Federal Register / Vol. 79, No. 241 / Tuesday, December 16, 2014 / Rules and Regulations 74599 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report of 

cracking at the splice plate of the frame (FR) 

47 butt joint crossing area found during fullscale fatigue testing. We are issuing this AD 

to detect and correct fatigue cracking of the 

splice plate of the FR47 butt joint crossing 

area, which could result in reduced 

structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

At the applicable time specified in 

paragraph (g)(1), (g)(2), or (g)(3) of this AD: 

Do a special detailed inspection (rototest) for 

cracking of both sides of the splice plate of 

the FR47 butt joint crossing area, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1260, dated December 19, 2012. Repeat 

the inspection thereafter at intervals not to 

exceed 14,800 flight cycles or 29,600 flight 

hours, whichever occurs first. 

(1) For airplanes that, as of the effective 

date of this AD, have accumulated 44,000 or 

more total flight cycles or 88,000 or more 

total flight hours since first flight of the 

airplane: Do the inspection within 1,500 

flight cycles or 3,000 flight hours after the 

effective date of this AD, whichever occurs 

first. 

(2) For airplanes that, as of the effective 

date of this AD, have accumulated 27,700 or 

more total flight cycles or 55,400 or more 

total flight hours, but fewer than 44,000 total 

flight cycles or 88,000 total flight hours since 

first flight of the airplane: Do the inspection 

within 3,000 flight cycles or 6,000 flight 

hours after the effective date of this AD, 

without exceeding 45,500 total flight cycles 

or 91,000 total flight hours since first flight 

of the airplane, whichever occurs first. 

(3) For airplanes that, as of the effective 

date of this AD, have accumulated fewer than 

27,700 total flight cycles and less than 55,400 

total flight hours since first flight of the 

airplane: Do the inspection before the 

accumulation of 30,700 total flight cycles or 

61,400 total flight hours since first flight of 

the airplane, whichever occurs first. 

(h) Corrective Action 

If any crack is found during any inspection 

required by this AD: Before further flight, 

repair using a method approved by the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

European Aviation Safety Agency (EASA); or 

Airbus’s EASA Design Organization 

Approval (DOA). If approved by the DOA, 

the approval must include the DOAauthorized signature. 

(i) Optional Modification 

Accomplishing the modification of the 

splice plate of the FR47 butt joint in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1271, dated December 18, 2012, 

constitutes terminating action for the 

repetitive inspections required by paragraph 

(g) of this AD. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–227–1405; fax: 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 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. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(k) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0203, dated 

September 6, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://www.regulations.

gov/#!documentDetail;D=FAA-2014-0453- 

0002. 

(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 this AD specifies otherwise. 

(i) Airbus Service Bulletin A320–53–1260, 

dated December 19, 2012. 

(ii) Airbus Service Bulletin A320–53–1271, 

dated December 18, 2012. 

(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

(4) You may view 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. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://www.archives.

gov/federal-register/cfr/ibr-locations.html. 

Issued in Renton, Washington, on 

December 3, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–29174 Filed 12–15–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0257; Directorate 

Identifier 2014–NM–012–AD; Amendment 

39–18051; AD 2014–25–09] 

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 737–100, 

–200, –200C, –300, –400, and –500 

series airplanes. This AD was prompted 

by reports of fatigue cracking in the skin 

assembly and bear strap of the aft lower 

corner of the forward airstair stowage 

doorway. This AD requires repetitive 

inspections for cracking of the skin 

assembly and bear strap of the forward 

airstair stowage doorway; post-repair 

and post-modification inspections for 

certain airplanes; and related 

investigative and corrective actions, if 

necessary. This AD also provides 

optional terminating actions for certain 

inspections. We are issuing this AD to 

detect and correct fatigue cracking, 

which could result in rapid loss of cabin 

pressure. 

DATES: This AD is effective January 20, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 20, 2015. 

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://


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www.myboeingfleet.com. You may view 

this 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 by searching for 

and locating Docket No. FAA–2014– 

0257; 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: 

Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

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 by adding an AD that would 

apply to certain The Boeing Company 

Model 737–100, –200, –200C, –300, 

–400, and –500 series airplanes. The 

NPRM published in the Federal 

Register on May 1, 2014 (79 FR 24628). 

