69744 Federal Register / Vol. 77, No. 225 / Wednesday, November 21, 2012 / Rules and Regulations 

Meacham Blvd., Fort Worth, Texas 76137; 

phone: (817) 222–5038; fax: (817) 222–5160; 

email: michael.a.heusser@faa.gov. 

(2) For service information identified in 

this AD, contact Sierra Industries, Ltd., 122 

Howard Langford Drive, Uvalde, Texas 

78801; telephone: 888–835–9377; email: 

chip@sijet.com; Internet: http:// 

www.sijet.com/r-stol-high. You may review 

copies of the service information at the FAA, 

Small Airplane Directorate, 901 Locust, 

Kansas City, Missouri 64106. For information 

on the availability of this material at the 

FAA, call 816–329–4148. 

(l) 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 the service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Sierra Industries, Ltd. Service Bulletin 

SI09–82 Series-1, Rev. A, dated June 12, 

2012. 

(ii) Sierra Industries, Ltd. Instructions for 

Continued Airworthiness, 82–1, Issue 1, 

dated June 12, 2012. 

(3) For Sierra Industries, Ltd. service 

information identified in this AD, contact 

Sierra Industries, Ltd., 122 Howard Langford 

Drive, Uvalde, Texas 78801; telephone: 888– 

835–9377; email: chip@sijet.com; Internet: 

http://www.sijet.com/r-stol-high. 

(4) You may view this service information 

at FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call 816–329–4148. 

(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 Kansas City, Missouri, on 

November 5, 2012. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–27456 Filed 11–20–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1168; Directorate 

Identifier 2010–NM–239–AD; Amendment 

39–17255; AD 2012–22–17] 

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 certain 

The Boeing Company Model 767–200 

and –300 series airplanes. This AD was 

prompted by reports of cracks in the 

inner chords at both left-side and rightside stations 859.5, 883.5, and 903.5. 

This AD requires repetitive inspections 

of the frame inner chord transition 

radius for cracks, and related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

prevent large cracks in the frames and 

adjacent structure that can adversely 

affect the structural integrity of the 

airplane. 

DATES: This AD is effective December 

26, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 26, 2012. 

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 

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: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6577; 

fax: 425–917–6590; email: 

Berhane.Alazar@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM published in the Federal 

Register on November 9, 2011 (76 FR 

69685). That NPRM proposed to require 

repetitive inspections of the frame inner 

chord transition radius for cracks, and 

related investigative and corrective 

actions if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (76 FR 69685, 

November 9, 2011) and the FAA’s 

response to each comment. 

Statement of Intent To Comply With the 

NPRM (76 FR 69685, November 9, 

2011) 

American Airlines stated that it will 

incorporate the NPRM (76 FR 69685, 

November 9, 2011) requirements into its 

maintenance program and that any 

corrective actions will be performed at 

a time that is appropriate based on the 

compliance thresholds in the NPRM. 

Request To Revise Note 1 to Paragraph 

(g) of the NPRM (76 FR 69685, 

November 9, 2011) 

Boeing requested that we revise the 

wording of Note 1 to paragraph (g) of the 

NPRM (76 FR 69685, November 9, 2011) 

to clarify that structural inspections of 

fuselage structure are mandated by AD 

2003–18–10, Amendment 39–13301 (68 

FR 53503, September 11, 2003). (AD 

2003–18–10 requires revising the 

airworthiness limitations section of the 

maintenance planning data document to 

incorporate certain inspections and 

compliance times to detect fatigue 

cracking of principal structural 

elements.) Boeing stated that an 

alteration of these structural inspections 

will be required for repair(s) done in 

accordance with Boeing Service Bulletin 

767–53A0209, Revision 1, dated July 27, 

2011. That service bulletin contains 

post-repair inspections that already 

provide alternative method of 

compliance (AMOC) coverage for the 

requirements of AD 2003–18–10. 

