66254 Federal Register / Vol. 78, No. 214 / Tuesday, November 5, 2013 / Rules and Regulations 

(i) Revise the Operating Limitations section 

of the Model 206L RFM by inserting Section 

1, Operating Limitations, page 1–4B, of Bell 

BHT–206L–FM–1, revision 28, dated 

December 8, 2008. 

(ii) Remove placard P/N 230–075–213–123, 

if installed. 

(ii) Install placard P/N 230–075–213–127, 

or equivalent, on the instrument panel below 

the dual tachometer. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Chinh Vuong, 

Aviation Safety Engineer, Safety Management 

Group, Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 76137; 

telephone (817) 222–5110; email 

chinh.vuong@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

(1) Bell Alert Service Bulletin (ASB) No. 

206–07–115, Revision C, dated February 4, 

2009, and Bell ASB No. 206L–07–146, 

Revision B, dated March 3, 2009, which are 

not incorporated by reference, contain 

additional information about the subject of 

this AD. For service information identified in 

this AD, contact Bell Helicopter Textron 

Canada Limited, 12,800 Rue de l’Avenir, 

Mirabel, Quebec J7J1R4; telephone (450) 

437–2862 or (800) 363–8023; fax (450) 433– 

0272; or at http://www.bellcustomer.com/

files/. You may review a copy of the service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(2) The subject of this AD is addressed in 

Transport Canada Civil Aviation (TCCA) AD 

No. CF–2007–13R2, dated December 9, 2009. 

You may view the TCCA AD on the internet 

in the AD Docket at http://

www.regulations.gov. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 7250: Turbine Section. 

(i) 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) Page 1–2A of Section 1, Operating 

Limitations, of Bell Rotorcraft Flight Manual 

BHT–206B–FM–1, Revision B–50, dated 

December 8, 2008. 

(ii) Page 1–4B of Section 1, Operating 

Limitations, of Bell Rotorcraft Flight Manual 

BHT–206L–FM–1, Revision 28, dated 

December 8, 2008. 

(3) For Bell service information identified 

in this AD, contact Bell Helicopter Textron 

Canada Limited, 12,800 Rue de l’Avenir, 

Mirabel, Quebec J7J1R4; telephone (450) 

437–2862 or (800) 363–8023; fax (450) 433– 

0272; or at http://www.bellcustomer.com/

files/. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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 Fort Worth, Texas, on September 

25, 2013. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–24037 Filed 11–4–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0328; Directorate 

Identifier 2012–NM–184–AD; Amendment 

39–17643; AD 2013–22–11] 

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) 2009–10– 

06 for certain The Boeing Company 

Model 747–400 and –400D series 

airplanes. AD 2009–10–06 required 

repetitive inspections to detect cracks in 

the floor panel attachment fastener 

holes of the Section 41 upper deck floor 

beam upper chords, and corrective 

actions if necessary; and repetitive postrepair and post-modification 

inspections, and corrective actions if 

necessary. This new AD adds repetitive 

inspections of Section 44 upper deck 

floor beam upper chords, and corrective 

actions if necessary; repetitive postrepair and post-modification 

inspections, and corrective actions if 

necessary; and replacement of the upper 

deck floor beam upper chords. This AD 

was prompted by an evaluation by the 

design approval holder (DAH) 

indicating that certain upper chords of 

the upper deck floor beam are subject to 

widespread fatigue damage (WFD). We 

are issuing this AD to detect and correct 

fatigue cracking in certain upper chords 

of the upper deck floor beam, which 

could become large and cause the floor 

beams to become severed and result in 

rapid decompression or reduced 

controllability of the airplane. 

DATES: This AD is effective December 

10, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 10, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of June 17, 2009 (74 FR 

22424, May 13, 2009). 