The NPRM was prompted by reports of 

fatigue cracking in certain areas. The 

NPRM proposed to require repetitive 

inspections for cracking of the skin 

assembly and bear strap of the forward 

airstair stowage doorway; post-repair 

and post-modification inspections for 

certain airplanes; and related 

investigative and corrective actions, if 

necessary. The NPRM also proposed to 

provide optional terminating actions for 

certain inspections. We are issuing this 

AD to detect and correct fatigue 

cracking, which could result in rapid 

loss of cabin pressure. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 24628, 

May 1, 2014) and the FAA’s response to 

each comment. 

Effect of Winglets on AD 

Aviation Partners Boeing and UPS 

stated that the installation of winglets 

per Supplemental Type Certificate 

(STC) ST01219SE (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/

rgstc.nsf/0/ebd1cec7b301293e86257

cb30045557a/$FILE/ST01219SE.pdf) 

does not affect the accomplishment of 

the manufacturer’s service instructions. 

We agree with the commenters’ 

statement. We have redesignated 

paragraph (c) of the NPRM (79 FR 

24628, May 1, 2014) as (c)(1) in this AD 

and added new paragraph (c)(2) to this 

AD to state that the installation of 

winglets as specified in STC ST01219SE 

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

Guidance_Library/rgstc.nsf/0/ebd1c

ec7b301293e86257cb30045557a/$FILE/

ST01219SE.pdf) does not affect 

accomplishment of the requirements of 

this AD, and for airplanes on which STC 

ST01219SE is installed, a ‘‘change in 

product’’ alternative method of 

compliance (AMOC) approval request is 

not necessary to comply with the 

requirements of section 39.17 of the 

Federal Aviation Regulations (14 CFR 

39.17). 

Request To Revise Paragraph (m) of the 

NPRM (79 FR 24628, May 1, 2014) 

Southwest Airlines (SWA) stated that 

the NPRM (79 FR 24628, May 1, 2014), 

does not address terminating the initial 

inspection if a repair was previously 

installed using Boeing Service Bulletin 

737–53–1058, Revision 4, dated January 

9, 2014. SWA requested that we revise 

the text of paragraph (m)(3) of the 

NPRM, to state that repairs or 

modifications using Boeing Service 

Bulletin 737–53–1058, Revision 4, dated 

January 9, 2014, terminates both the 

initial and repetitive inspections 

required by paragraph (j) of this AD. 

SWA also requested that repairs 

previously approved by a Boeing 

authorized representative via an FAA 

8100–9 form are terminating action to 

both the initial and repetitive inspection 

requirements required by paragraph (j) 

of the NPRM. 

We agree with the request because it 

was not intended that a separate initial 

inspection would be performed on 

airplanes that have the repair previously 

installed. We have deleted the word 

‘‘repetitive’’ from paragraphs (m)(1) 

through (m)(3) of this AD to clarify that 

accomplishing the actions in those 

paragraphs terminates certain initial and 

repetitive inspections. We have also 

added paragraph (m)(4) to this final 

rule, which specifies that the 

accomplishment of a repair of the aft 

lower corner of the forward airstair 

stowage doorway that was previously 

approved using FAA Form 8100–9, 

terminates the inspections required by 

paragraph (j) of this AD. 

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 (79 FR 

24628, May 1, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 24628, 

May 1, 2014). 

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 132 

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 ...... 5 work-hours × $85 per hour = $425 per inspection 

cycle.

None ............ $425 per inspection cycle $56,100 per inspection 

cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates for any on-condition actions 

specified in this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 


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Federal Register / Vol. 79, No. 241 / Tuesday, December 16, 2014 / Rules and Regulations 74601 

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): 

2014–25–09 The Boeing Company: 

Amendment 39–18051; Docket No. 

FAA–2014–0257; Directorate Identifier 

2014–NM–012–AD. 