We disagree with the commenter’s 

request. Paragraph F., ‘‘Approval,’’ of 

Boeing Service Bulletin 767–53A0209, 

Revision 1, dated July 27, 2011, already 

contains approval of the inspections as 

an AMOC for the requirements of the 

pertinent paragraphs of AD 2003–18–10, 

Amendment 39–13301 (68 FR 53503, 

September 11, 2003). We have not 

changed the final rule in this regard. 


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Federal Register / Vol. 77, No. 225 / Wednesday, November 21, 2012 / Rules and Regulations 69745 

Request To Exclude Certain Inspections 

All Nippon Airways (ANA) requested 

that we include a statement in the 

proposed requirements of the NPRM (76 

FR 69685, November 9, 2011) to give 

credit for the inspection at the locations 

where FAA-approved repairs have been 

accomplished for the subject cracking of 

the inner chords prior to the release of 

Boeing Service Bulletin 767–53A0209, 

Revision 1, dated July 27, 2011. ANA 

stated that Boeing Service Bulletin 767– 

53A0209, Revision 1, dated July 27, 

2011, does not describe how operators 

treat the previously FAA-approved 

repairs and that a credit statement was 

included in the service information 

referenced in AD 2011–02–06, 

Amendment 39–16579 (76 FR 4224, 

January 25, 2011). ANA stated that it 

would have to obtain approvals for all 

previously FAA-approved repairs as 

AMOCs to the new AD; and considered 

this a huge burden that increases costs 

and work-hours. 

We disagree with the commenter’s 

request. The structural issues in the 

identified unsafe condition for this AD 

are significantly different and more 

complex than those addressed by AD 

2011–02–06, Amendment 39–16579 (76 

FR 4224, January 25, 2011). We are 

unable to approve AMOCs for repairs 

that may have had previous FAA 

approvals without information as to 

how they mitigate the unsafe condition 

addressed in this AD. Under the 

provisions of paragraph (j) of this AD, 

we will consider requests for approval 

of an AMOC for previous repairs if 

sufficient data are submitted to 

substantiate that the repairs would 

provide an acceptable level of safety for 

the unsafe condition addressed in this 

AD. We have not changed the final rule 

in this regard. 

Request for Global Terminating Action 

and Delay of AD 

Delta Airlines (Delta) requested that 

we revise the NPRM (76 FR 69685, 

November 9, 2011) to add the statement 

‘‘FAA approved repairs for cracking at 

the subject locations prior to the release 

of this service bulletin (Boeing Service 

Bulletin 767–53A0209, Revision 1, 

dated July 27, 2011), constitute 

terminating action for the inspections 

defined in this AD.’’ Delta stated that, if 

previously installed FAA-approved 

repairs are not approved as terminating 

action, then it would request that the 

AD effective date be three months after 

the release of the AD, rather than two or 

three weeks after the release of the AD. 

Delta asserted that this would allow 

additional time for Boeing and Aviation 

Partners Boeing to review and provide 

AMOC information for the large volume 

of previous repairs associated with this 

area. 

We disagree to add approval of a 

global terminating action for previously 

approved repairs. We are unable to 

approve a global terminating action for 

repairs that might have had previous 

FAA approvals without information as 

to how each repair mitigates the 

identified unsafe condition addressed in 

this AD. In addition, requirements that 

must be met for approvals of AMOC 

requests exceed those for repair 

approvals. We also disagree to delay the 

effective date of this AD. We considered 

that delaying issuance of this AD is 

inappropriate in light of the identified 

unsafe condition. We have not changed 

the final rule in this regard. 

Clarification of Effect of Winglet 

Installation 

We have added new paragraph (c)(2) 

to this AD, which states that 

Supplemental Type Certificate (STC) 

ST01920SE (http://rgl.faa.gov/ 

Regulatory_and_Guidance_Library/ 

rgstc.nsf/0/ 

082838ee177dbf62862576a4005cdfc0/ 

$FILE/ST01920SE.pdf) does not affect 

the ability to accomplish the actions 

required by this AD. Therefore, for 

airplanes on which STC ST01920SE is 

installed, a ‘‘change in product’’ AMOC 

approval request is not necessary to 

comply with the requirements of 14 CFR 

39.17. For all other AMOC requests, the 

operator must request approval for an 

AMOC in accordance with the 

procedures specified in paragraph (j) of 

this AD. 

