21246 Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations 

which Airbus Modification 30975 has been 

embodied in production. 

(1) Airbus Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 airplanes. 

(2) Airbus Model A320–211, –212, –214, 

–231, –232, and –233 airplanes. 

(3) Airbus Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by fatigue testing 

that determined that fatigue damage could 

appear on clips, shear webs, and angles at 

certain rear fuselage sections and certain 

frames. This AD is intended to complete 

certain mandated programs intended to 

support the airplane reaching its limit of 

validity of the engineering data that support 

the established structural maintenance 

program. We are issuing this AD to prevent 

fatigue damage on the clips, shear webs, and 

angles, which could affect the structural 

integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replacement 

At the later of the times specified in 

paragraphs (g)(1) and (g)(2) of this AD: 

Replace the clips, shear webs, and angles at 

rear fuselage section 19, frame FR72 and 

FR74, and do all applicable related 

investigative actions before further flight, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1266, Revision 03, dated May 7, 2015. If 

any crack is found during any related 

investigative action 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). 

(1) Before exceeding 48,000 flight cycles or 

96,000 flight hours, whichever occurs first 

since the airplane’s first flight. 

(2) Within 30 days after the effective date 

of this AD. 

(h) Additional Replacement for Certain 

Airplanes 

For airplanes on which the replacement of 

clips, shear webs, and angles specified in 

Airbus Service Bulletin A320–53–1266 is 

done before accumulating 30,000 flight 

cycles or 60,000 flight hours, whichever 

occurred first since the airplane’s first flight: 

Within 30,000 flight cycles or 60,000 flight 

hours, whichever occurs first after that 

replacement, do the replacement specified in 

paragraph (g) of this AD. 

(i) Credit for Previous Actions 

Except as required by paragraph (h) of this 

AD: This paragraph provides credit for the 

replacement required by paragraph (g) of this 

AD, if those actions were performed before 

the effective date of this AD using the service 

information identified in paragraph (i)(1), 

(i)(2), or (i)(3) of this AD. This service 

information is not incorporated by reference 

in this AD. 

(1) Airbus Service Bulletin A320–53–1266, 

dated January 11, 2013. 

(2) Airbus Service Bulletin A320–53–1266, 

Revision 01, dated June 20, 2013. 

(3) Airbus Service Bulletin A320–53–1266, 

Revision 02, dated August 13, 2014. 

(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; 

telephone 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. 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. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0177, dated 

July 25, 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– 

2015–1277. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(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 A320–53–1266, 

Revision 03, dated May 7, 2015. 

(ii) Reserved. 

(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/ibrlocations.html. 

Issued in Renton, Washington, on March 

25, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–07375 Filed 4–8–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1426; Directorate 

Identifier 2013–NM–200–AD; Amendment 

39–18462; AD 2016–07–17] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 97–20–07 

for certain Airbus Model A300 B4–600, 

B4–600R, and F4–600R series airplanes, 

and Model A300 C4–605R Variant F 

airplanes (collectively called Model 

A300–600 series airplanes). AD 97–20– 

07 required repetitive inspections to 

detect fatigue cracking in the left and 

right wings in the area where the top 

skin attaches to the center spar, and 

repair or modification of this area if 

necessary. This new AD reduces the 

inspection compliance time and 

repetitive inspection intervals. This AD 

was prompted by a determination that 

the inspection compliance time and 

repetitive inspection interval must be 

reduced to allow timely detection of 

fatigue cracking in the left and right 

wings in the area where the top skin 

attaches to the center spar. We are 

issuing this AD to detect and correct 

this fatigue cracking, which could 

reduce the residual strength of the top 

skin of the wings, and consequently 


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Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations 21247 

affect the structural integrity of the 

airframe. 

DATES: This AD becomes effective May 

16, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 16, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of October 30, 1997 (62 FR 

50251, September 25, 1997). 

ADDRESSES: For service information 

identified in this final rule, 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–2015–1426. 

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– 

1426; 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 in the ADDRESSES

section. 

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 to supersede AD 97–20–07, 

Amendment 39–10145 (62 FR 50251, 

September 25, 1997) (‘‘AD 97–20–07’’). 