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, 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: Bill 

Ashforth, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle ACO, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6432; fax: 

425–917–6590; email: bill.ashforth@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2009–10–06, 

Amendment 39–15901 (74 FR 22424, 

May 13, 2009). AD 2009–10–06 applied 

to the specified products. The NPRM 

published in the Federal Register on 


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Federal Register / Vol. 78, No. 214 / Tuesday, November 5, 2013 / Rules and Regulations 66255 

April 16, 2013 (78 FR 22435). The 

NPRM proposed to continue to require 

repetitive inspections to detect cracks in 

the floor panel attachment fastener 

holes of the Section 41 upper deck floor 

beam upper chords, and corrective 

actions if necessary; and repetitive postrepair and post-modification 

inspections, and corrective actions if 

necessary. The NPRM also proposed to 

add repetitive inspections of Section 44 

upper deck floor beam upper chords, 

and corrective actions if necessary; 

repetitive post-repair and postmodification inspections, and corrective 

actions if necessary; and replacement of 

the upper deck floor beam upper 

chords. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (78 FR 22435, 

April 16, 2013) and the FAA’s response 

to each comment. 

Request To Eliminate Duplicate 

Reference to Post-Repair and PostModification Repetitive Inspections 

Boeing requested that we delete the 

reference to post-repair and postmodification repetitive inspections from 

paragraph (g) of the NPRM (78 FR 

22435, April 16, 2013). Boeing stated 

that the post-repair and postmodification inspections are required by 

paragraph (i) of the NPRM, and need to 

be deleted from paragraph (g) of the 

NPRM to avoid confusion. 

We agree to remove the duplicate 

reference to post-repair and postmodification repetitive inspections from 

paragraph (g) of this final rule. We have 

changed paragraph (g) of this final rule 

accordingly. 

Request To Revise the Heading and 

Clarify Paragraph (k) of the NPRM (78 

FR 22435, April 16, 2013) 

Boeing requested that we revise the 

heading of paragraph (k) of the NPRM 

(78 FR 22435, April 16, 2013) to clarify 

that the modification specified in Table 

2 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Service Bulletin 747–53A2688, 

Revision 1, dated September 19, 2012, is 

not new and is not fully terminating. 

Boeing also requested that we add text 

concerning terminating inspections 

required by paragraphs (g) and (j) of the 

NPRM, and also for the resumption of 

inspections required by paragraphs (i) 

and (l) of the NPRM. 

We agree with the request. We have 

revised the heading of paragraph (k) of 

this final rule to ‘‘New Terminating 

Action for Certain Conditions.’’ We also 

agree with adding text to paragraph (k) 

of this final rule to clarify which 

modifications or repairs as 

modifications terminate which 

inspections required by this final rule. 

We have revised paragraph (k) of this 

final rule to add new paragraph (k)(1) to 

this final rule to specify that, for Section 

41, doing a hole modification or repair 

as a hole modification, in accordance 

with ‘‘Part 2—Section 41—Repair,’’ of 

the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747– 

53A2688, Revision 1, dated September 

19, 2012, terminates the repetitive 

inspections specified in paragraph (g) of 

this final rule. We have also included 

clarification in paragraph (k)(1) of this 

final rule to indicate that the repetitive 

inspections specified in paragraph (i) of 

this final rule must be done. 

We have also moved the content of 

paragraph (k) of the NPRM (78 FR 

22435, April 16, 2013) to new paragraph 

(k)(2) of this final rule to specify that, 

for Section 44, doing a hole 

modification or repair as a hole 

modification, in accordance with ‘‘Part 

5—Section 44—Repair,’’ of the 

Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2688, 

Revision 1, dated September 19, 2012, 

terminates the repetitive inspections 

specified in paragraph (j) of this final 

rule. We have also included clarification 

in paragraph (k)(2) of this final rule to 

indicate that the repetitive inspections 

specified in paragraph (l) of this final 

rule must be done. 

Request To Restart Inspections After 

Replacement of Upper Deck Floor 

Beam Upper Chords 

Boeing requested that we revise 

paragraph (m) of the NPRM (78 FR 

22435, April 16, 2013) to add a note 

concerning the new inspection 

threshold, equal to the original 

threshold, to restart inspections after 

replacement of the upper deck floor 

beam upper chords. Boeing stated that 

paragraph (m) of the NPRM requires the 

replacement of upper deck floor beam 

upper chords in Sections 41 and 44, as 

given in Table 5 of Boeing Service 

Bulletin 747–53A2688, Revision 1, 

dated September 19, 2012. Boeing stated 

that the new inspection threshold needs 

to be provided in paragraph (m) of this 

NPRM. 