Change to Paragraph (j)(3) of This AD 

We have removed the reference to 

Federal Aviation Regulations 14 CFR 

25.571, Amendment 45 from this AD 

that was specified in paragraph (j)(3) of 

the NPRM (76 FR 69685, November 9, 

2011). Removing this reference will 

neither increase the economic burden 

on any operator nor increase the scope 

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 changes: 

• Are consistent with the intent that 

was proposed in the NPRM (76 FR 

69685, November 9, 2011), for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (76 FR 69685, 

November 9, 2011). 

Costs of Compliance 

We estimate that this AD will affect 

325 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 

Detailed or HFEC inspection 23 or 26 work-hours × $85 

per hour = $1,955 or 2,210 

per inspection cycle.

$0 $1,955 or $2,210 per inspection cycle.Up to $718,250 per inspection 

cycle. 

We estimate the following costs to do 

any necessary repairs 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. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Repair ............................................ 24 work-hours × $85 per hour = 

$2,040.

$383 to $8,327 per frame ............. $2,423 to $10,367 per frame. 


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69746 Federal Register / Vol. 77, No. 225 / Wednesday, November 21, 2012 / Rules and Regulations 

ON-CONDITION COSTS—Continued 

Action Labor cost Parts cost Cost per product 

On-condition detailed and HFEC 

inspections and measurement.

7 work-hours × $85 per hour = 

$595 per frame.

$0 .................................................. $595 

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): 

2012–22–17 The Boeing Company: 

Amendment 39–17255; Docket No. 

FAA–2011–1168; Directorate Identifier 

2010–NM–239–AD. 

(a) Effective Date 

This AD is effective December 26, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to The Boeing 

Company Model 767–200 and –300 series 

airplanes, certificated in any category, as 

identified in Boeing Service Bulletin 767– 

53A0209, Revision 1, dated July 27, 2011. 

(2) Supplemental Type Certificate (STC) 

ST01920SE (http://rgl.faa.gov/ 

Regulatory_and_Guidance_Library/rgstc.nsf/ 

0/082838ee177dbf62862576a4005cdfc0/ 

$FILE/ST01920SE.pdf) does not affect the 

ability to accomplish the actions required by 

this AD. Therefore, for airplanes on which 

STC ST01920SE is installed, a ‘‘change in 

product’’ alternative method of compliance 

(AMOC) approval request is not necessary to 

comply with the requirements of 14 CFR 

39.17. For all other AMOC requests, the 

operator must request approval for an AMOC 

in accordance with the procedures specified 

in paragraph (j) of this AD. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of cracks 

in the inner chords at both left-side and rightside stations 859.5, 883.5, and 903.5. We are 

issuing this AD to prevent large cracks in the 

frames and adjacent structure that can 

adversely affect the structural integrity of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections, Related 

Investigative Actions, and Corrective 

Actions 

Except as required by paragraph (h)(2) of 

this AD, at the times specified in paragraph 

1.E., ‘‘Compliance,’’ of Boeing Service 

Bulletin 767–53A0209, Revision 1, dated July 

27, 2011: Perform a detailed inspection or a 

surface high frequency eddy current (HFEC) 

inspection for cracking in the frame inner 

chord transition radius at stations 859.5, 

883.5, and 903.5, as applicable, left buttock 

line and right buttock line 89, below water 

line 200; and do all applicable related 

investigative and corrective actions; in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

53A0209, Revision 1, dated July 27, 2011; 

except as required by paragraph (h)(1) of this 

AD. Do all applicable related investigative 

and corrective actions before further flight. If 

no cracking is found, repeat the inspections 

thereafter at the applicable interval specified 

in paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Service Bulletin 767–53A0209, Revision 1, 

dated July 27, 2011. 

