27986 Federal Register / Vol. 81, No. 89 / Monday, May 9, 2016 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4808; Directorate 

Identifier 2014–NM–134–AD; Amendment 

39–18509; AD 2016–09–11] 

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 certain 

Airbus Model A330–200, –200 

Freighter, and –300 series airplanes; and 

Model A340–200 and –300 series 

airplanes. This AD was prompted by 

reports that cracks were found on an 

adjacent hole of certain frames of the 

center wing box (CWB). This AD 

requires removing fasteners, doing a 

rototest inspection of fastener holes, 

installing new fasteners, oversizing the 

holes and doing rototest inspections for 

cracks if necessary, and repairing any 

cracking that is found. We are issuing 

this AD to detect and correct cracking 

on certain holes of certain frames of the 

CWB that could affect the structural 

integrity of the airplane. 

DATES: This AD becomes effective June 

13, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 13, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus SAS, Airworthiness Office— 

EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone 

+33 5 61 93 36 96; fax +33 5 61 93 45 

80; email airworthiness.A330-A340@

airbus.com; Internet http://

www.airbus.com. 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– 

4808. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

4808; 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 street address for 

the Docket Operations office (telephone 

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. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1138; 

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 Airbus Model A330– 

200, –200 Freighter, and –300 series 

airplanes; and Model A340–200 and 

–300 series airplanes. The NPRM 

published in the Federal Register on 

November 2, 2015 (80 FR 67348) (‘‘the 

NPRM’’). We are issuing this AD to 

detect and correct cracking on certain 

holes of certain frames of the CWB, 

which could affect the structural 

integrity of the airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0149, dated June 13, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for certain Airbus 

Model A330–200, –200 Freighter, and 

–300 series airplanes; and Model A340– 

200 and –300 series airplanes. The 

MCAI states: 

During accomplishment of A330 

Airworthiness Limitation Item (ALI) task 57– 

11–04 on the rear fitting of the Frame (FR) 

40 between stringers 38 and 39 on both [lefthand] LH/[right-hand] RH sides, cracks were 

found on an adjacent hole. After reaming at 

second oversize of the subject hole, the crack 

was still present. 

Other crack findings on this adjacent hole 

have been reported on A330 and A340–200/ 

300 aeroplanes as a result of sampling 

inspections. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

For the reasons described above, this 

[EASA] AD requires removal of the fasteners 

and repetitive rototest inspections of fastener 

holes at FR40 vertical web located above 

Center Wing Box (CWB) lower panel 

reference and/or below CWB lower panel 

reference on both sides and, depending on 

findings, accomplishment of the applicable 

corrective actions. 

Note: These holes affected by this [EASA] 

AD are different from the ones affected by 

EASA AD 2009–0001 [http://ad.easa.europa.

eu/blob/easa_ad_2009_0001.pdf/AD_2009- 

0001_1]. 

Required actions also include 

oversizing certain holes, installing new 

fasteners, and repairing any cracking 

that is found. The initial compliance 

times range from 13,500 to 30,900 flight 

cycles, or 57,000 to 162,000 flight hours, 

depending on airplane operation and 

utilization. The repetitive compliance 

times are 7,400 flight cycles/24,300 

flight hours or 5,950 flight cycles/40,400 

flight hours from ALI embodiment. You 

may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

4808. 

Change Made to the Format of 

Paragraph (g) of This AD 

At the request of the Office of the 

Federal Register, we have revised the 

format of paragraph (g) of this AD by 

converting the table to text. This change 

to the format does not affect the 

requirements of that paragraph. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. The 

commenter, Bowen Gass, supported the 

NPRM. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, 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 for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued the following 

service information. The service 

information describes procedures for 

removing the fasteners and doing a 

repetitive rototest inspection of fastener 

holes at FR40 vertical web on both 

sides, installing new fasteners in 

transition fit, and oversizing the holes. 

• Airbus Service Bulletin A330–57– 

3114, dated March 12, 2013. 

• Airbus Service Bulletin A330–57– 

3115, dated April 4, 2013. 

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Federal Register / Vol. 81, No. 89 / Monday, May 9, 2016 / Rules and Regulations 27987 

• Airbus Service Bulletin A330–57– 

3116, dated March 12, 2013. 

• Airbus Service Bulletin A340–57– 

4123, dated March 12, 2013. 

• Airbus Service Bulletin A340–57– 

4124, Revision 01, dated August 22, 

2013. 

• Airbus Service Bulletin A340–57– 

4125, dated March 12, 2013. 

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. 

Costs of Compliance 

We estimate that this AD affects 35 

airplanes of U.S. registry. 

