Document ID: FAA-2013-0369-0007
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: The Boeing Company Airplanes
Posted Date: 2014-03-18T04:00Z

[Federal Register Volume 79, Number 52 (Tuesday, March 18, 2014)]
[Rules and Regulations]
[Pages 14987-14992]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-04843]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0369; Directorate Identifier 2012-NM-128-AD; 
Amendment 39-17793; AD 2014-05-20]
RIN 2120-AA64

Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all The 
Boeing Company Model 757 airplanes. This AD was prompted by reports of 
fractured rudder pedal pushrod connecting bolts in a rudder pedal 
assembly. This AD requires repetitive replacements of the rudder pedal 
pushrod connecting bolts and repetitive inspections of the rudder pedal 
assembly bolt holes in each of the captain and the first officer rudder 
pedal assemblies, and if necessary, repair or replacement of worn 
rudder pedal assemblies. We are issuing this AD to prevent fracture of 
the rudder pedal pushrod connecting bolts during pedal use, which could 
result in large involuntary inputs to the rudder and nose-wheel 
steering and an asymmetric application of braking, if pedal brakes are 
applied, leading to a runway excursion.

DATES: This AD is effective April 22, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of April 22, 
2014.

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; telephone 206-544-
5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information 
at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., 
Renton, Washington 98057-3356. 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 by searching for and locating Docket No. FAA-2013-
0369; 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 Docket 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: Marie Hogestad, Aerospace Engineer, 
Systems and Equipment Branch, ANM-130S, Seattle Aircraft Certification 
Office, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-
917-6418; fax: 425-917-6590; email: marie.hogestad@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all The Boeing Company 
Model 757 airplanes. The NPRM published in the Federal Register on May 
10, 2013 (78 FR 27315). The NPRM was prompted by reports of fractured 
rudder pedal pushrod connecting bolts in a rudder pedal assembly. The 
NPRM proposed to require repetitive

[[Page 14988]]

replacements of the rudder pedal pushrod connecting bolts and 
repetitive inspections of the rudder pedal assembly bolt holes in each 
of the captain and the first officer rudder pedal assemblies, and if 
necessary, repair or replacement of worn rudder pedal assemblies. We 
are issuing this AD to prevent fracture of the rudder pedal pushrod 
connecting bolts during pedal use, which could result in large 
involuntary inputs to the rudder and nose-wheel steering and an 
asymmetric application of braking, if pedal brakes are applied, leading 
to a runway excursion.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the proposal 
(78 FR 27315, May 10, 2013) and the FAA's response to each comment.

Request To Reduce the Compliance Time

    Air Line Pilots Association International (the commenter) stated 
that it agrees with the intent of the NPRM (78 FR 27315, May 10, 2013), 
but requested that we reduce the compliance time from 60 months to 24 
months. The commenter provided no justification for this request.
    We disagree with the request to revise the compliance time in this 
final rule. In developing the compliance time for this final rule, we 
considered not only the safety implications of the identified unsafe 
condition, but also the average utilization rate of the affected fleet, 
the practical aspects of an orderly modification of the fleet, the 
availability of required parts, and the time necessary for the 
rulemaking process. We find that the compliance time, as proposed, 
adequately represents an appropriate interval of time in which the 
required actions can be performed in a timely manner within the 
affected fleet, while still maintaining an adequate level of safety. We 
have not changed this final rule in this regard.

Request To Clarify the Unsafe Condition

    Boeing requested that we revise the unsafe condition in the NPRM 
(78 FR 27315, May 10, 2013), and suggested language to clarify the 
expectation of asymmetric braking, in the event of fracture of the 
subject bolt. Boeing added that symmetric braking inputs prior to 
fracture can become asymmetric following bolt fracture due to loss of 
brake inputs on the affected side.
    We agree with the request to revise the unsafe condition for the 
reasons provided by Boeing. We have revised this final rule to reflect 
the revised language.