AD 97–20–07 applied to certain Airbus 

Model A300 B4–600, B4–600R, and F4– 

600R series airplanes, and Model A300 

C4–605R Variant F airplanes 

(collectively called Model A300–600 

series airplanes). The NPRM published 

in the Federal Register on June 5, 2015 

(80 FR 32058) (‘‘the NPRM’’). The 

NPRM was prompted by a 

determination that the inspection 

compliance time and repetitive 

inspection interval must be reduced to 

allow timely detection of fatigue 

cracking in the left and right wings in 

the area where the top skin attaches to 

the center spar. The NPRM proposed to 

continue to require repetitive 

inspections to detect fatigue cracking in 

the left and right wings in the area 

where the top skin attaches to the center 

spar, and repair or modification of this 

area if necessary. The NPRM also 

proposed to reduce the inspection 

compliance time and repetitive 

inspection intervals. We are issuing this 

AD to detect and correct this fatigue 

cracking, which could reduce the 

residual strength of the top skin of the 

wings, and consequently affect the 

structural integrity of the airframe. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2013–0221, dated September 

19, 2013 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for certain Airbus 

Model A300 B4–600, B4–600R, and F4– 

600R series airplanes, and Model A300 

C4–605R Variant F airplanes 

(collectively called Model A300–600 

series airplanes). The MCAI states: 

During fatigue tests conducted in the early 

1990’s, cracks were found on the top skin of 

the wing at the centre spar joint between ribs 

1 and 7. 

Consequently, Airbus developed 

production mod. 10089 and issued Service 

Bulletin (SB) A300–57–6041, involving 

installation of a reinforcing plate on the 

affected area. Despite this improvement, 

subsequent cases of cracks were reported by 

operators. 

This condition, if not detected and 

corrected, could adversely affect the 

structural integrity of the aeroplane. 

To address this potential unsafe condition, 

Airbus issued SB A300–57–6044 and DGAC 

[Direction Ge ́ne ́rale de l’Aviation Civile] 

France issued * * * [an airworthiness 

directive] (later revised twice) to require 

repetitive inspections of the affected area 

and, depending on findings, accomplishment 

of applicable corrective action(s). 

Since [the French] * * * [airworthiness 

directive] [which corresponds to FAA AD 

97–20–07, Amendment 39–10145 (62 FR 

50251, September 25, 1997)] was issued, a 

fleet survey and updated Fatigue and Damage 

Tolerance Analyses were performed in order 

to substantiate the second A300–600 

Extended Service Goal (ESG2) exercise. The 

results of these analyses have shown that the 

inspection thresholds and intervals must be 

reduced to allow timely detection of these 

cracks and accomplishment of an applicable 

corrective action. Prompted by these 

findings, Airbus issued SB A300–57–6044 

Revision 04 [dated August 19, 2011]. 

For the reasons described above, this 

[EASA] AD retains the requirements of [the 

French AD] * * * which is superseded, but 

requires the repetitive inspections to be 

accomplished at reduced thresholds and 

intervals and, depending on findings, 

corrective actions. 

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– 

1426. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Changes Made to This Final Rule 

Paragraph (m)(2) of the proposed AD 

inadvertently included the corrective 

action for the low frequency eddy 

current (LFEC) inspections for cracking 

specified in paragraphs (k) and (l) of the 

proposed AD; however, the corrective 

action in paragraph (m)(2) of this AD 

applies only to the new high frequency 

eddy current (HFEC) inspections 

required by this AD. We have revised 

paragraph (m)(2) of this AD to specify 

the corrective action for the HFEC 

inspections for cracking specified in 

paragraphs (i), (j), and (m)(1) of this AD. 

We have added new paragraph (m)(4) of 

this AD to specify the corrective actions 

for the LFEC inspections specified in 

paragraphs (k) and (l) of this AD. 

Conclusion 

We reviewed the available data 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 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 Service Bulletin 

A300–57–6044, Revision 04, dated 

August 19, 2011, including Appendix 

01, Revision 04, dated August 19, 2011. 

The service information describes 

procedures for inspections to detect 

fatigue cracking in the left and right 

wings in the area where the top skin 

attaches to the center spar, and repair or 

modification of this area. This service 

information is reasonably available 


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21248 Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations 

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 47 

airplanes of U.S. registry. 

The actions required by AD 97–20–07, 

and retained in this AD take about 3 

work-hours per product, at an average 

labor rate of $85 per work-hour. Based 

on these figures, the estimated cost of 

the actions that were required by AD 

97–20–07 is $255 per product. 

We also estimate that it will take 

about 5 work-hours per product to 

comply with the new 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 $19,975, 

or $425 per product 

We have received no definitive data 

that would enable us to provide cost 

estimates for the 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 

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 

removing Airworthiness Directive (AD) 

97–20–07, Amendment 39–10145 (62 

FR 50251, September 25, 1997), and 

adding the following new AD: 

2016–07–17 Airbus: Amendment 39–18462. 