(a) Effective Date 

This AD is effective January 20, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes, 

certificated in any category, as identified in 

Boeing Service Bulletin 737–53–1058, 

Revision 4, dated January 9, 2014. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01219SE (http://rgl.faa.

gov/Regulatory_and_Guidance_Library/

rgstc.nsf/0/ebd1cec7b301293e86257cb300

45557a/$FILE/ST01219SE.pdf) does not 

affect the ability to accomplish the actions 

required by this AD. Therefore, for airplanes 

on which STC ST01219SE 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. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

fatigue cracking in the skin assembly and 

bear strap of the aft lower corner of the 

forward airstair stowage doorway. We are 

issuing this AD to detect and correct fatigue 

cracking, which could result in rapid loss of 

cabin pressure. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections and Corrective Actions for 

Group 1 and Group 2 Airplanes That Do Not 

Have a Certain Repair or Preventative 

Modification Installed 

For Group 1 and Group 2 airplanes 

identified in Boeing Service Bulletin 737–53– 

1058, Revision 4, dated January 9, 2014, on 

which no repair or preventative modification 

has been done as specified in any of the 

service information identified in paragraphs 

(g)(1) through (g)(4) of this AD: At the 

applicable times specified in Table 1 of 

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

Service Bulletin 737–53–1058, Revision 4, 

dated January 9, 2014, except as required by 

paragraph (o)(1) of this AD, do high 

frequency eddy current and detailed 

inspections for cracking of the skin assembly 

and bear strap of the forward airstair stowage 

doorway, and do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 737– 

53–1058, Revision 4, dated January 9, 2014, 

except as required by paragraph (o)(2) of this 

AD. Do all applicable related investigative 

and corrective actions before further flight. 

Repeat the inspections at the applicable 

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

‘‘Compliance,’’ of Boeing Service Bulletin 

737–53–1058, Revision 4, dated January 9, 

2014, until the applicable terminating action 

specified in paragraph (m) of this AD is done. 

(1) Boeing Service Bulletin 737–53–1058, 

dated April 4, 1980. 

(2) Boeing Service Bulletin 737–53–1058, 

Revision 1, dated March 5, 1987. 

(3) Boeing Service Bulletin 737–53–1058, 

Revision 2, dated December 7, 1989. 

(4) Boeing Service Bulletin 737–53–1058, 

Revision 3, dated March 11, 1993. 

(h) Inspections and Corrective Actions for 

Group 1 and Group 2 Airplanes That Have 

a Certain Repair Installed 

For Group 1 and Group 2 airplanes 

identified in Boeing Service Bulletin 737–53– 

1058, Revision 4, dated January 9, 2014, on 

which a repair has been installed as specified 

in Boeing Service Bulletin 737–53–1058, 

dated April 4, 1980: Within the applicable 

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

‘‘Compliance,’’ of Boeing Service Bulletin 

737–53–1058, Revision 4, dated January 9, 

2014, except as required by paragraph (o)(1) 

of this AD, do a high frequency eddy current 

inspection for cracking of the bear strap of 

the forward airstair stowage doorway, and do 

low frequency eddy current and detailed 

inspections for cracking of the skin assembly 

and bear strap of the forward airstair stowage 

doorway; and do all applicable related 

investigative and corrective actions; in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 737– 

53–1058, Revision 4, dated January 9, 2014, 

except as required by paragraph (o)(2) of this 

AD. Do all applicable related investigative 

and corrective actions before further flight. 

Repeat the inspections at the applicable 

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

‘‘Compliance,’’ of Boeing Service Bulletin 

737–53–1058, Revision 4, dated January 9, 

2014, until the applicable terminating action 

specified in paragraph (m) of this AD is done. 