Request To Use One Service Bulletin Revision

    Aviation Technical Services, Inc. (the commenter) requested that we 
revise the NPRM (78 FR 27315, May 10, 2013) to mandate only one version 
of the service information. The commenter also requested that we 
require that Boeing combine both versions of the service bulletin 
specified in the NPRM, into one final revision. The commenter reasoned 
that having two versions of the service bulletin will require operators 
and maintenance providers to integrate the two service bulletins in 
order to comply with the NPRM. The commenter expressed that this burden 
should be on the original equipment manufacturer (OEM) and the FAA.
    The commenter also requested that to further determine the adequacy 
of Boeing Alert Service Bulletin 757-27A0153, dated May 9, 2012, as 
revised by Boeing Alert Service Bulletin 757-27A0153, Revision 1, dated 
October 29, 2012, the FAA should use its own guidance, as provided by 
FAA Advisory Circular (AC) 20-176, dated December 19, 2011 (http://
rgl.avs.faa.gov/Regulatory--and--Guidance--Library/
rgAdvisoryCircular.nsf/0/a78cc91a47b192278625796b0075f419/$FILE/
AC%2020-176.pdf).
    We disagree with the request to provide a single service bulletin 
version for the required method of compliance. Boeing Alert Service 
Bulletin 757-27A0153, Revision 1, dated October 29, 2012, includes only 
minor corrections to washer part numbers in top kit 012N8932-21 and an 
additional instruction for getting better access, if necessary, for the 
detailed inspections required by this final rule. It is not necessary 
that Boeing combine both revisions of the referenced service bulletin 
into one final revision.
    Also, the design approval holder (DAH) followed the guidance in FAA 
AC 20-176, dated December 19, 2011 (http://rgl.avs.faa.gov/Regulatory--
and--Guidance--Library/rgAdvisoryCircular.nsf/0/
a78cc91a47b192278625796b0075f419/$FILE/AC%2020-176.pdf). We approved 
Boeing Alert Service Bulletin 757-27A0153, dated May 9, 2012, as 
revised by Boeing Alert Service Bulletin 757-27A0153, Revision 1, dated 
October 29, 2012, using the guidance in FAA Order 8110.117, dated 
September 12, 2012 (http://rgl.avs.faa.gov/Regulatory--and--Guidance--
Library/rgOrders.nsf/0/984bb9eb07cdd86986257a7f0070744c/$FILE/
Order%208110.117.pdf). (Refer to Section 2-11, ``Streamlining 
Development and Revision of SBs,'' paragraph (c)(5), ``Partial Revision 
Process--A process in which only changed information in a service 
bulletin is sent to affected customers,'' of FAA AC 20-176, dated 
December 19, 2011.) We have not changed this final rule in this regard.

Request for Additional Guidance

    Aviation Technical Services, Inc. (the commenter) requested that we 
revise the NPRM (78 FR 27315, May 10, 2013) to provide sufficient 
instruction to determine the installation finish associated with the 
replacement bushing for the rudder pedal pushrod. The commenter 
reasoned that the instructions provided by Boeing Alert Service 
Bulletin 757-27A0153, dated May 9, 2012, as revised by Boeing Alert 
Service Bulletin 757-27A0153, Revision 1, dated October 29, 2012, refer 
to Boeing Standard Overhaul Practices Manual (SOPM) 20-50-03 for the 
shrink fit procedure to install repair bushings, and that the SOPM 
procedure contain instructions such as: ``Apply the specified 
installation finish. . . .'' and ``Refer to the overhaul instructions 
for applicable operations. . . .'' The commenter asserted that neither 
Boeing Alert Service Bulletin 757-27A0153, dated May 9, 2012, as 
revised by Boeing Alert Service Bulletin 757-27A0153, Revision 1, dated 
October 29, 2012, nor the SOPM provide sufficient instruction to 
determine the installation finish associated with the replacement 
bushing for the rudder pedal pushrod.
    We disagree to revise this final rule. Step 4 of Figures 3 and 4 of 
the Accomplishment Instructions of Boeing Alert Service Bulletin 757-
27A0153, dated May 9, 2012, as revised by Boeing Alert Service Bulletin 
757-27A0153, Revision 1, dated October 29, 2012, already provides 
procedures for installing bushing 001N0004-1 with BMS 5-95 sealant, as 
specified in ``the shrink fit'' procedure referred to in Standard 
Overhaul Practices Manual (SOPM) 20-50-03 (bushing 001N0004-1 is 
already finished). SOPM 20-50-03 Bearing and Bushing Replacement, 
Paragraph 7.B, ``Shrink Fit (Temperature Differential) Procedure,'' 
specifies, among other things, to apply the specified installation 
finish ``as specified in Paragraph 6B,'' which, in turn, specifies 
``Installation with sealant.'' The finish is, in this case, the sealant 
that is used during the installation (BMS 5-95). Therefore, Boeing 
Alert Service Bulletin 757-27A0153, dated May 9, 2012, as revised by 
Boeing Alert Service Bulletin 757-27A0153, Revision 1, dated October 
29,