Docket No. FAA–2015–1426; Directorate 

Identifier 2013–NM–200–AD. 

(a) Effective Date 

This AD becomes effective May 16, 2016. 

(b) Affected ADs 

This AD replaces AD 97–20–07, 

Amendment 39–10145 (62 FR 50251, 

September 25, 1997) (‘‘AD 97–20–07’’). 

(c) Applicability 

This AD applies to the Airbus airplanes 

identified in paragraphs (c)(1) through (c)(4) 

of this AD, certificated in any category, all 

manufacturer serial numbers except those on 

which Airbus Modification 10160 has been 

done in production. 

(1) Airbus Model A300 B4–601, B4–603, 

B4–620, and B4–622 airplanes. 

(2) Airbus Model A300 B4–605R and B4– 

622R airplanes. 

(3) Airbus Model A300 F4–605R and F4– 

622R airplanes. 

(4) Airbus Model A300 C4–605R Variant F 

airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by a determination 

that the inspection compliance time and 

repetitive inspection interval must be 

reduced to allow timely detection of fatigue 

cracking in the left and right wings in the 

area where the top skin attaches to the center 

spar. We are issuing this AD to detect and 

correct this fatigue cracking, which could 

reduce the residual strength of the top skin 

of the wings, and consequently affect the 

structural integrity of the airframe. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Repetitive Inspections and 

Corrective Actions, With Revised Service 

Information 

This paragraph restates the requirements of 

paragraph (a) of AD 97–20–07, with revised 

service information. For airplanes on which 

Airbus Modification 10089 has not been 

installed: Prior to the accumulation of 18,000 

total landings, or within 1,500 landings after 

October 30, 1997 (the effective date of AD 

97–20–07), whichever occurs later, conduct 

either a detailed visual inspection or a high 

frequency eddy current (HFEC) inspection to 

detect fatigue cracking in the left and right 

wings in the area where the top skin attaches 

to the center spar between ribs 1 and 7, in 

accordance with Airbus Service Bulletin 

A300–57–6044, Revision 2, dated September 

6, 1995, including Appendix 1, Revision 1, 

dated November 25, 1994; or Airbus Service 

Bulletin A300–57–6044, Revision 04, dated 

August 19, 2011, including Appendix 01, 

Revision 04, dated August 19, 2011. As of the 

effective date of this AD, use only Airbus 

Service Bulletin A300–57–6044, Revision 04, 

dated August 19, 2011, including Appendix 

01, Revision 04, dated August 19, 2011. 

Accomplishment of the inspection required 

by paragraph (i) of this AD terminates the 

inspection requirements of this paragraph. 

(1) If no cracking is detected, conduct 

repetitive inspections thereafter at the 

following intervals: 

(i) If the immediately preceding inspection 

was conducted using detailed visual 

inspection techniques, conduct the next 

inspection within 5,000 landings. 

(ii) If the immediately preceding inspection 

was conducted using HFEC techniques, 

conduct the next inspection within 9,500 

landings. 

(2) If any cracking is detected or suspected 

during any detailed visual inspection 

required by the introductory text of 

paragraph (g), paragraph (g)(1), or paragraph 

(g)(3)(i) of this AD, prior to further flight, 

confirm this finding and the length of this 

cracking by conducting an HFEC inspection, 

in accordance with Airbus Service Bulletin 

A300–57–6044, Revision 2, dated September 

6, 1995, including Appendix 1, Revision 1, 

dated November 25, 1994; or Airbus Service 

Bulletin A300–57–6044, Revision 04, dated 

August 19, 2011, including Appendix 01, 

Revision 04, dated August 19, 2011. As of the 

effective date of this AD, use only Airbus 

Service Bulletin A300–57–6044, Revision 04, 

dated August 19, 2011, including Appendix 

01, Revision 04, dated August 19, 2011. If no 

cracking is confirmed during the HFEC 

inspection, accomplish the repetitive 

inspection required by paragraph (g)(1)(ii) of 

this AD at the time specified in that 

paragraph. 