We also estimate that it will take 

about 78 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Required parts will cost 

about $0 per product. Based on these 

figures, we estimate the cost of this AD 

on U.S. operators to be $232,050, per 

inspection cycle, or $6,630 per product, 

per inspection cycle. 

In addition, we estimate that any 

necessary follow-on actions will take 

about 98 work-hours and require parts 

costing $136,400, for a cost of up to 

$144,730 per product. We have no way 

of determining the number of aircraft 

that might need this action. 

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. 

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): 

2016–09–11 Airbus: Amendment 39–18509. 

Docket No. FAA–2015–4808; Directorate 

Identifier 2014–NM–134–AD. 

(a) Effective Date 

This AD becomes effective June 13, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) and (c)(2) of this AD, 

certificated in any category, all manufacturer 

serial numbers, except those on which 

Airbus Modification (Mod) 55792 or Mod 

55306 has been embodied in production, and 

except those on which Airbus Repair 

Instruction R57115092 has been embodied in 

service on both right-hand (RH) and left-hand 

(LH) sides. 

(1) Airbus Model A330–201, –202, –203, 

–223, –223F, –243 –243F, –301, –302, –303, 

–321, –322, –323, –341, –342, and –343 

airplanes. 

(2) Airbus Model A340–211, –212, –213, 

–311, –312, and –313 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by reports that 

cracks were found on an adjacent hole of 

certain frames of the center wing box (CWB). 

We are issuing this AD to detect and correct 

cracking on certain holes of the CWB, which 

could affect the structural integrity of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

Do a rototest inspection of the fastener 

holes at the frame (FR) 40 vertical web, on 

both sides, as specified in paragraphs (g)(1) 

through (g)(6) of this AD, except as required 

by paragraph (k) of this AD. 

(1) For Model A330–300 series airplanes in 

pre-mod 44360 configuration: At the later of 

the times specified in paragraphs (g)(1)(i) and 

(g)(1)(ii) of this AD, inspect below the CWB 

lower panel reference, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–57–3114, dated March 

12, 2013. 

(i) At the applicable time specified in 

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

Service Bulletin A330–57–3114, dated March 

12, 2013. 

(ii) Within 2,400 flight cycles or 24 months 

after the effective date of this AD, whichever 

occurs first. 

(2) For Model A330–200 series airplanes in 

post-mod 44360 and pre-mod 49202 

configuration: At the later of the times 

specified in paragraphs (g)(2)(i) and (g)(2)(ii) 

of this AD, inspect below the CWB lower 

panel reference, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–57–3116, dated March 

12, 2013. 

(i) At the applicable time specified in 

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

Service Bulletin A330–57–3116, dated March 

12, 2013. 

(ii) Within 2,400 flight cycles or 24 months 

after the effective date of this AD, whichever 

occurs first. 

(3) For Model A330–200 and –300 series 

airplanes in pre-mod 55306 and pre-mod 

55792 configuration: At the later of the times 

specified in paragraphs (g)(3)(i) and (g)(3)(ii) 

of this AD, inspect above the CWB lower 

panel reference, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A330–57–3115, dated April 

4, 2013. 

(i) At the applicable time specified in 

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

Service Bulletin A330–57–3115, dated April 

4, 2013. 

(ii) Within 2,400 flight cycles or 24 months 

after the effective date of this AD, whichever 

occurs first. 

(4) For Model A340–200 and –300 series 

airplanes in pre-mod 44360 configuration: At 

the later of the times specified in paragraphs 

(g)(4)(i) and (g)(4)(ii) of this AD, inspect 

below the CWB lower panel reference, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A340– 

57–4123, dated March 12, 2013. 

(i) At the applicable time specified in 

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

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27988 Federal Register / Vol. 81, No. 89 / Monday, May 9, 2016 / Rules and Regulations 

Service Bulletin A330–57–4123, dated March 

12, 2013. 

(ii) Within 1,300 flight cycles or 24 months 

after the effective date of this AD, whichever 

occurs first. 

(5) For Model A340–200 and –300 series 

airplanes in pre-mod 55306 and pre-mod 

55792 configuration: At the later of the times 

specified in paragraphs (g)(5)(i) and (g)(5)(ii) 

of this AD, inspect above the CWB lower 

panel reference, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A340–57–4124, Revision 01, 

dated August 22, 2013. 

(i) At the applicable time specified in 

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

Service Bulletin A340–57–4124, Revision 01, 

dated August 22, 2013. 

(ii) Within 1,300 flight cycles or 24 months 

after the effective date of this AD, whichever 

occurs first. 