[[Page 14989]]

2012, in combination with SOPM 20-50-03, provide sufficient 
instructions to install the bushing. We have not changed the AD in this 
regard.

Request To Match Terminology

    American Airlines (AAL) requested that we revise the NPRM (78 FR 
27315, May 10, 2013) to match certain wording in Boeing Alert Service 
Bulletin 757-27A0153, dated May 9, 2012, as revised by Boeing Alert 
Service Bulletin 757-27A0153, Revision 1, dated October 29, 2012. AAL 
explained that Boeing Alert Service Bulletin 757-27A0153, dated May 9, 
2012, as revised by Boeing Alert Service Bulletin 757-27A0153, Revision 
1, dated October 29, 2012, refers to bolt part number (P/N) 
BACB30NM5DK47 as changed to P/N BACB30UU5K48D as the rudder pedal 
pushrod bolt, while the NPRM refers to this part number as the rudder 
pedal pushrod connecting bolt. AAL expressed that matching the 
terminology in Boeing Alert Service Bulletin 757-27A0153, dated May 9, 
2012, as revised by Boeing Alert Service Bulletin 757-27A0153, Revision 
1, dated October 29, 2012, would eliminate any possible confusion.
    We disagree with the request to match the terminology in this final 
rule with the terminology found in Boeing Alert Service Bulletin 757-
27A0153, dated May 9, 2012, as revised by Boeing Alert Service Bulletin 
757-27A0153, Revision 1, dated October 29, 2012. The word 
``connecting'' was added in the NPRM (78 FR 27315, May 10, 2013) to 
further clarify that this bolt secures the rudder pedal arm to the 
rudder pushrod. We have not changed this final rule in this regard.

