Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations 51447 

Programs, 7121 Southwest Boulevard, 

Wichita, KS 67215. Provide the brushes and 

the information specified in paragraphs 

(m)(1) through (m)(6) of this AD within 30 

days after the replacement if the replacement 

was done on or after the effective date of this 

AD, or within 30 days after the effective date 

of this AD if the replacement was done before 

the effective date of this AD. 

(1) The model and serial number of the 

airplane. 

(2) The part number of the motor. 

(3) The part number of the brushes, if 

known. 

(4) The elapsed time, in motor hours, since 

the last brush/motor replacement, if known. 

(5) If motor hours are unknown, report the 

elapsed airplane flight hours since the last 

brush/motor replacement, and indicate that 

motor hours are unknown. 

(6) The number of motor hours currently 

displayed on the pallet hour meter, if 

installed. 

(n) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install an A/C compressor motor 

having P/N FWA1134104–1 or P/N 

FWA1134104–5, unless the inspection 

specified in paragraph (h) of this AD is done 

before installation, and the replacements 

specified in paragraph (i) of this AD are 

subsequently done in accordance with the 

applicable service information identified in 

paragraphs (j)(1) through (j)(6) of this AD at 

the times specified in paragraph (i) of this 

AD. 

(o) Special Flight Permit Limitation 

Special flight permits may be issued in 

accordance with sections 21.197 and 21.199 

of the Federal Aviation Regulations (14 CFR 

21.197 and 21.199) with the following 

limitation: Operation of the A/C system is 

prohibited. 

(p) Paperwork Reduction Act Burden 

Statement 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject to 

a penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork Reduction 

Act unless that collection of information 

displays a current valid OMB Control 

Number. The OMB Control Number for this 

information collection is 2120–0056. Public 

reporting for this collection of information is 

estimated to be approximately 5 minutes per 

response, including the time for reviewing 

instructions, completing and reviewing the 

collection of information. All responses to 

this collection of information are mandatory. 

Comments concerning the accuracy of this 

burden and suggestions for reducing the 

burden should be directed to the FAA at: 800 

Independence Ave. SW., Washington, DC 

20591, Attn: Information Collection 

Clearance Officer, AES–200. 

(q) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Wichita 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) of this AD. 

(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. 

(r) Related Information 

For more information about this AD, 

contact Craig Henrichsen, Aerospace 

Engineer, Electrical Systems and Avionics 

Branch, ACE–119W, FAA, Wichita ACO, 

1801 Airport Road, Room 100, Mid-Continent 

Airport, Wichita, KS 67209; phone: 316–946– 

4110; fax: 316–946–4107; email: 

Craig.Henrichsen@faa.gov. 

(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) Subject 4–11–00, Replacement Time 

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 6, dated June 23, 2014, 

of the Cessna Model 500/501 Maintenance 

Manual. 

(ii) Subject 4–11–00, Replacement Time 

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 10, dated June 23, 

2014, of the Cessna Model 550/551 

Maintenance Manual. 

(iii) Subject 4–11–00, Replacement Time 

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 12, dated June 23, 

2014, of the Cessna Model 550 Bravo 

Maintenance Manual. 

(iv) Subject 4–11–00, Replacement Time 

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 9, dated June 23, 2014, 

of the Cessna Model S550 Maintenance 

Manual. 

(v) Subject 4–11–00, Replacement Time 

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 22, dated June 23, 

2014, of the Cessna Model 560 Maintenance 

Manual. 

(vi) Subject 4–11–00, Replacement Time 

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 32, dated June 23, 

2014, of the Cessna Model 650 Maintenance 

Manual. 

(3) For service information identified in 

this AD, contact Cessna Aircraft Co., P.O. Box 

7706, Wichita, KS 67277; phone: 316–517– 

6215; fax: 316–517–5802; email: 

citationpubs@cessna.textron.com; Internet 

https://www.cessnasupport.com/

newlogin.html. 

(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/ibrlocations.html. 