(i) Inspections and Corrective Actions for 

Group 1 and Group 2 Airplanes That Have 

a Certain Preventative Modification 

Installed 

For Group 1 and Group 2 airplanes 

identified in Boeing Service Bulletin 737–53– 

1058, Revision 4, dated January 9, 2014, on 

which a preventative modification has been 

installed as specified in any of the service 

information identified in paragraphs (i)(1) 

through (i)(4) of this AD: Within the 

applicable times specified in Table 1 of 

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

Service Bulletin 737–53–1058, Revision 4, 

dated January 9, 2014, except as required by 

paragraph (o)(1) of this AD, do a high 

frequency eddy current inspection for 

cracking of the bear strap of the forward 

airstair stowage doorway, a low frequency 

eddy current inspection for cracking of the 

skin assembly and bear strap of the forward 

airstair stowage doorway, and detailed 

inspections for cracking of the skin assembly 

and bear strap of the forward airstair stowage 

doorway; and do all related investigative and 

applicable corrective actions; in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 737–53–1058, 


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Revision 4, dated January 9, 2014, except as 

required by paragraph (o)(2) of this AD. Do 

all applicable related investigative and 

corrective actions before further flight. 

Repeat the inspections at the applicable 

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

‘‘Compliance,’’ of Boeing Service Bulletin 

737–53–1058, Revision 4, dated January 9, 

2014, until the applicable terminating action 

specified in paragraph (m) of this AD is done. 

(1) Boeing Service Bulletin 737–53–1058, 

dated April 4, 1980. 

(2) Boeing Service Bulletin 737–53–1058, 

Revision 1, dated March 5, 1987. 

(3) Boeing Service Bulletin 737–53–1058, 

Revision 2, dated December 7, 1989. 

(4) Boeing Service Bulletin 737–53–1058, 

Revision 3, dated March 11, 1993. 

(j) Inspections and Corrective Actions for 

Group 3 Through Group 5 Airplanes 

For Group 3 through Group 5 airplanes 

identified in Boeing Service Bulletin 737–53– 

1058, Revision 4, dated January 9, 2014: At 

the applicable times specified in Table 2 of 

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

Service Bulletin 737–53–1058, Revision 4, 

dated January 9, 2014, except as required by 

paragraph (o)(1) of this AD, do a high 

frequency eddy current inspection for 

cracking of the bear strap of the forward 

airstair stowage doorway, a low frequency 

eddy current inspection for cracking of the 

skin assembly and bear strap of the forward 

airstair stowage doorway, and detailed 

inspections for cracking of the skin assembly 

and bear strap of the forward airstair stowage 

doorway; and do all related investigative and 

applicable corrective actions; in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 737–53–1058, 

Revision 4, dated January 9, 2014, except as 

required by paragraph (o)(2) of this AD. Do 

all applicable related investigative and 

corrective actions before further flight. 

Repeat the inspections at the applicable 

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

‘‘Compliance,’’ of Boeing Service Bulletin 

737–53–1058, Revision 4, dated January 9, 

2014, until the applicable terminating action 

specified in paragraph (m) of this AD is done. 

(k) Inspections and Corrective Actions for 

Group 6 Airplanes 

For Group 6 airplanes identified in Boeing 

Service Bulletin 737–53–1058, Revision 4, 

dated January 9, 2014: Within 120 days after 

the effective date of this AD, inspect and 

repair any cracking using a method approved 

in accordance with the procedures specified 

in paragraph (q) of this AD. 

(l) Post-Repair and Post-Modification 

Inspections for Group 1 and Group 2 

Airplanes 

For Group 1 and Group 2 airplanes on 

which any repair has been done as specified 

in any of the service information identified 

in paragraphs (l)(1) through (l)(3) of this AD, 

or on which any repair or modification has 

been done as specified in the service 

information identified in paragraph (l)(4) of 

this AD: At the applicable times specified in 

Table 3 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Service Bulletin 737–53–1058, 

Revision 4, dated January 9, 2014, except as 

required by paragraph (o)(1) of this AD, do 

a high frequency eddy current inspection for 

cracking in the bear strap and skin assembly 

and a general visual inspection for cracking 

in the frame of the forward airstair stowage 

doorway; or do low frequency eddy current 

inspections for cracking of the skin assembly 

and bear strap of the forward airstair stowage 

doorway; in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–53–1058, Revision 4, 

dated January 9, 2014. Options provided in 

Boeing Service Bulletin 737–53–1058, 

Revision 4, dated January 9, 2014, for 

accomplishing the inspections are acceptable 

for compliance with the corresponding 

requirements of this paragraph provided that 

the inspections are done at the applicable 

times specified in paragraph 1.E., 

‘‘Compliance,’’ of the Boeing Service Bulletin 

737–53–1058, Revision 4, dated January 9, 

2014. If any cracking is found, before further 

flight, repair the cracking using a method 

approved in accordance with the procedures 

specified in paragraph (q) of this AD. Repeat 

the inspections at the applicable times 

specified in Table 3 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

737–53–1058, Revision 4, dated January 9, 

2014. 