(6) For Model A340–200 and –300 series 

airplanes in post-mod 44360 and pre-mod 

49202 configuration: At the later of the times 

specified in paragraphs (g)(6)(i) and (g)(6)(ii) 

of this AD, inspect below the CWB lower 

panel reference, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A340–57–4125, dated March 

12, 2013. 

(i) At the applicable time specified in 

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

Service Bulletin A340–57–4125, dated March 

12, 2013. 

(ii) Within 1,300 flight cycles or 24 months 

after the effective date of this AD, whichever 

occurs first. 

(h) Follow-on Actions: No Cracking 

If no crack is found during any inspection 

required by paragraph (g) of this AD, do the 

actions specified in paragraphs (h)(1) and 

(h)(2) of this AD. 

(1) Before further flight, install new 

fasteners in the transition fit, in accordance 

with the Accomplishment Instructions of the 

applicable service information identified in 

paragraph (g) of this AD. 

(2) Repeat the inspection required by 

paragraph (g) of this AD thereafter at the 

applicable time identified in paragraph 1.E., 

‘‘Compliance,’’ of the applicable service 

information identified in paragraph (g) of this 

AD. 

(i) Follow-on Actions for Crack Findings 

If any crack is found during any inspection 

required by paragraph (g) of this AD: Before 

further flight, oversize the holes to the first 

oversize in comparison with the current hole 

diameter, and do a rototest inspection for 

cracks, in accordance with the 

Accomplishment Instructions of the 

applicable service information identified in 

paragraph (g) of this AD. 

(1) If no cracking is found during the 

rototest inspection required by paragraph (i) 

of this AD, do the actions specified in 

paragraphs (i)(1)(i) and (i)(1)(ii) of this AD. 

(i) Before further flight: Install new 

fasteners in the transition fit, in accordance 

with the Accomplishment Instructions of the 

applicable service information identified in 

paragraph (g) of this AD. 

(ii) Repeat the inspection required by 

paragraph (g) of this AD thereafter at the 

applicable time identified in paragraph 1.E., 

‘‘Compliance,’’ of the applicable service 

information identified in paragraph (g) of this 

AD. 

(2) If cracking is found during the rototest 

inspection required by paragraph (i) of 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). 

(j) Terminating Action Specifications 

Accomplishment of the initial and 

repetitive inspections required by this AD 

terminates accomplishment of Airworthiness 

Limitation Items Tasks 57–11–04 and 57–11– 

02 of the Airworthiness Limitation Section 

(ALS) Part 2, Damage Tolerant Airworthiness 

Limitation Items (DT ALI). 

(1) Installation of new fasteners, as 

specified in paragraph (h)(1) of this AD, does 

not terminate the repetitive inspections 

required by paragraph (g) of this AD. 

(2) Accomplishment of the corrective 

actions specified in the introductory text of 

paragraph (i) and paragraph (i)(1) of this AD 

does not terminate the repetitive inspections 

required by paragraph (g) of this AD. 

(3) Accomplishment of the repair specified 

in paragraph (i)(2) of this AD does not 

terminate repetitive inspections required by 

paragraph (g) of this AD, unless the approved 

repair method specifies otherwise. 

(k) Exceptions to Service Information 

(1) If the applicable service information 

identified in paragraph (g) of this AD 

specifies contacting Airbus for appropriate 

action: Before further flight, repair using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the EASA; or 

Airbus’s EASA DOA. 

(2) Where paragraph 1.E., ‘‘Compliance,’’ of 

the applicable service information specified 

in paragraph (g) of this AD specifies a 

compliance time in terms of a ‘‘Threshold’’ 

and ‘‘Grace Period,’’ this AD requires 

compliance at the later of the applicable 

threshold and grace period. 

(3) Where paragraph 1.E., ‘‘Compliance,’’ of 

the applicable service information specified 

in paragraph (g) of this AD specifies a 

threshold as ‘‘before next flight,’’ this AD 

requires compliance before the next flight 

after the applicable finding. 

(l) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (g) and (i) of this AD, 

if those actions were performed before the 

effective date of this AD using the applicable 

service information specified in paragraph 

(l)(1), (l)(2), (l)(3), (l)(4), (l)(5), (l)(6), (l)(7), 

(l)(8), or (l)(9) of this AD. This service 

information is not incorporated by reference 

in this AD. 

(1) Airbus Technical Disposition 

LR57D11023270, Issue B, dated July 12, 

2011. 

(2) Airbus Technical Disposition 

LR57D11029171, Issue B, dated September 6, 

2011. 

