Federal Register / Vol. 79, No. 52 / Tuesday, March 18, 2014 / Rules and Regulations 14987 

Service Bulletin 757–54–0028, dated March 

31, 1994, which is not incorporated by 

reference in this AD. 

(n) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Certification 

Office (ACO), FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (o)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane and the 

approval must specifically refer to this AD. 

(4) AMOCs approved for AD 2004–12–07, 

Amendment 39–13666 (69 FR 33561, June 

16, 2004), are approved as AMOCs for 

paragraphs (g) and (h) of this AD, except for 

AMOCs that approved a revised compliance 

time. 

(o) 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, WA 98057– 

3356; phone: 425–917–6440; fax: 425–917– 

6590; email: Nancy.Marsh@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be obtained at the addresses specified in 

paragraphs (p)(6) and (p)(7) of this AD. 

(p) 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 this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on April 22, 2014. 

(i) Boeing Service Bulletin 757–54–0003, 

Revision 1, dated August 30, 1985. 

(ii) Boeing Service Bulletin 757–54–0028, 

Revision 1, dated August 25, 1994. 

(iii) Boeing Service Bulletin 757–54–0035, 

Revision 6, dated December 2, 2011. 

(4) The following service information was 

approved for IBR on July 21, 2004 (69 FR 

33561, June 16, 2004). 

(i) Boeing Service Bulletin 757–54–0035, 

Revision 1, dated April 15, 1999. 

(ii) Boeing Service Bulletin 757–54–0035, 

Revision 2, dated June 13, 2002. 

(5) The following service information was 

approved for IBR on January 3, 2000 (64 FR 

66370, November 26, 1999). 

(i) Boeing Service Bulletin 757–54–0035, 

dated July 17, 1997. 

(ii) Reserved. 

(6) 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. 

(7) You may view copies of this 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. 

(8) 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/ibrlocations.html. 

Issued in Renton, Washington, on February 

19, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–04826 Filed 3–17–14; 8:45 am] 

BILLING CODE 4910–13–P 

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. 

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 


sroberts on DSK5SPTVN1PROD with RULES
14988 Federal Register / Vol. 79, No. 52 / Tuesday, March 18, 2014 / Rules and Regulations 

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, 


sroberts on DSK5SPTVN1PROD with RULES
Federal Register / Vol. 79, No. 52 / Tuesday, March 18, 2014 / Rules and Regulations 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 


sroberts on DSK5SPTVN1PROD with RULES
14990 Federal Register / Vol. 79, No. 52 / Tuesday, March 18, 2014 / Rules and Regulations 

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

Action Labor cost Parts 

cost Cost per product Cost on U.S. operators 

Inspect/replace bolts (Condition 1 in 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).

5 work-hours × $85 per 

hour = $425 per inspection cycle.

$217 $642 per inspection 

cycle.

$439,770 per inspection 

cycle 

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

Action Labor cost Parts cost Cost per 

product 

Replace rudder pedal assembly (Condition 2 in 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 work-hours × $85 per hour = $170 Unknown .... $170 

Repair rudder pedal assembly (Condition 3 in 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 work-hours × $85 per hour = $255 Unknown .... $255 


sroberts on DSK5SPTVN1PROD with RULES
Federal Register / Vol. 79, No. 52 / Tuesday, March 18, 2014 / Rules and Regulations 14991 

ON-CONDITION COSTS—Continued 

Action Labor cost Parts cost Cost per 

product 

Repair rudder pedal assembly (Condition 4 in 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).

4 work-hours × $85 per hour = $340 Unknown .... $340 

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 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 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 nosewheel 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 


sroberts on DSK5SPTVN1PROD with RULES
14992 Federal Register / Vol. 79, No. 52 / Tuesday, March 18, 2014 / Rules and Regulations 

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-AMOCRequests@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/ibrlocations.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 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0327; Directorate 

Identifier 2011–NM–161–AD; Amendment 

39–17794; AD 2014–05–21] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2008–11– 

04 for all The Boeing Company Model 

737–100, –200, –200C, –300, –400, and 

–500 series airplanes. AD 2008–11–04 

required repetitive inspections for 

cracking in and around the upper and 

lower hinge cutouts of the forward entry 

and forward galley service doorways, 

and corrective actions if necessary. This 

new AD reduces the inspection 

threshold for cracking in and around the 

galley service doorway hinge cutouts, 

adds inspections of certain repaired 

structure at the forward entry and galley 

service doorway upper and lower hinge 

cutouts, expands the inspection area at 

the forward entry and galley service 

doorway upper and lower hinge cutouts, 

and removes certain airplanes from the 

applicability. This AD was prompted by 

multiple reports of cracks in the skin 

and/or bear strap at the forward galley 

service doorway hinge cutouts, and 

multiple reports of cracking under the 

repairs installed at the hinge cutouts. 

We are issuing this AD to detect and 

correct such cracking, which could 

result in rapid decompression of the 

airplane. 

DATES: This AD is effective April 22, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 22, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of June 25, 2008 (73 FR 

29421, May 21, 2008). 

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 view 

this referenced service information at 

the FAA, Transport Airplane 


sroberts on DSK5SPTVN1PROD with RULES