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(3) If any cracking is detected or confirmed 

during any HFEC inspection required by the 

introductory text of paragraph (g), paragraph 

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

(i) If the cracking is 75 millimeters (mm) 

or less per rib bay, prior to further flight, 

repair in accordance with Airbus Service 

Bulletin A300–57–6044, Revision 2, dated 

September 6, 1995, including Appendix 1, 

Revision 1, dated November 25, 1994; or 

Airbus Service Bulletin A300–57–6044, 

Revision 04, dated August 19, 2011, 

including Appendix 01, Revision 04, dated 

August 19, 2011. As of the effective date of 

this AD, use only Airbus Service Bulletin 

A300–57–6044, Revision 04, dated August 

19, 2011, including Appendix 01, Revision 

04, dated August 19, 2011. Thereafter, 

conduct repetitive detailed visual inspections 

of the repaired area at intervals not to exceed 

50 landings, in accordance with Airbus 

Service Bulletin A300–57–6044, Revision 2, 

dated September 6, 1995, including 

Appendix 1, Revision 1, dated November 25, 

1994; or Airbus Service Bulletin A300–57– 

6044, Revision 04, dated August 19, 2011, 

including Appendix 01, Revision 04, dated 

August 19, 2011. As of the effective date of 

this AD, use only Airbus Service Bulletin 

A300–57–6044, Revision 04, dated August 

19, 2011, including Appendix 01, Revision 

04, dated August 19, 2011. 

(ii) If the cracking exceeds 75 mm per rib 

bay, prior to further flight, install Airbus 

Modification 10089, in accordance with 

Airbus Service Bulletin A300–57–6044, 

Revision 2, dated September 6, 1995, 

including Appendix 1, Revision 1, dated 

November 25, 1994; or Airbus Service 

Bulletin A300–57–6044, Revision 04, dated 

August 19, 2011, including Appendix 01, 

Revision 04, dated August 19, 2011. As of the 

effective date of this AD, use only Airbus 

Service Bulletin A300–57–6044, Revision 04, 

dated August 19, 2011, including Appendix 

01, Revision 04, dated August 19, 2011. 

Thereafter, conduct a low frequency eddy 

current (LFEC) inspection in accordance with 

the requirements of paragraph (h) of this AD. 

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

Service Bulletin A300–57–6044, Revision 2, 

dated September 6, 1995, including 

Appendix 1, Revision 1, dated November 25, 

1994, references Airbus Service Bulletin 

A300–57–6041, Revision 4, dated November 

16, 1995, as an additional source of guidance 

for installing Airbus Modification 10089. 

(h) Retained Repetitive Inspections and 

Corrective Actions for Certain Airplanes, 

With Revised Service Information and 

Repair Instructions 

This paragraph restates the requirements of 

paragraph (b) of AD 97–20–07, with revised 

service information and repair instructions. 

For airplanes on which Airbus Modification 

10089 has been installed: Prior to the 

accumulation of 22,000 total landings after 

this modification has been installed, or 

within 1,500 landings after October 30, 1997 

(the effective date of AD 97–20–07), 

whichever occurs later, conduct a LFEC 

inspection to detect fatigue cracking in the 

inboard and rear edges of the top skin 

reinforcing plates, in accordance with Airbus 

Service Bulletin A300–57–6044, Revision 2, 

dated September 6, 1995, including 

Appendix 1, Revision 1, dated November 25, 

1994; or Airbus Service Bulletin A300–57– 

6044, Revision 04, dated August 19, 2011, 

including Appendix 01, Revision 04, dated 

August 19, 2011. As of the effective date of 

this AD, use only Airbus Service Bulletin 

A300–57–6044, Revision 04, dated August 

19, 2011, including Appendix 01, Revision 

04, dated August 19, 2011. Accomplishment 

of the inspection required by paragraph (k) of 

this AD terminates the inspection 

requirements of this paragraph. 

(1) If no cracking is detected, repeat this 

inspection thereafter at intervals not to 

exceed 11,000 landings. 

(2) If any cracking is detected, prior to 

further flight, repair in accordance with a 

method approved by the Manager, 

Standardization Branch, ANM–113, 

Transport Airplane Directorate, FAA. As of 

the effective date of this AD, 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). 

Thereafter, repeat this inspection at intervals 

not to exceed 11,000 landings. 

(i) New Requirement of This AD: Initial 

Inspections 

For airplanes on which Airbus 

Modification 10089 has not been installed: At 

the applicable time specified in paragraphs 

(i)(1) and (i)(2) of this AD, do either a 

detailed visual inspection or an HFEC 

inspection to detect fatigue cracking in the 

left and right wings in the area where the top 

skin attaches to the center spar between ribs 

1 and 7, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–6044, Revision 04, 

dated August 19, 2011, including Appendix 

01, Revision 04, dated August 19, 2011. 