Request To Use Specific Instructions

    AAL requested that we revise the NPRM (78 FR 27315, May 10, 2013) 
to require only those instructions that correct the unsafe condition. 
AAL explained that paragraphs (g) and (h) of the NPRM are more 
restrictive than necessary to ensure safety of flight, and that the 
Accomplishment Instructions of Boeing Alert Service Bulletin 757-
27A0153, dated May 9, 2012, as revised by Boeing Alert Service Bulletin 
757-27A0153, Revision 1, dated October 29, 2012, should not be mandated 
in their entirety.
    AAL requested the following revisions to certain paragraphs of the 
NPRM (78 FR 27315, May 10, 2013):
     Since paragraph (g) of the NPRM (78 FR 27315, May 10, 
2013) specified a detailed inspection of the rudder pedal assembly bolt 
holes, the only procedure that should be mandated by this paragraph is 
FIGURE 1 of the Accomplishment Instructions of Boeing Alert Service 
Bulletin 757-27A0153, dated May 9, 2012, as revised by Boeing Alert 
Service Bulletin 757-27A0153, Revision 1, dated October 29, 2012.
     Since paragraph (h)(1) of the NPRM (78 FR 27315, May 10, 
2013) specified replacement of a new bolt, washer, nut, and cotter pin, 
the only procedure that should be mandated by this paragraph is FIGURE 
2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 
757-27A0153, dated May 9, 2012, as revised by Boeing Alert Service 
Bulletin 757-27A0153, Revision 1, dated October 29, 2012.
     Paragraph (h)(2)(i) of the NPRM (78 FR 27315, May 10, 
2013) should be revised as follows: ``Install a new rudder pedal 
assembly in accordance with `Condition 2' of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-27A0153, dated May 9, 
2012, as revised by Boeing Alert Service Bulletin 757-27A0153, Revision 
1, dated October 29, 2012; or install a bushing in the worn hole in 
accordance with FIGURE 3 of the Accomplishment Instructions of Boeing 
Alert Service Bulletin 757-27A0153, dated May 9, 2012, as revised by 
Boeing Alert Service Bulletin 757-27A0153, Revision 1, dated October 
29, 2012.''
     Paragraph (h)(2)(ii) of the NPRM (78 FR 27315, May 10, 
2013) specified installation of a new bolt, washer, nut, and cotter pin 
in accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 757-27A0153, dated May 9, 2012, as revised by Boeing 
Alert Service Bulletin 757-27A0153, Revision 1, dated October 29, 2012. 
However, Boeing Alert Service Bulletin 757-27A0153, dated May 9, 2012, 
as revised by Boeing Alert Service Bulletin 757-27A0153, Revision 1, 
dated October 29, 2012, does not provide explicit instructions to 
replace the bolt, washer, nut, and cotter pin in the event that the 
diameter of only one hole is greater than 0.3140 inch. There is only a 
note in the procedure to make sure to discard the existing hardware, 
and to install new hardware as provided in Boeing Kit 0l2N8932-21.
    AAL has determined that the instructions provided in FIGURE 2 of 
the Accomplishment Instructions of Boeing Alert Service Bulletin 757-
27A0153, dated May 9, 2012, as revised by Boeing Alert Service Bulletin 
757-27A0153, Revision 1, dated October 29, 2012, contain the proper 
instructions and part numbers to replace the bolt, washer, nut, and 
cotter pin to correct the unsafe condition. Therefore, the only 
procedure that should be mandated by this paragraph is FIGURE 2 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 757-
27A0153, dated May 9, 2012, as revised by Boeing Alert Service Bulletin 
757-27A0153, Revision 1, dated October 29, 2012.
     Paragraph (h)(3)(i) of the NPRM (78 FR 27315, May 10, 
2013) should be revised as follows: ``Install a new rudder pedal 
assembly in accordance with `Condition 2' of the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-27A0153, dated May 9, 
2012, as revised by Boeing Alert Service Bulletin 757-27A0153, Revision 
1, dated October 29, 2012, or install two bushings in the two worn 
holes in accordance with FIGURE 4 of the Accomplishment Instructions of 
Boeing Alert Service Bulletin757-27A0153, dated May 9, 2012, as revised 
by Boeing Alert Service Bulletin 757-27A0153, Revision 1, dated October 
29, 2012.''
     Paragraph (h)(3)(ii) of the NPRM (78 FR 27315, May 10, 
2013) requires installation of a new bolt, washer, nut, and cotter pin 
in accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 757-27A0153, dated May 9, 2012, as revised by Boeing 
Alert Service Bulletin 757-27A0153, Revision 1, dated October 29, 2012. 
However, Boeing Alert Service Bulletin 757-27A0153, dated May 9, 2012, 
as revised by Boeing Alert Service Bulletin 757-27A0153, Revision 1, 
dated October 29, 2012, does not provide explicit instructions to 
replace the bolt, washer, nut, and cotter pin in the event that the 
diameters of both holes are greater than 0.3140 inch. Again, there is 
only a note in the procedure to make sure to discard the existing 
hardware, and to install new hardware as provided in Boeing Kit 
012N8932-21.
    AAL has determined that the instructions provided in FIGURE 2 of 
the Accomplishment Instructions of Boeing Alert Service Bulletin 757-
27A0153, dated May 9, 2012, as revised by Boeing Alert Service Bulletin 
757-27A0153, Revision 1, dated October 29, 2012, contain the proper 
instructions and part numbers to replace the bolt, washer, nut, and 
cotter pin to correct the unsafe condition. Therefore, the only 
procedure that should be mandated by this paragraph is FIGURE 2 of the 
Accomplishment Instructions of Boeing Alert Service Bulletin 757-
27A0153, dated May 9, 2012, as revised by Boeing Alert Service Bulletin 
757-27A0153, Revision 1, dated October 29, 2012.
    We agree with the concept of minimizing AD requirements when 
appropriate. However, we do not agree with AAL's request. The FAA 
worked in conjunction with industry, under the Airworthiness Directives 
Implementation Aviation Rulemaking Committee (ARC), to enhance the AD 
system. One enhancement is a new