We agree with the request to include 

a relieving compliance time for the 

inspections required by this final rule 

for airplanes on which the upper deck 

floor beam upper chords are replaced. 

Paragraphs (g), (i), (j), and (l) of this final 

rule require repetitive inspections at the 

applicable times specified in Tables 1 

through 4 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service 

Bulletin 747–53A2688, Revision 1, 

dated September 19, 2012. However, 

Boeing Service Bulletin 747–53A2688, 

Revision 1, dated September 19, 2012, 

does not specify that accomplishing the 

replacement terminates the repetitive 

inspections, nor does it provide a longer 

compliance time for the next inspection 

done after accomplishing the 

replacement. We also agree that the next 

inspection after accomplishing the 

replacement may be done within 20,000 

flight cycles. We have determined that 

this compliance time will provide an 

adequate level of safety. We have 

revised paragraph (m) of this final rule 

to add the first interval for the repetitive 

inspections required by this final rule 

for airplanes on which a replacement 

required by paragraph (m) of this final 

rule is done. 

Request To Add References to 

Paragraph (n)(1) of the NPRM (78 FR 

22435, April 16, 2013) 

Boeing requested that we revise 

paragraph (n)(1) of the NPRM (78 FR 

22435, April 16, 2013) to refer to 

paragraphs (j) and (l) of the NPRM. 

Boeing stated that since paragraph (n) of 

the NPRM is referring to new 

exceptions, it should refer to cracks 

found as part of the new inspections 

specified in paragraph (i), (j), or (l) of 

the NPRM (reference Compliance Tables 

2, 3, or 4 of Boeing Service Bulletin 

747–53A2688, Revision 1, dated 

September 19, 2012). 

We partially agree with the request. 

We have added a reference to paragraph 

(j) of this final rule in paragraph (n)(1) 

of this final rule. Paragraph (j) of this 

final rule already references paragraph 

(n)(1) of this final rule as an exception. 

However, we do not agree to add a 

reference to paragraph (l) of this final 

rule in paragraph (n)(1) of this final rule, 

because paragraph (l) of this final rule 

does not include a reference to the 

service information for the corrective 

action. Paragraph (l) of this final rule 

specifies to refer to the procedures in 

paragraph (p) of this final rule for 

airplanes on which any cracking is 

found. 

Request To Allow Boeing Organization 

Designation Authorization (ODA) 

Approval 

Boeing requested we revise paragraph 

(n)(3) of the NPRM (78 FR 22435, April 

16, 2013) to allow the full provisions of 

Boeing ODA approval. Boeing stated 

that alternative method of compliance 

(AMOC) approval provisions allowed in 

paragraph (p) of the NPRM should apply 

to all sections of the NPRM. 

We disagree. Paragraph (p)(3) of this 

final rule already allows for ODA 


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66256 Federal Register / Vol. 78, No. 214 / Tuesday, November 5, 2013 / Rules and Regulations 

approval of repairs. We have not 

changed this final rule in this regard. 

However, we have revised paragraph 

(n)(3) of this final rule to clarify where 

the service information specifies to 

contact the FAA, operators must contact 

the Seattle Aircraft Certification Office 

(ACO). 

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 

except for minor editorial changes. We 

have determined that these minor 

changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

22435, April 16, 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 22435, 

April 16, 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 84 

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 

Inspection (retained actions 

from AD 2009–10–06, 

Amendment 39-15901 (74 

FR 22424, May 13, 2009)).

Up to 50 work-hours × $85 

per hour = Up to $4,250 

per inspection cycle.

$0 Up to $4,250 per inspection 

cycle.

Up to $357,000 per inspection 

cycle. 

Inspection (new action) .......... 259 work-hours × $85 per 

hour = $22,015 per inspection cycle.