Accomplishment of the inspection required 

by this paragraph terminates the inspection 

requirements of paragraph (g) of this AD. 

(1) For airplanes whose flight time average 

is equal to or more than 1.5 hours, at the later 

of the times specified in paragraphs (i)(1)(i) 

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

(i) Before the accumulation of 14,000 total 

flight cycles or 30,300 total flight hours, 

whichever occurs first. 

(ii) Within 1,500 flight cycles or 3,200 

flight hours after the effective date of this AD, 

whichever occurs first. 

(2) For airplanes whose flight time average 

is less than 1.5 hours, at the later of the times 

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

of this AD. 

(i) Before the accumulation of 15,100 total 

flight cycles or 22,700 total flight hours, 

whichever occurs first. 

(ii) Within 1,600 flight cycles or 2,500 

flight hours after the effective date of this AD, 

whichever occurs first. 

(j) New Requirement of This AD: Repetitive 

Inspections 

Repeat the inspections specified in 

paragraph (i) of this AD thereafter at the 

applicable interval specified in paragraphs 

(j)(1) and (j)(2) of this AD. 

(1) For airplanes whose flight time average 

is equal to or more than 1.5 hours, at the 

applicable interval specified in paragraphs 

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

(i) For a detailed visual inspection, at 

intervals not to exceed 3,900 flight cycles or 

8,400 flight hours, whichever occurs first. 

(ii) For an HFEC inspection, at intervals 

not to exceed 7,400 flight cycles or 16,000 

flight hours, whichever occurs first. 

(2) For airplanes whose flight time average 

is less than 1.5 hours, at the applicable 

interval specified in paragraphs (j)(2)(i) and 

(j)(2)(ii) of this AD. 

(i) For a detailed visual inspection, at 

intervals not to exceed 4,200 flight cycles or 

6,300 flight hours, whichever occurs first. 

(ii) For an HFEC inspection, at intervals 

not to exceed 8,000 flight cycles or 11,900 

flight hours, whichever occurs first. 

(k) New Requirement of This AD: Initial 

Inspection for Certain Airplanes 

For airplanes on which Airbus 

Modification 10089 has been installed: At the 

applicable time specified in paragraphs (k)(1) 

and (k)(2) of this AD, do an LFEC inspection 

to detect fatigue cracking in the inboard and 

rear edges of the top skin reinforcing plates, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

57–6044, Revision 04, dated August 19, 2011, 

including Appendix 01, Revision 04, dated 

August 19, 2011. Accomplishment of the 

inspection required by this paragraph 

terminates the inspection requirements of 

paragraph (h) of this AD. 

(1) For airplanes whose flight time average 

is equal to or more than 1.5 hours, at the later 

of the times specified in paragraphs (k)(1)(i) 

and (k)(1)(ii) of this AD. 

(i) Before the accumulation of 17,000 total 

flight cycles or 37,100 total flight hours, 

whichever occurs first. 

(ii) Within 1,500 flight cycles or 3,200 

flight hours after the effective date of this AD, 

whichever occurs first. 

(2) For airplanes whose flight time average 

is less than 1.5 hours, at the later of the times 

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

of this AD. 

(i) Before the accumulation of 18,500 total 

flight cycles or 27,800 total flight hours, 

whichever occurs first. 

(ii) Within 1,600 flight cycles or 2,500 

flight hours after the effective date of this AD, 

whichever occurs first. 

(l) New Requirement of This AD: Repetitive 

Inspections for Certain Airplanes 

Repeat the inspection specified in 

paragraph (k) of this AD thereafter at the 

applicable interval specified in paragraphs 

(l)(1) and (l)(2) of this AD. 

(1) For airplanes whose flight time average 

is equal to or more than 1.5 hours, at 

intervals not to exceed 8,500 flight cycles or 

18,500 flight hours, whichever occurs first. 

(2) For airplanes whose flight time average 

is less than 1.5 hours, at intervals not to 

exceed 9,200 flight cycles or 13,700 flight 

hours, whichever occurs first. 

(m) New Requirement of This AD: Corrective 

Actions 

(1) If any cracking is detected or suspected 

during any detailed inspection required by 

paragraph (i) or (j) of this AD: Before further 

flight, confirm this finding and the length of 


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21250 Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations 

this cracking by conducting an HFEC 

inspection, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–6044, Revision 04, 

dated August 19, 2011, including Appendix 

01, Revision 04, dated August 19, 2011, 

except as specified in paragraph (o) of this 

AD. If no cracking is confirmed during the 

HFEC inspection, accomplish the applicable 

repetitive inspections required by paragraphs 

(j) and (l) of this AD at the applicable time 

specified in those paragraphs. 

