specify Certain Section of Service Information

    Boeing requested that we specifically call out Part V of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 757-
54A0047, Revision 5, dated June 9, 2011, in paragraph (o) of the SNPRM 
(77 FR 37332, June 21, 2012) to prevent misinterpretation in that 
paragraph because it is different than all other locations in the 
SNPRM.
    We agree to specify Part V in paragraph (o) of this AD, as 
requested by Boeing, since doing so will help prevent 
misinterpretation. We have changed paragraph (o) of this AD to specify 
PART V of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 757-54A0047, Revision 5, dated June 9, 2011.

Request To Change Paragraph Header

    Boeing requested that we revise the header of paragraph (g) of the 
SNPRM (77 FR 37332, June 21, 2012), by deleting ``With Reduced 
Repetitive Intervals and New Optional Inspection Method.'' Boeing 
stated that there are no repetitive inspection requirements in 
paragraph (g) of the SNPRM.
    We agree to modify the specified header, since the repetitive 
inspection is specified in paragraph (h) of this AD. We have removed 
the words ``Reduced Repetitive Intervals and New Optional Inspection 
Interval'' from the header of paragraph (g) of this AD.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the changes described previously--and minor editorial 
changes. We have determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
SNPRM (77 FR 37332, June 21, 2012) for correcting the unsafe condition; 
and
    <bullet> Do not add any additional burden upon the public than was 
already proposed in the SNPRM (77 FR 37332, June 21, 2012).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of the AD.

Costs of Compliance

    We estimate that this AD affects 309 airplanes of U.S. registry.
    We estimate the following costs to comply with this 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 4044]]

 
Part II inspection on fasteners--  6 work-hours x $85                0  $510 per inspection  $157,590 per
 horizontal flange [retained        per hour = $510                      cycle.               inspection cycle.
 actions from AD 2008-05-10,        per inspection
 Amendment 39-15404 (73 FR 11347,   cycle.
 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                      cycle.               inspection cycle.
 [retained action from AD 2008-05-  per inspection
 10, Amendment 39-15404 (73 FR      cycle.
 11347, March 3, 2008)].
Part II additional inspection on   10 work-hours x $85               0  $850 per inspection  $262,650 per
 fasteners--horizontal flange       per hour = $850                      cycle.               inspection cycle.
 [new action].                      per inspection
                                    cycle.
Part IV inspection on critical     8 to 22 work-hours                0  $680 to $1,870 per   $210,120 to
 fasteners--horizontal flange       x $85 per hour =                     inspection cycle.    $577,830 per
 [new action].                      $680 to $1,870 per                                        inspection cycle.
                                    inspection cycle.
Part V fastener replacement        Up to 37 work-hours             750  Up to $3,895 per     Up to $1,203,555
 flange [new action].               x $85 per hour =                     strut.               per 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 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 AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The 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:

2012-26-04 The Boeing Company: Amendment 39-17299; Docket No. FAA-
2011-0724; Directorate Identifier 2010-NM-181-AD.

(a) Effective Date

    This airworthiness directive (AD) is effective February 22, 
2013.

(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

    This paragraph restates the one-time inspection and repair 
required by paragraph (g) of AD 2008-05-10, Amendment 39-15404 (73 
FR 11347, March 3, 2008), with optional inspection method and 
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 
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

[[Page 4045]]

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 of 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 the actions 
specified in 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 inspections 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 specified 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 specified in 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 and 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 Additional 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 March 18, 2008 (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 4046]]

(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 PART V of 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 
performed 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 (which are not incorporated by reference in this AD).
    (2) This paragraph provides credit for the initial inspection 
required by paragraph (h) of this AD, if that inspection was 
performed 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, 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 Boeing service information identified in this 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.

(s) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
February 22, 2013.
    (i) Boeing Alert Service Bulletin 757-54A0047, Revision 4, dated 
June 24, 2010.
    (ii) Boeing Alert Service Bulletin 757-54A0047, Revision 5, 
dated June 9, 2011.
    (4) The following service information was approved for IBR on 
August 24, 2007, (72 FR 44753, August 9, 2007).
    (i) Boeing Alert Service Bulletin 757-54A0047, Revision 3, dated 
June 27, 2007.
    (ii) Reserved.
    (5) For Boeing service information identified in this 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.

[[Page 4047]]

    (6) You may view this service information at 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.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton Washington, on December 17, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-00897 Filed 1-17-13; 8:45 am]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T02:57:33.135303+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

eaf6a00a29498f8163cfb9fe4de35b30ed62c82d99d367076db3cfe8706e5643

Text SHA-256

dc0d3bc9e7e2f509930a7683c0af824b9f4e3058ac9ff662795183c48ca760f6