0 $22,015 per inspection cycle $1,849,260 per inspection 

cycle. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the repair or modification 

specified in this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 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 

removing airworthiness directive (AD) 

2009–10–06, Amendment 39–15901 (74 

FR 22424, May 13, 2009), and adding 

the following new AD: 

2013–22–11 The Boeing Company: 

Amendment 39–17643; Docket No. 

FAA–2013–0328; Directorate Identifier 

2012–NM–184–AD. 

(a) Effective Date 

This AD is effective December 10, 2013. 

(b) Affected ADs 

This AD supersedes AD 2009–10–06, 

Amendment 39–15901 (74 FR 22424, May 13, 

2009). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–400 and –400D series airplanes; 

certificated in any category; as identified in 

Boeing Alert Service Bulletin 747–53A2688, 

Revision 1, dated September 19, 2012. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by an evaluation by 

the design approval holder (DAH) indicating 

that certain upper chords of the upper deck 

floor beam are subject to widespread fatigue 

damage (WFD). We are issuing this AD to 

detect and correct fatigue cracking in certain 

upper chords of the upper deck floor beam, 

which could become large and cause the 

floor beams to become severed and result in 

rapid decompression or reduced 

controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspections and Corrective 

Actions With Revised Service Information 

and Compliance Times 

This paragraph restates the actions 

required by paragraph (g) of AD 2009–10–06, 

Amendment 39–15901 (74 FR 22424, May 13, 

2009), with revised service information and 

compliance times. Except as required by 

paragraphs (h)(1) and (h)(2) of this AD: At the 

applicable times in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2688, dated August 21, 

2008, do an inspection (open-hole or surface 

high frequency eddy current (HFEC)) to 


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Federal Register / Vol. 78, No. 214 / Tuesday, November 5, 2013 / Rules and Regulations 66257 

detect cracks in the floor panel attachment 

fastener holes of the Section 41 upper deck 

floor beam upper chords, and do applicable 

corrective actions, by accomplishing all the 

applicable actions specified in the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2688, dated August 

21, 2008; or Revision 1, dated September 19, 

2012. Repeat the inspections thereafter at the 

applicable times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2688, dated August 21, 

2008, except as required by paragraphs (i) 

and (m) of this AD. As of the effective date 

of this AD, use only Boeing Alert Service 

Bulletin 747–53A2688, Revision 1, dated 

September 19, 2012, to accomplish the 

actions in this paragraph. 

(h) Retained Exceptions 

(1) This paragraph restates the exception 

stated in paragraph (h) of AD 2009–10–06, 

Amendment 39–15901 (74 FR 22424, May 13, 

2009). If any crack is found during any 

inspection required by paragraph (g) of this 

AD, and Boeing Alert Service Bulletin 747– 

53A2688, dated August 21, 2008; or Revision 

1, dated September 19, 2012; specifies to 

contact Boeing for appropriate action: Before 

further flight, repair the crack using a method 

approved in accordance with the procedures 

specified in paragraph (p) of this AD. 

(2) This paragraph restates the exception 

stated in paragraph (i) of AD 2009–10–06, 

Amendment 39–15901 (74 FR 22424, May 13, 

2009). Where Boeing Alert Service Bulletin 

747–53A2688, dated August 21, 2008, 

specifies a compliance time after the date on 

the service bulletin, this AD requires 

compliance within the specified compliance 

time after June 17, 2009 (the effective date of 

AD 2009–10–06). 

(i) Inspections and Corrective Actions for 

Airplanes on Which a Repair or 

Modification Is Done (for Section 41) 

For airplanes on which a repair or 

modification identified in Table 2 of 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2688, Revision 1, dated 

September 19, 2012, has been done: At the 

times specified in Table 2 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2688, Revision 1, dated 

September 19, 2012, except as required by 

paragraph (n)(3) of this AD, do open-hole and 

surface HFEC inspections, as applicable, for 

cracking, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2688, Revision 1, 

dated September 19, 2012. Repeat at the 

applicable intervals specified in Table 2 of 

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

Alert Service Bulletin 747–53A2688, 

Revision 1, dated September 19, 2012. If any 

cracking is found in the repaired or modified 

locations, before further flight, repair the 

crack using a method approved in 

accordance with the procedures specified in 

paragraph (p) of this AD. 