Issued in Renton, Washington, on August 

10, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–20692 Filed 8–24–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0242; Directorate 

Identifier 2014–NM–100–AD; Amendment 

39–18240; AD 2015–17–07] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Airbus Model A300 B4–603, B4–605R, 

B4–620, B4–622, B4–622R airplanes; all 

Airbus Model A300 C4–605R Variant F 

airplanes; and certain Airbus Model 

A300 F4–605R airplanes. This AD was 

prompted by the manufacturer’s review 

of all repairs accomplished using the 

structural repair manual. This review 

was done using revised fatigue and 

damage tolerance calculations. This AD 

requires an inspection of the 

surrounding panels of the left and right 

forward passenger doors, and corrective 

actions if necessary. We are issuing this 

AD to detect and correct previous 

incomplete or inadequate repairs to the 

surrounding panels of the left and right 

forward passenger doors and the failsafe ring, which could negatively affect 

the structural integrity of the airplane. 

DATES: This AD becomes effective 

September 29, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 29, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-0242 or in 

person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, M– 


Lhorne on DSK5TPTVN1PROD with RULES
51448 Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

For service information identified in 

this AD, contact Airbus SAS, 

Airworthiness Office—EAW, 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. 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. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

0242. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–2125; 

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 all Airbus Model A300 B4–603, 

B4–605R, B4–620, B4–622, B4–622R 

airplanes; all Airbus Model A300 C4– 

605R Variant F airplanes; and certain 

Airbus Model A300 F4–605R airplanes. 

The NPRM published in the Federal 

Register on February 18, 2015 (80 FR 

8566). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0101, dated May 2, 2014 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for all Airbus Model A300 

B4–603, B4–605R, B4–620, B4–622, B4– 

622R airplanes; all Airbus Model A300 

C4–605R Variant F airplanes; and 

certain Airbus Model A300 F4–605R 

airplanes. The MCAI states: 

In the frame of the Ageing Airplane Safety 

Rule (AASR), all existing Structural Repair 

Manual (SRM) repairs were reviewed. 

This analysis, which consisted in new 

Fatigue and Damage Tolerance calculations, 

revealed that some repairs in the area 

surrounding the forward passenger/crew 

door and the fail safe ring are no longer 

adequate. 

These repairs, if not reworked, could affect 

the structural integrity of the aeroplane. 

To address this potential unsafe condition, 

Airbus issued Service Bulletin (SB) A300– 

53–6173 (later revised), to provide 

instructions for the inspection of repairs on 

the left-hand (LH) and right-hand (RH) 

forward door surrounding panels. 

For the reasons described above, and 

further to the AASR implementation, this 

[EASA] AD requires a one-time inspection of 

the forward door surrounding panels to 

identify SRM repairs in these areas and, 

depending on findings, accomplishment of 

applicable corrective action(s). 

Corrective actions include rework or 

repair. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2015-0242- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (80 

FR 8566, February 18, 2015) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (80 FR 8566, 

February 18, 2015) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (80 FR 8566, 

February 18, 2015). 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A300–53–6173, Revision 01, dated 

February 28, 2014. The service 

information describes procedures for a 

one-time detailed of the area 

surrounding the forward passenger/crew 

door and the fail safe ring to determine 

if any repairs have been done, and 

corrective actions. This service 

information is reasonably available 

because the interested parties have 

access to it through their normal course 

of business or by the means identified 

in the ADDRESSES section of this AD. 

Costs of Compliance 

We estimate that this AD affects 65 

airplanes of U.S. registry. 

We also estimate that it will take 

about 120 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $663,000, or $10,200 per 

product. 

In addition, we estimate that any 

necessary follow-on actions will take up 

to 730 work-hours and require parts 

costing up to $72,250, for a cost of up 

to $134,300 per product. We have no 

way of determining the number of 

aircraft that might need these actions. 

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 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 the 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-0242; 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 


Lhorne on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations 51449 

information. The street address for the 

Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. 

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): 

2015–17–07 Airbus: Amendment 39–18240. 