(1) Boeing Service Bulletin 737–53–1058, 

Revision 1, dated March 5, 1987. 

(2) Boeing Service Bulletin 737–53–1058, 

Revision 2, dated December 7, 1989. 

(3) Boeing Service Bulletin 737–53–1058, 

Revision 3, dated March 11, 1993. 

(4) Boeing Service Bulletin 737–53–1058, 

Revision 4, dated January 9, 2014. 

(m) Optional Terminating Actions 

(1) For Group 1 and Group 2 airplanes 

identified in Boeing Service Bulletin 737–53– 

1058, Revision 4, dated January 9, 2014: 

Accomplishment of a repair for cracking of 

the skin assembly and bear strap of the 

forward airstair stowage doorway before the 

effective date of this AD, using any service 

information specified in paragraphs (m)(1)(i) 

through (m)(1)(iv) of this AD, terminates the 

inspections required by paragraphs (g), (h), 

and (i) of this AD. 

(i) Boeing Service Bulletin 737–53–1058, 

Revision 1, dated March 5, 1987. 

(ii) Boeing Service Bulletin 737–53–1058, 

Revision 2, dated December 7, 1989. 

(iii) Boeing Service Bulletin 737–53–1058, 

Revision 3, dated March 11, 1993. 

(iv) Boeing Service Bulletin 737–53–1058, 

Revision 4, dated January 9, 2014. 

(2) For Group 1 and Group 2 airplanes 

identified in Boeing Service Bulletin 737–53– 

1058, Revision 4, dated January 9, 2014: 

Accomplishment of a preventative 

modification for cracking of the skin 

assembly and bear strap of the forward 

airstair stowage doorway before the effective 

date of this AD, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–53–1058, Revision 4, 

dated January 9, 2014, terminates the 

inspections required by paragraphs (g), (h), 

and (i) of this AD. 

(3) For Group 3 through Group 5 airplanes 

identified in Boeing Service Bulletin 737–53– 

1058, Revision 4, dated January 9, 2014: 

Repairing or modifying the forward airstair 

stowage doorway, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–53–1058, Revision 4, 

dated January 9, 2014, terminates the 

inspections required by paragraph (j) of this 

AD. 

(4) Accomplishment, prior to the effective 

date of this AD, of a repair of the aft lower 

corner of the forward airstair stowage 

doorway that was approved by Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) using FAA 

Form 8100–9, terminates the inspections 

required by paragraph (j) of this AD. 

(n) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (g), (h), and 

(i) of this AD, if those actions were performed 

before the effective date of this AD using any 

service information specified in paragraphs 

(n)(i) through (n)(iii) of this AD. 

(i) Boeing Service Bulletin 737–53–1058, 

Revision 1, dated March 5, 1987. 

(ii) Boeing Service Bulletin 737–53–1058, 

Revision 2, dated December 7, 1989. 

(iii) Boeing Service Bulletin 737–53–1058, 

Revision 3, dated March 11, 1993. 

(o) Exceptions to the Service Information 

(1) Where Boeing Service Bulletin 737–53– 

1058, Revision 4, dated January 9, 2014, 

specifies a compliance time ‘‘after the 

Revision 4 date of this service bulletin,’’ this 

AD requires compliance within the specified 

compliance time ‘‘after the effective date of 

this AD.’’ 

(2) Where Boeing Service Bulletin 737–53– 

1058, Revision 4, dated January 9, 2014, 

specifies to contact Boeing for repair 

instructions: Before further flight, repair 

using a method approved in accordance with 

the procedures specified in paragraph (q) of 

this AD. 