(j) New Inspections and Repair 

For Group 1 airplanes identified in Boeing 

Alert Service Bulletin 747–53A2688, 

Revision 1, dated September 19, 2012: At the 

applicable times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2688, Revision 1, dated 

September 19, 2012, except as specified in 

paragraph (n)(2) of this AD, do an open-hole 

or surface HFEC inspection to detect cracking 

in the floor panel attachment fastener holes 

of the Section 44 upper deck floor beam 

upper chords, and all applicable corrective 

actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2688, Revision 1, 

dated September 19, 2012, except as required 

by paragraph (n)(1) of this AD. Repeat the 

inspections thereafter at the applicable 

intervals specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2688, Revision 1, dated 

September 19, 2012, except as provided by 

paragraph (m) of this AD. Do all applicable 

corrective actions before further flight. 

(k) New Terminating Action for Certain 

Conditions 

(1) For Section 41: Doing a hole 

modification or repair as a hole modification, 

in accordance with ‘‘Part 2—Section 41— 

Repair,’’ of the Accomplishment Instructions 

of Boeing Alert Service Bulletin 747– 

53A2688, Revision 1, dated September 19, 

2012, terminates the repetitive inspections 

specified in paragraph (g) of this AD. 

However, the repetitive inspections specified 

in paragraph (i) of this AD must be done. 

(2) For Section 44: Doing a hole 

modification or repair as a hole modification, 

in accordance with ‘‘Part 5—Section 44— 

Repair,’’ of the Accomplishment Instructions 

of Boeing Alert Service Bulletin 747– 

53A2688, Revision 1, dated September 19, 

2012, terminates the repetitive inspections 

specified in paragraph (j) of this AD. 

However, the repetitive inspections specified 

in paragraph (l) of this AD must be done. 

(l) New Inspections and Corrective Actions 

for Airplanes on Which a Repair or 

Modification Is Done (for Section 44) 

For airplanes on which a repair or 

modification specified in the ‘‘Condition’’ 

column of Table 4 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2688, Revision 1, dated 

September 19, 2012, has been done: At the 

times specified in Table 4 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2688, Revision 1, dated 

September 19, 2012, except as required by 

paragraph (n)(3) of this AD, do open hole and 

surface HFEC inspections, as applicable, for 

cracking, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2688, Revision 1, 

dated September 19, 2012. Repeat at the 

applicable intervals specified in Table 4 of 

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

Alert Service Bulletin 747–53A2688, 

Revision 1, dated September 19, 2012. If any 

cracking is found in the repaired or modified 

locations, before further flight, repair the 

crack using a method approved in 

accordance with the procedures specified in 

paragraph (p) of this AD. 

(m) New Replacement and Post-Replacement 

Inspections 

At the time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2688, Revision 1, dated 

September 19, 2012: Replace Section 41 and 

44 upper deck floor beam upper chords, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2688, Revision 1, dated September 

19, 2012. Repeat the inspections required by 

paragraphs (g) and (j) of this AD within 

20,000 flight cycles after doing the 

replacement. Thereafter, repeat the 

inspection required by paragraphs (g) and (j) 

of this AD at the times specified in 

paragraphs (g) and (j) of this AD. 

(n) New Exceptions 

(1) If any crack is found during any 

inspection required by paragraph (i), (j), or (l) 

of this AD, and Boeing Alert Service Bulletin 

747–53A2688, Revision 1, dated September 

19, 2012, specifies to contact Boeing for 

appropriate action: Before further flight, 

repair the crack using a method approved in 

accordance with the procedures specified in 

paragraph (p) of this AD. 

(2) Where Boeing Alert Service Bulletin 

747–53A2688, Revision 1, dated September 

19, 2012, specifies a compliance time ‘‘after 

the Revision 1 date of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(3) Where Table 2 or Table 4 of paragraph 

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

Bulletin 747–53A2688, Revision 1, dated 

September 19, 2012, specifies to contact 

Boeing for inspections and compliance times: 

Before further flight, contact the Manager, 

FAA, Seattle Aircraft Certification Office 

(ACO), for inspections and compliance times 

and accomplish the inspections at the given 

times. 