Docket No. FAA–2015–0242; Directorate 

Identifier 2014–NM–100–AD. 

(a) Effective Date 

This AD becomes effective September 29, 

2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes 

identified in paragraphs (c)(1), (c)(2), and 

(c)(3) of this AD, certificated in any category. 

(1) Model A300 B4–603, B4–605R, B4–620, 

B4–622, and B4–622R airplanes, all 

manufacturer serial numbers. 

(2) Model A300 C4–605R Variant F 

airplanes, all manufacturer serial numbers. 

(3) Model A300F4–605R airplanes, all 

manufacturer serial numbers, except those on 

which Airbus Modification 12699 was 

embodied in production. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by the 

manufacturer’s review of all repairs 

accomplished using the structural repair 

manual. This review was done using revised 

fatigue and damage tolerance calculations. 

We are issuing this AD to detect and correct 

previous incomplete or inadequate repairs to 

the surrounding panels of the left and right 

forward passenger doors and the fail-safe 

ring, which could negatively affect the 

structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

At the time specified in paragraph (g)(1) or 

(g)(2) of this AD, whichever is later: Do a 

detailed inspection of the surrounding panels 

of the left and right forward passenger doors 

to determine if any repairs have been done, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

53–6173, Revision 01, dated February 28, 

2014. 

(1) Prior to the accumulation of 30,000 

total flight cycles or 67,500 total flight hours, 

whichever occurs first. 

(2) Within 28 months after the effective 

date of this AD. 

(h) Identification of Repairs 

If any affected repair is found during the 

inspection required by paragraph (g) of this 

AD: Before further flight, identify the 

reworked area(s), the percentage of the 

rework, and the limits of the rework, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

53–6173, Revision 01, dated February 28, 

2014. 

(i) Corrective Actions 

During the repair identification required by 

paragraph (h) of this AD, if any rework is 

found that is outside the allowable damage 

limits specified in Airbus Service Bulletin 

A300–53–6173, Revision 01, dated February 

28, 2014: Before further flight, rework or 

repair, as applicable, using a method 

approved by the Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA; the European Aviation 

Safety Agency (EASA); or Airbus’s EASA 

Design Organization Approval (DOA). 

(j) Exception to Service Information 

Specifications 

Although Airbus Service Bulletin A300– 

53–6173, Revision 01, dated February 28, 

2014, specifies to contact Airbus for repair 

instructions, and specifies that action as 

‘‘RC’’ (Required for Compliance), this AD 

requires repair before further flight using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; EASA; or 

Airbus’s EASA DOA. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

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

this AD, if those actions were performed 

before the effective date of this AD using 

Airbus Service Bulletin A300–53–6173, 

dated August 1, 2013, which is not 

incorporated by reference in this AD. 

(l) 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–2125; 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. The AMOC approval letter 

must specifically reference this AD. 

(2) Required for Compliance (RC): Except 

as required by paragraph (j) of this AD: If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures and tests that 

are not identified as RC are recommended. 

Those procedures and tests that are not 

identified as RC may be deviated from using 

accepted methods in accordance with the 

operator’s maintenance or inspection 

program without obtaining approval of an 

AMOC, provided the procedures and tests 

identified as RC can be done and the airplane 

can be put back in a serviceable condition. 

Any substitutions or changes to procedures 

or tests identified as RC require approval of 

an AMOC. 

(3) 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; 

the EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0101, dated 

May 2, 2014, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov/

#!documentDetail;D=FAA-2015-0242-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(n) 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 A300–53–6173, 

Revision 01, dated February 28, 2014. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 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, 


Lhorne on DSK5TPTVN1PROD with RULES
51450 Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Rules and Regulations 

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/ibrlocations.html. 