[[Page 14990]]

process for annotating which steps in the service information are 
``required for compliance'' (RC) with an AD. Differentiating these 
steps from other tasks in the service information is expected to 
improve an owner's/operator's understanding of AD requirements and help 
provide consistent judgment in AD compliance.
    In response to the AD Implementation ARC, the FAA released AC 20-
176, dated December 19, 2011 (http://rgl.avs.faa.gov/Regulatory--and--
Guidance--Library/rgAdvisoryCircular.nsf/0/
a78cc91a47b192278625796b0075f419/$FILE/AC%2020-176.pdf); and Order 
8110.117, dated September 12, 2012 (http://rgl.avs.faa.gov/Regulatory--
and--Guidance--Library/rgOrders.nsf/0/984bb9eb07cdd86986257a7f0070744c/
$FILE/Order%208110.117.pdf), which include the concept of RC. The FAA 
has begun implementing this concept in ADs when we receive service 
information containing RC steps. While some design approval holders 
have implemented the RC concept, the implementation is voluntary. The 
FAA does not intend to develop or revise AD requirements to incorporate 
the RC concept if it is not included in the service information.
    Contrary to AAL's statement that ADs should mandate only those 
service bulletin provisions that are ``necessary to ensure safety of 
flight,'' ADs generally contain requirements that are reasonably 
related to addressing the unsafe condition, as determined by the FAA 
and the design approval holder that developed the service bulletin. 
Typically, operators' maintenance programs were not developed in 
recognition of the unsafe condition that is being addressed by an AD. 
Whenever we issue an AD, those programs had failed to prevent the 
unsafe condition in the first place. Therefore, many provisions of ADs 
address aspects of accomplishing the required maintenance that are 
necessary to prevent operators from inadvertently aggravating the 
unsafe condition or introducing new unsafe conditions.
    For many years, the Air Transport Association (now Airlines for 
America, A4A) has sponsored the ``Lead Airline'' program through which 
individual airlines are provided an opportunity to prototype 
manufacturers' draft service instructions before they are finalized. 
One objective of this activity is to minimize the procedures included 
in the instructions that are considered unnecessary. Therefore, when 
the FAA receives a manufacturer's service bulletin, we recognize that 
the procedures specified have been determined to be necessary by both 
the manufacturer and affected operators. As in this case, the 
instructions provided in service bulletins referenced in ADs are 
reasonably related to addressing the unsafe condition.
    As always, if AAL or any other operator prefers to address the 
unsafe condition by means other than those specified in the referenced 
service information, they may request approval for an alternative 
method of compliance and, if approved, may use it instead of the 
procedures specified in the service information.
    Therefore, no changes have been made to this final rule in this 
regard.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 27315, May 10, 2013) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 27315, May 10, 2013).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this AD affects 685 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                            Parts                               Cost on U.S.
              Action                      Labor cost         cost      Cost per product          operators
----------------------------------------------------------------------------------------------------------------
Inspect/replace bolts (Condition 1  5 work-hours x $85        $217  $642 per inspection    $439,770 per
 in the Accomplishment               per hour = $425 per             cycle.                 inspection cycle
 Instructions of Boeing Alert        inspection cycle.
 Service Bulletin 757-27A0153,
 dated May 9, 2012, as revised by
 Boeing Alert Service Bulletin 757-
 27A0153, Revision 1, dated
 October 29, 2012).
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs/
replacements that would be required based on the results of the 
inspection. We have no way of determining the number of aircraft that 
might need these repairs/replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                       Cost per
                     Action                               Labor cost                Parts cost          product
----------------------------------------------------------------------------------------------------------------
Replace rudder pedal assembly (Condition 2 in    2 work-hours x $85 per hour  Unknown...............        $170
 the Accomplishment Instructions of Boeing        = $170.
 Alert Service Bulletin 757-27A0153, dated May
 9, 2012, as revised by Boeing Alert Service
 Bulletin 757-27A0153, Revision 1, dated
 October 29, 2012).
Repair rudder pedal assembly (Condition 3 in     3 work-hours x $85 per hour  Unknown...............        $255
 the Accomplishment Instructions of Boeing        = $255.
 Alert Service Bulletin 757-27A0153, dated May
 9, 2012, as revised by Boeing Alert Service
 Bulletin 757-27A0153, Revision 1, dated
 October 29, 2012).