(3) Airbus Technical Disposition 

LR57D11029173, Issue B, dated September 6, 

2011. 

(4) Airbus Technical Disposition 

LR57D11030741, Issue B, dated September 

22, 2011. 

(5) Airbus Technical Disposition 

LR57D11029170, Issue C, dated September 6, 

2011. 

(6) Airbus Technical Disposition 

LR57D11023714, Issue B, dated July 12, 

2011. 

(7) Airbus Technical Disposition 

LR57D11029172, Issue B, dated September 6, 

2011. 

(8) Airbus Technical Disposition 

LR57D11030740, Issue C, dated September 

22, 2011. 

(9) Airbus Service Bulletin A340–57–4124, 

dated April 4, 2013. 

(m) 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1138; 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) 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 EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0149, dated 

June 13, 2014, for related information. This 

MCAI may be found in the AD docket on the 

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

searching for and locating Docket No. FAA– 

2015–4808. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(o) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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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 A330–57–3114, 

dated March 12, 2013. 

(ii) Airbus Service Bulletin A330–57–3115, 

dated April 4, 2013. 

(iii) Airbus Service Bulletin A330–57– 

3116, dated March 12, 2013. 

(iv) Airbus Service Bulletin A340–57– 

4123, dated March 12, 2013. 

(v) Airbus Service Bulletin A340–57–4124, 

Revision 01, dated August 22, 2013. 

(vi) Airbus Service Bulletin A340–57– 

4125, dated March 12, 2013. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@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 April 21, 

2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–10287 Filed 5–6–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0246; Directorate 

Identifier 2014–NM–187–AD; Amendment 

39–18511; AD 2016–09–13] 

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 737–300, 

–400, and –500 series airplanes. This 

AD was prompted by reports of fatigue 

cracking found at the left-side and rightside upper frames, at a certain area. This 

AD requires repetitive medium 

frequency eddy current (MFEC) 

inspections for cracking of the left-side 

and right-side upper frames, and repair 

(including open hole high frequency 

eddy current (HFEC) inspections for 

cracking of fastener holes) if necessary. 

This AD also provides an optional 

preventive modification, which 

terminates the repetitive inspections at 

the modified location. We are issuing 

this AD to detect and correct fatigue 

cracking of the upper frame, which can 

grow in size and result in a severed 

frame, leading to rapid decompression 

and consequent reduced structural 

integrity of the airplane. 

DATES: This AD is effective June 13, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 13, 2016. 

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–2015– 

0264. 

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–2015– 

0246; 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: 

Galib Abumeri, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office 

(ACO), 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; 

phone: 562–627–5324; fax: 562–627– 

5210; email: galib.abumeri@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 737–300, –400, and –500 series 

airplanes. The NPRM published in the 

Federal Register on February 24, 2015 

(80 FR 9667) (‘‘the NPRM’’). The NPRM 

was prompted by reports of fatigue 

cracking found at the left-side and rightside upper frame, at a certain area. The 

NPRM proposed to require repetitive 

MFEC inspections for cracking of the 

left-side and right-side upper frames, 

and repair (including open hole HFEC 

inspections for cracking of fastener 

holes) if necessary. The NPRM also 

provided an optional preventative 

modification that would terminate the 

repetitive inspections at the modified 

location. We are issuing this AD to 

detect and correct fatigue cracking of the 

upper frame, which can grow in size 

and result in a severed frame, leading to 

rapid decompression and consequent 

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 and the FAA’s 

response to each comment. 

Requests To Clarify Compliance Time 

Europe Airpost and Boeing requested 

that we revise the NPRM to clarify the 

‘‘Condition’’ column of table 1 of 

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

Alert Service Bulletin 737–53A1339, 

dated August 12, 2014, which specifies 

airplanes with certain flight cycles ‘‘on 

the original issue date of this service 

bulletin.’’ The commenters questioned 

whether the corresponding compliance 

time should be ‘‘on the effective date of 

the AD.’’ 

For the reasons suggested by both 

commenters, we agree to add paragraph 

(i)(3) to this AD to state that the 

corresponding reference point is on the 

effective date of this AD, and we have 

included reference to paragraph (i)(3) in 

all appropriate paragraphs in this AD. 

Request for Clarify Inspection 

Requirements 

Boeing requested that we revise 

paragraph (g) of the proposed AD to 

address the inspection requirements in 

areas of an existing repair to eliminate 

cracking approved by a Boeing 

Organization Designation Authorization 

(ODA) via FAA Form 8100–9. Boeing 

explained that this condition is 

addressed in note (c) of table 1 of 

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

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