Issued in Renton, Washington, on August 

10, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–20585 Filed 8–24–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0772; Directorate 

Identifier 2014–NM–090–AD; Amendment 

39–18233; AD 2015–16–08] 

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) 2011–08– 

51 for certain The Boeing Company 

Model 737–300, –400, and –500 series 

airplanes. AD 2011–08–51 required 

repetitive inspections of the lap joint at 

certain stringers along the entire length 

from certain body stations. This new AD 

expands the inspection area, requires 

additional inspections for cracks and 

open pockets, requires corrective 

actions if necessary, and revises the 

compliance times. This AD was 

prompted by an evaluation by the 

design approval holder (DAH) that has 

determined that the lower fastener holes 

in the lower skin of the fuselage lap 

splice are subject to widespread fatigue 

damage (WFD). We are issuing this AD 

to detect and correct fatigue cracking of 

the lower fastener holes in the lower 

skin of the fuselage lap splice, which 

could result in reduced structural 

integrity of the airplane. 

DATES: This AD is effective September 

29, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 29, 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://

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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA 2014– 

0772. 

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– 

0772; 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: 

Jennifer Tsakoumakis, Aerospace 

Engineer, Airframe Branch, ANM–120L, 

FAA, Los Angeles Aircraft Certification 

Office (ACO), 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5264; fax: 562–627– 

5210; email: jennifer.tsakoumakis@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2011–08–51, 

Amendment 39–16701 (76 FR 28632, 

May 18, 2011). AD 2011–08–51 applied 

to certain The Boeing Company Model 

737–300, –400, and –500 series 

airplanes. The NPRM published in the 

Federal Register on November 17, 2014 

(79 FR 68381). The NPRM was 

prompted by an evaluation by the DAH 

that has determined that the lower 

fastener holes in the lower skin of the 

fuselage lap splice are subject to WFD. 

The NPRM proposed to continue to 

require repetitive inspections of the lap 

joint at certain stringers along the entire 

length from certain body stations. The 

NPRM also proposed to expand the 

inspection area, require additional 

inspections for cracks and open pockets, 

require corrective actions if necessary, 

and revise the compliance times. We are 

issuing this AD to detect and correct 

fatigue cracking of the lower fastener 

holes in the lower skin of the fuselage 

lap splice, which could result in 

reduced structural integrity of the 

airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 68381, 

November 17, 2014) and the FAA’s 

response to each comment. 

Request To Revise Wording 

Boeing requested that we revise the 

last sentence in paragraph (k) of the 

proposed AD (79 FR 68381, November 

17, 2014) to clarify that the on-condition 

actions may be ‘‘inspection or repair’’ 

rather than ‘‘inspection and repair.’’ 

Boeing stated that condition 10 in table 

6 of Boeing Alert Service Bulletin 737– 

53A1319, Revision 2, dated April 4, 

2014, describes obtaining inspection or 

repair instructions. Boeing explained 

that, depending on the configuration 

details identified, repetitive inspections 

alone may be an appropriate action, or 

a repair may be the appropriate action. 

We agree with the commenter’s 

request. Varying detail configurations 

and the total flight cycles at the time of 

the finding are used to determine if an 

inspection program is adequate to 

address the unsafe condition or if 

installation of a repair is required. We 

have revised the wording in paragraph 

(k) of this AD to require inspection or 

repair. 

Request To Clarify Paragraph Heading 

Southwest Airlines (SWA) stated that 

the heading ‘‘Repetitive Inspections for 

Crack Indications at Stringers S–4R and 

S–4L, Body Station (BS) 360 to BS 908,’’ 

of paragraph (g) of the proposed AD (79 

FR 68381, November 17, 2014) is 

misleading. SWA explained that the 

heading is confusing since the 

paragraph contains both an initial 

inspection and repetitive inspections. 

We agree to clarify the terminology 

used in the heading. When the term 

‘‘repetitive’’ is used, it does not 

necessarily exclude the initial action. 

Many existing ADs use the term 

‘‘repetitive’’ in the headers for 

paragraphs that contain both the initial 

action and repetitive actions. We find 

that no change to this AD is necessary 

regarding this issue. 


Lhorne on DSK5TPTVN1PROD with RULES