[[Page 14991]]

 
Repair rudder pedal assembly (Condition 4 in     4 work-hours x $85 per hour  Unknown...............        $340
 the Accomplishment Instructions of Boeing        = $340.
 Alert Service Bulletin 757-27A0153, dated May
 9, 2012, as revised by Boeing Alert Service
 Bulletin 757-27A0153, Revision 1, dated
 October 29, 2012).
----------------------------------------------------------------------------------------------------------------

    The on-condition costs in the table above are per rudder pedal 
assembly. Depending on the diameter of the holes found during the 
inspection, it may be necessary to replace or repair the rudder pedal 
assemblies. The parts cost to replace or repair the rudder pedal 
assemblies are not included in the estimate; it is considered ``Parts & 
Materials Supplied by the Operator,'' which is referenced in Boeing 
Alert Service Bulletin 757-27A0153, dated May 9, 2012, as revised by 
Boeing Alert Service Bulletin 757-27A0153, Revision 1, dated October 
29, 2012.
    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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

    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 adding the following new airworthiness 
directive (AD):

2014-05-20 The Boeing Company: Amendment 39-17793; Docket No. FAA-
2013-0369; Directorate Identifier 2012-NM-128-AD.

(a) Effective Date

    This AD is effective April 22, 2014.

(b) Affected ADs

    Certain requirements of this AD terminate the requirements of AD 
2001-22-13, Amendment 39-12492 (66 FR 55075, November 1, 2001), for 
Model 757 airplanes.

(c) Applicability

    This AD applies to all The Boeing Company Model 757-200, -200PF, 
-200CB, and -300 series airplanes, certificated in any category.

(d) Subject

    Air Transport Association (ATA) of America Code 27, Flight 
Controls.

(e) Unsafe Condition

    This AD was prompted by reports of fractured rudder pedal 
pushrod connecting bolts in the rudder pedal assembly. We are 
issuing this AD to prevent fracture of the rudder pedal pushrod 
connecting bolts during pedal use, which could result in large 
involuntary inputs to the rudder and nose-wheel steering and an 
asymmetric application of braking, if pedal brakes are applied, 
leading to a runway excursion.

(f) Compliance

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

(g) Inspection

    Within 60 months after the effective date of this AD, do a 
detailed inspection of the rudder pedal assembly bolt holes to 
determine the diameter in each of the captain and the first officer 
rudder pedal assemblies, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-27A0153, dated May 
9, 2012, as revised by Boeing Alert Service Bulletin 757-27A0153, 
Revision 1, dated October 29, 2012. Repeat this inspection 
thereafter at intervals not to exceed 15,000 flight cycles.