(o) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Alert 

Service Bulletin 747–53A2688, dated August 

21, 2008. 

(p) 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 (q)(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 


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66258 Federal Register / Vol. 78, No. 214 / Tuesday, November 5, 2013 / Rules and Regulations 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved for AD 2009–10–06, 

Amendment 39–15901 (74 FR 22424, May 13, 

2009), are approved as AMOCs for the 

corresponding actions of this AD. 

(q) Related Information 

(1) For more information about this AD, 

contact Bill Ashforth, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6432; fax: 425– 

917–6590; email: bill.ashforth@faa.gov. 

(2) Service information that is not 

incorporated by reference in this AD may be 

obtained at the addresses identified in 

paragraph (r)(5) of this AD. 

(r) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on December 10, 2013. 

(i) Boeing Alert Service Bulletin 747– 

53A2688, Revision 1, dated September 19, 

2012. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on June 17, 2009 (74 FR 

22424, May 13, 2009). 

(i) Boeing Alert Service Bulletin 747– 

53A2688, dated August 21, 2008. 

(ii) Reserved. 

(5) 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. 

(6) You may view this service information 

at FAA, 1601 Lind Avenue SW., Renton, WA. 

For information on the availability of this 

material at the FAA, call 425–227–1221. 

(7) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on October 

17, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–25950 Filed 11–4–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0868; Directorate 

Identifier 2013–NM–194–AD; Amendment 

39–17650; AD 2013–22–18] 

RIN 2120–AA64 

Airworthiness Directives; Empresa 

Brasileira de Aeronautica S.A. 

(EMBRAER) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final Rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Empresa Brasileira de Aeronautica S.A. 

(EMBRAER) Model EMB–135ER, 

–135KE, –135KL, and –135LR airplanes; 

and Model EMB–145, –145ER, –145MR, 

–145LR, –145XR, –145MP, and –145EP 

airplanes. This AD requires repetitive 

detailed inspections to detect 

discrepancies on the attaching parts of 

the lower eyelet fitting of the cockpit 

windshield center-post, and, if no 

discrepancy is found, a check to make 

sure the bolts are tight, and replacement 

of the attaching parts if necessary. This 

AD also provides an option to 

accomplish the replacement of the 

attaching parts, which terminates the 

repetitive inspections. This AD was 

prompted by reports of failure of the 

bolts that connect the lower eyelet 

fitting of the cockpit windshield centerpost to the forward fuselage. We are 

issuing this AD to detect and correct 

failed bolts and attaching parts of the 

lower eyelet fitting of the cockpit 

windshield center-post, which could 

lead to loss of structural integrity of the 

airplane. 

DATES: This AD becomes effective 

November 20, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 20, 2013. 

We must receive comments on this 

AD by December 20, 2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC, between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

For service information identified in 

this AD, contact Empresa Brasileira de 

Aeronautica S.A. (EMBRAER), 

Technical Publications Section (PC 

060), Av. Brigadeiro Faria Lima, 2170— 

Putim—12227–901 Sa ̃o Jose dos 

Campos—SP—BRASIL; telephone +55 

12 3927–5852 or +55 12 3309–0732; fax 

+55 12 3927–7546; email distrib@

embraer.com.br; Internet http://

www.flyembraer.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 Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the Mandatory 

Continuing Airworthiness Information 

(MCAI), the regulatory evaluation, any 

comments received, and other 

information. The street address for the 

Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1175; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The Ageˆncia Nacional de Aviac ̧a ̃o 

Civil (ANAC), which is the aviation 

authority for Brazil, has issued Brazilian 

Emergency Airworthiness Directive 

2013–10–01, effective October 3, 2013 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI states: 

This [Brazilian] EAD [emergency AD] was 

prompted by reports of failure of the bolts 

that connect the lower eyelet fitting of the 

cockpit windshield center-post to the 

forward fuselage. We are issuing this EAD to 

detect failed bolts and correct the attaching 

parts of the lower eyelet fitting of the cockpit 

windshield center-post, which could lead to 

loss of structural integrity of the airplane. 


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