(p) Post-Repair and Post-Modification 

Inspections for Group 3 Through Group 5 

Airplanes Not Required 

The post-repair and post-modification 

inspections specified in Table 4 of paragraph 

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

Bulletin 737–53–1058, Revision 4, dated 

January 9, 2014, are not required by this AD. 

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

post-repair and post-modification inspections 

specified in Table 4 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

737–53–1058, Revision 4, dated January 9, 

2014, may be used in support of compliance 

with section 121.1109(c)(2) or 129.109(b)(2) 

of the Federal Aviation Regulations (14 CFR 

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

(q) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

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

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


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Federal Register / Vol. 79, No. 241 / Tuesday, December 16, 2014 / Rules and Regulations 74603 

(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. 

(r) Related Information 

(1) For more information about this AD, 

contact Nenita Odesa, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office, 3960 

Paramount Boulevard, Lakewood, CA 90712– 

4137; phone: (562) 627–5234; fax: (562) 627– 

5210; email: nenita.odesa@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (s)(3) and (s)(4) of this AD. 

(s) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Service Bulletin 737–53–1058, 

Revision 4, dated January 9, 2014. 

(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 view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

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

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://www.archives.

gov/federal-register/cfr/ibr-locations.html. 

Issued in Renton, Washington, on 

December 5, 2014. 

Michael J. Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–29190 Filed 12–15–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0566; Directorate 

Identifier 2014–NM–041–AD; Amendment 

39–18050; AD 2014–25–08] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Aviation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Dassault Aviation Model FALCON 2000 

and FALCON 2000EX airplanes. This 

AD was prompted by a design review, 

which revealed that the forward 

servicing compartment (FSC) is 

configured with tie-down points. This 

AD requires inspecting the FSC for 

installed tie-down points, and removing 

those tie-down points. We are issuing 

this AD to detect and correct installed 

tie-down points, which could lead to 

inadvertent use of the FSC as a cargo 

compartment, which could result in 

damage to the structure of the airplane 

or potential risk of fire. 

DATES: This AD becomes effective 

January 20, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 20, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://www.

regulations.gov/#!docketDetail;D=FAA2014-0566; or in person at the 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. 

For service information identified in 

this AD, contact Dassault Falcon Jet, 

P.O. Box 2000, South Hackensack, NJ 

07606; telephone 201–440–6700; 

Internet http://www.dassaultfalcon.com. 

You may view this 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. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1137; 

fax 425- 227–1149. 

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 certain Dassault Aviation 

Model FALCON 2000 and FALCON 

2000EX airplanes. The NPRM published 

in the Federal Register on August 14, 

2014 (79 FR 47592). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2014–0027R1, 

dated February 5, 2014 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for certain Dassault Aviation Model 

FALCON 2000 and FALCON 2000EX 

airplanes. The MCAI states: 

The Forward Servicing Compartment (FSC) 

of the Falcon 2000 is an unpressurized 

service compartment located between 

fuselage frames 26 and 33. This compartment 

is accessible from a lockable external door 

located in the lower aft fuselage. 

A design review has brought to light that 

the compartment is configured with tie-down 

points, which were used by operators to fix 

loads (e.g. ski or golf bags) in that 

compartment. However, the FSC has not been 

designed and consequently demonstrated as 

being compliant with cargo compartment 

airworthiness requirements. 

This condition, if not corrected, could lead 

to inadvertent use of the FSC as [a] cargo 

compartment, which could result in damage 

to the structure of the aeroplane or potential 

risk of fire. 

To address this potential unsafe condition, 

Dassault Aviation issued Service Bulletin 

(SB) F2000–407 and SB F2000EX–289, as 

applicable, which provide instructions for 

removal of the tie-down points. 

For the reasons described above, this 

[EASA] AD requires removal of the tie-down 

points from the FSC. 

Note: Operators are also reminded about 

the intended function of the FSC. 

This [EASA] AD is revised to clarify the 

AD Applicability and to correct the [type 

certificate data sheet] TCDS Number. 

Required actions include inspecting 

for installed tie-down points. You may 

examine the MCAI in the AD docket on 

the Internet at http://www.regulations.

gov/#!documentDetail;D=FAA-2014- 

0566-0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 47592, August 14, 2014) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 


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