Note 1 to paragraph (g) of this AD: The 

post-repair inspections specified in Tables 2, 

4, 6, and 8 of paragraph 1.E., ‘‘Compliance,’’ 

of Boeing Service Bulletin 767–53A0209, 

Revision 1, dated July 27, 2011, may be used 

in support of compliance with paragraph 

(c)(2) of Section 121.1109 or 129.109 of the 

Federal Aviation Regulations (14 CFR 

121.1109(c)(2) or 14 CFR 129.109(c)(2)). 

(h) Exceptions to the Service Information 

(1) If any cracking is found during any 

inspection required by this AD, and Boeing 

Service Bulletin 767–53A0209, Revision 1, 

dated July 27, 2011, specifies to contact 

Boeing for appropriate action: Before further 

flight, repair the cracking using a method 

approved in accordance with the procedures 

specified in paragraph (j) of this AD. 

(2) Where Boeing Service Bulletin 767– 

53A0209, Revision 1, dated July 27, 2011, 

specifies a compliance time after the date on 

that service bulletin, this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(i) No Reporting Required 

Although Boeing Service Bulletin 767– 

53A0209, Revision 1, dated July 27, 2011, 

specifies to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(j) 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 


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Federal Register / Vol. 77, No. 225 / Wednesday, November 21, 2012 / Rules and Regulations 69747 

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: 9-ANMSeattle-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. 

(k) Related Information 

For more information about this AD, 

contact Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, ACO, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6577; fax: 425–917– 

6590; email: Berhane.Alazar@faa.gov. 

(l) 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 Service Bulletin 767–53A0209, 

Revision 1, dated July 27, 2011. 

(ii) Reserved. 

(3) 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. 

(4) 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. 

(5) You may also review copies of the 

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 October 

31, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–27344 Filed 11–20–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0722; Directorate 

Identifier 2010–NM–262–AD; Amendment 

39–17260; AD 2012–23–04] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 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 

737–100 and –200 series airplanes. The 

existing AD currently requires various 

inspections for cracks in the outboard 

chord of the frame at body station (BS) 

727 and in the outboard chord of 

stringer (S) 18A, and repair or 

replacement of cracked parts. This new 

AD adds airplanes to the applicability 

statement in the existing AD and adds 

inspections for cracks in the BS 727 

frame outboard chords and the radius of 

the auxiliary chord, for certain 

airplanes. This new AD also removes 

the inspections of the outboard chord of 

S–18A required by the existing AD. This 

AD was prompted by several reports of 

fatigue cracking in the frame outboard 

chord at BS 727 and in the radius of the 

auxiliary chord on airplanes that were 

not affected by the existing AD. We are 

issuing this AD to detect and correct 

fatigue cracking of the outboard and 

auxiliary chords, which could result in 

reduced structural integrity of the 

outboard chord and consequent rapid 

decompression of the airplane. 

DATES: This AD is effective December 

26, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 26, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of August 18, 1995 (60 FR 

36981, July 19, 1995). 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

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: 

Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone (425) 

917–6450; fax (425) 917–6590; email 

alan.pohl@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 95–12–17, 

Amendment 39–9268 (60 FR 36981, July 

19, 1995). That AD applies to the 

specified products. The NPRM 

published in the Federal Register on 

August 5, 2011 (76 FR 47522). That 

NPRM proposed to continue to require 

various inspections for cracks in the 

outboard chord of the frame at BS 727, 

and repair or replacement of cracked 

parts. That NPRM also proposed to add 

airplanes to the applicability statement 

in the existing AD and add inspections 

for cracks in the BS 727 frame outboard 

chords and the radius of the auxiliary 

chord, for certain airplanes. That NPRM 

also proposed to remove the inspections 

of the outboard chord of S–18A required 

by the existing AD. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (76 FR 47522, 

August 5, 2011) and the FAA’s response 

to each comment. 

Support for NPRM (76 FR 47522, 

August 5, 2011) 

Europe Airpost has no objection to the 

NRPM (76 FR 47522, August 5, 2011), 

and noted that it has already 

implemented the procedures in Boeing 


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