 (h) Installation

    Do the applicable actions specified in paragraph (h)(1), (h)(2), 
or (h)(3) of this AD for each of the captain and first officer 
rudder pedal assemblies, based on the results of any inspection 
required by paragraph (g) of this AD. Accomplishment of paragraph 
(h)(1), (h)(2), or (h)(3) of this AD terminates the requirements of 
AD 2001-22-13, Amendment 39-12492 (66 FR 55075, November 1, 2001), 
for that Model 757 airplane only.
    (1) If the diameters of both holes are within 0.3120 and 0.3140 
inch on the assembly, before further flight, install a new rudder 
pedal pushrod connecting bolt, washer, nut, and cotter pin, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 757-27A0153, dated May 9, 2012, as revised by 
Boeing Alert Service Bulletin 757-27A0153, Revision 1, dated October 
29, 2012.
    (2) If the diameter of only one hole is greater than 0.3140 inch 
on the assembly, before further flight, do the actions specified in 
paragraphs (h)(2)(i) and (h)(2)(ii) of this AD.
    (i) Install a new rudder pedal assembly, or install a bushing in 
the worn hole, in accordance with the Accomplishment

[[Page 14992]]

Instructions of Boeing Alert Service Bulletin 757-27A0153, dated May 
9, 2012, as revised by Boeing Alert Service Bulletin 757-27A0153, 
Revision 1, dated October 29, 2012.
    (ii) Install a new rudder pedal pushrod connecting bolt, washer, 
nut, and cotter pin, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-27A0153, dated May 
9, 2012, as revised by Boeing Alert Service Bulletin 757-27A0153, 
Revision 1, dated October 29, 2012.
    (3) If the diameters of both holes are greater than 0.3140 inch 
on the assembly, before further flight, do the actions specified in 
paragraphs (h)(3)(i) and (h)(3)(ii) of this AD.
    (i) Install a new rudder pedal assembly, or install two bushings 
in the two worn holes, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-27A0153, dated May 
9, 2012, as revised by Boeing Alert Service Bulletin 757-27A0153, 
Revision 1, dated October 29, 2012.
    (ii) Install a new rudder pedal pushrod connecting bolt, washer, 
nut, and cotter pin, in accordance with the Accomplishment 
Instructions of Boeing Alert Service Bulletin 757-27A0153, dated May 
9, 2012, as revised by Boeing Alert Service Bulletin 757-27A0153, 
Revision 1, dated October 29, 2012.

 (i) Parts Installation Prohibition

    As of the effective date of this AD, no person may install, in a 
rudder pedal assembly of any Boeing Model 757 airplane, a bolt 
having part number (P/N) BACB30NM5DK47.

 (j) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraphs (g) and (h) of this AD, if operators installed washers 
having P/N NAS1149D0516J, NAS1149D0532J, and NAS1149D0563J, and if 
those actions were performed before the effective date of this AD 
using Boeing Alert Service Bulletin 757-27A0153, dated May 9, 2012, 
as unmodified by Boeing Alert Service Bulletin 757-27A0153, Revision 
1, dated October 29, 2012.

(k) 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 paragraph (l)(1) of this AD. 
Information may be emailed 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.

(l) Related Information

    (1) For more information about this AD, contact Marie Hogestad, 
Aerospace Engineer, Systems and Equipment Branch, ANM-130S, Seattle 
Aircraft Certification Office, FAA, 1601 Lind Avenue SW., Renton, WA 
98057-3356; phone: 425-917-6418; fax: 425-917-6590; email: 
marie.hogestad@faa.gov.
    (2) Service information identified in this AD that is not 
incorporated by reference in this AD may be obtained at the address 
specified in paragraphs (m)(3) and (m)(4) of this AD.

(m) 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.
    (i) Boeing Alert Service Bulletin 757-27A0153, dated May 9, 
2012.
    (ii) Boeing Alert Service Bulletin 757-27A0153, Revision 1, 
dated October 29, 2012.
    (3) 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; 
telephone 206-544-5000, extension 1; fax 206-766-5680; Internet 
https://www.myboeingfleet.com.
    (4) You may view this service information at FAA, 1601 Lind 
Avenue SW., Renton, WA 98057-3356. For information on the 
availability of this material at the FAA, call 425-227-1221.
    (5) 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 February 19, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-04843 Filed 3-17-14; 8:45 am]
BILLING CODE 4910-13-P