(2) If any cracking is found during any 

HFEC inspection required by paragraph (i), 

(j), or (m)(1) of this AD: Before further flight, 

do the applicable actions specified in 

paragraphs (m)(2)(i) and (m)(2)(ii) of this AD. 

(i) If the cracking is 75 mm or less per each 

rib bay: Before further flight, repair the 

cracking, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–6044, Revision 04, 

dated August 19, 2011, including Appendix 

01, Revision 04, dated August 19, 2011, 

except as specified in paragraph (o) of this 

AD. Do repetitive detailed inspections of the 

repaired area thereafter at intervals not to 

exceed 50 flight cycles or 110 flight hours, 

whichever occurs first, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A300–57–6044, Revision 04, 

dated August 19, 2011, including Appendix 

01, Revision 04, dated August 19, 2011. 

Within 250 flight cycles or 550 flight hours, 

whichever occurs first after doing the 

temporary repair, do a permanent repair of 

the repaired area, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–6044, Revision 04, 

dated August 19, 2011, including Appendix 

01, Revision 04, dated August 19, 2011. 

(ii) If the cracking exceeds 75 mm per any 

rib bay: Before further flight, install Airbus 

Modification 10089, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–6044, Revision 04, 

dated August 19, 2011, including Appendix 

01, Revision 04, dated August 19, 2011. Do 

an LFEC inspection thereafter at the intervals 

specified in paragraph (l) of this AD. 

(3) If any cracking is found during any 

inspection required by this AD at fastener 

hole 1A, 1, or 2: Before further flight, repair 

the cracking, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–6044, Revision 04, 

dated August 19, 2011, including Appendix 

01, Revision 04, dated August 19, 2011. 

(4) If any cracking is found during any 

LFEC inspection required by paragraph (k) or 

(l) of this AD: Before further flight, repair 

using a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or EASA; or 

Airbus’s EASA DOA. 

(n) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (i) through (l) of this 

AD, if those actions were performed before 

the effective date of this AD using Airbus 

Service Bulletin A300–57–6044, Revision 03, 

dated April 7, 1999, including Appendix 01, 

Revision 03, dated April 7, 1999, which is 

not incorporated by reference in this AD. 

(o) Exception to Service Information 

Specification 

Although Airbus Service Bulletin A300– 

57–6044, Revision 04, dated August 19, 2011, 

including Appendix 01, Revision 04, dated 

August 19, 2011, specifies to submit 

information to Airbus, this AD does not 

require that submission. 

(p) 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) Contacting the Manufacturer: As of the 

effective date of this AD, 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 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(q) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0221, dated 

September 19, 2013, 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–2015–1426. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (r)(5) and (r)(6) of this AD. 

(r) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on May 16, 2016 

(i) Airbus Service Bulletin A300–57–6044, 

Revision 04, dated August 19, 2011, 

including Appendix 01, Revision 04, dated 

August 19, 2011. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on October 30, 1997 (62 FR 

50251, September 25, 1997). 

(i) Airbus Service Bulletin A300–57–6044, 

Revision 2, dated September 6, 1995, 

including Appendix 1, Revision 1, dated 

November 25, 1994. Pages 1 through 8 of this 

document are identified as Revision 2, dated 

September 6, 1995; pages 9 and 10 are 

identified as original, dated March 1, 1993. 

Page 1 of Appendix 1 is identified as 

Revision 1, dated November 25, 1994; and 

pages 2 through 6 are identified as original, 

dated March 1, 1993. 

(ii) Reserved. 

(5) 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.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(6) 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. 

(7) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

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

Issued in Renton, Washington, on March 

24, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–07574 Filed 4–8–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–5457; Directorate 

Identifier 2016–CE–008–AD; Amendment 

39–18469; AD 2016–07–24] 

RIN 2120–AA64 

Airworthiness Directives; Textron 

Aviation, Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Textron Aviation, Inc. Models 310 

through 310R, E310H, E310J, T310P 

through T310R, 310J–1, 320 through 

320F, 320–1, 335, 340, 340A, 401 

through 401B, 402 through 402C, 411, 

411A, 414, 414A, and 421 through 421C 


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