Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations 21255 

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): 

2016–07–28 The Boeing Company: 

Amendment 39–18473; Docket No. 

FAA–2016–5458; Directorate Identifier 

2016–NM–027–AD. 

(a) Effective Date 

This AD is effective April 26, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model DC–9–81 (MD–81), DC–9– 

82 (MD–82), DC–9–83 (MD–83), and DC–9– 

87 (MD–87) airplanes, and Model MD–88 

airplanes, certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by reports of 

cracking at certain stringers, associated end 

fittings, and skins in the center wing fuel 

tank where the stringers meet the end 

fittings. We are issuing this AD to detect and 

correct cracking in the center wing lower 

skin. Such cracking could cause structural 

failure of the wings. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

Except as required by paragraph (h)(1) and 

(h)(2) of this AD, at the applicable time 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin MD80–57A244, 

dated March 3, 2016: Do an eddy current 

high frequency (ETHF) inspection for any 

cracking in the left and right side center wing 

lower skin, and do all applicable corrective 

actions; except as required by paragraph 

(h)(3) of this AD. Do all applicable corrective 

actions before further flight. Repeat the 

inspection thereafter at the intervals 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin MD80–57A244, 

dated March 3, 2016. 

(h) Exception to the Service Information 

(1) Where Boeing Alert Service Bulletin 

MD80–57A244, dated March 3, 2016, 

specifies a compliance time ‘‘after the 

original issue date of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(2) The Condition column of paragraph 

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

Bulletin MD80–57A244, dated March 3, 

2016, refers to total flight cycles ‘‘as of the 

original issue date of this service bulletin.’’ 

This AD, however, applies to the airplanes 

with the specified total flight cycles as of the 

effective date of this AD. 

(3) If any crack is found during any 

inspection required by this AD, and Boeing 

Alert Service Bulletin MD80–57A244, dated 

March 3, 2016, specifies to contact Boeing for 

appropriate action, and specifies that action 

as ‘‘RC’’ (Required for Compliance): Before 

further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (i) of this AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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 (j) of this AD. Information may be 

emailed to: 9-ANM-LAACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO, to make those findings. To be 

approved, the repair method, modification 

deviation, or alteration deviation must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) Except as required by paragraph (h)(3) 

of this AD: For service information that 

contains steps that are labeled as Required 

for Compliance (RC), the provisions of 

paragraphs (i)(4)(i) and (i)(4)(ii) of this AD 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled 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 RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(j) Related Information 

For more information about this AD, 

contact Haytham Alaidy, Aerospace 

Engineer, Airframe Branch, ANM–120L, 

FAA, Los Angeles Aircraft Certification 

Office (ACO), 3960 Paramount Boulevard, 

Lakewood, CA 90712–4137; phone: 562–627– 

5224; fax: 562–627–5210; email: 

haytham.alaidy@faa.gov. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin MD80– 

57A244, dated March 3, 2016. 

(ii) Reserved. 

(3) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, 3855 Lakewood 

Boulevard, MC D800–0019, Long Beach, CA 

90846–0001; telephone 206–544–5000, 

extension 2; fax 206–766–5683; Internet 

https://www.myboeingfleet.com. 

(4) 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. 

(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 

30, 2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–07842 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–2015–4817; Directorate 

Identifier 2014–NM–115–AD; Amendment 

39–18465; AD 2016–07–20] 

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) 95–18–08 

for all Airbus Model A300–600 series 

airplanes. AD 95–18–08 required 

repetitive inspections to detect cracks in 

the bottom skin of the wing in the area 

of the cut-out for the pylon rear 

attachment fitting, and repair if 

necessary. This new AD, for certain 


jstallworth on DSK7TPTVN1PROD with RULES
21256 Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations 

airplanes, reduces the compliance times 

for the inspections. This AD was 

prompted by a report that updated 

fatigue and damage tolerance analyses 

and a fleet survey found that certain 

inspection thresholds and intervals 

must be reduced to allow more timely 

findings of cracking. We are issuing this 

AD to detect and correct fatigue-related 

cracking in the bottom skin of the wing 

in the area of the cut-out for the pylon 

rear attachment fitting, which could 

result in reduced structural integrity of 

the wing. 

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 16, 1995 (60 FR 

47677, September 14, 1995). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2015-4817; or in 

person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

For service information identified in 

this 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– 

4817. 

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 95–18–08, 

Amendment 39–9355 (60 FR 47677, 

September 14, 1995) (‘‘AD 95–18–08’’). 

AD 95–18–08 applied to all Airbus 

Model A300–600 series airplanes 

(which includes Airbus Model A300 

C4–605R Variant F airplanes), Model 

A300 B4–622 airplanes, and Model 

A300 F4–622R airplanes that were 

added to the U.S. Type Certificate Data 

Sheet since issuance of AD 95–18–08. 

The NPRM published in the Federal 

Register on November 19, 2015 (80 FR 

72395) (‘‘the NPRM’’ or ‘‘the proposed 

AD’’). The NPRM was prompted by a 

report that updated fatigue and damage 

tolerance analyses and a fleet survey 

found that certain inspection thresholds 

and intervals must be reduced to allow 

more timely findings of cracking. The 

NPRM proposed to continue to require 

repetitive inspections to detect cracks in 

the bottom skin of the wing in the area 

of the cut-out for the pylon rear 

attachment fitting, and repair if 

necessary. The NPRM also proposed, for 

certain airplanes, reduce the compliance 

times for the inspections. We are issuing 

this AD to detect and correct such 

fatigue-related cracking in the bottom 

skin of the wing in the area of the cutout for the pylon rear attachment fitting, 

which could result in reduced structural 

integrity of the wing. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0119, dated May 13, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition on all 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: 

Full-scale fatigue tests carried out on the 

A300–600 test specimen by Airbus revealed 

crack initiation in the bottom skin adjacent 

to the aft pylon attachment fitting. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

To address this unsafe condition, DGAC 

[Direction Ge ́ne ́rale de l’Aviation Civile] 

France issued AD 94–069–158(B) (http://

ad.easa.europa.eu/blob/1994069158tb_

superseded.pdf/AD_F-1994-069-158_2) 

[which corresponds to FAA AD 95–18–08, 

Amendment 39–9355 (60 FR 47677, 

September 14, 1995)] to require repetitive 

detailed visual inspections (DVI) of the wing 

bottom skin in the area of the cut-out for the 

pylon rear attachment fitting on Left Hand 

(LH) and Right Hand (RH) wings [to detect 

cracks, and repair if necessary]. 

Since that [DGAC] AD was issued, a fleet 

survey and updated Fatigue and Damage 

Tolerance analyses have been performed in 

order to substantiate the second A300–600 

Extended Service Goal (ESG2) exercise. As a 

result, it was revealed that the inspection 

threshold and interval must be reduced to 

allow timely detection of cracks and the 

accomplishment of an applicable corrective 

action. Prompted by these findings, Airbus 

issued Revision 07 of Service Bulletin (SB) 

A300–57–6028. 

For the reasons described above, this 

[EASA] AD retains the requirements of DGAC 

France AD 94–069–158(B), which is 

superseded, but reduces the inspection 

thresholds and intervals [e.g., compliance 

times]. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2015-4817- 

0002. 

Comment 

The following presents the comment 

received on the NPRM and the FAA’s 

response to the comment. 

Statement on Fleet Activity 

FedEx Express (FedEx) stated that the 

NPRM will affect 71 Model A300 

airplanes in its fleet. FedEx stated that 

42 of its Model A300–F4 airplanes have 

not reached the inspection threshold, 

and it is currently accomplishing 

repetitive actions on 15 of its 29 Model 

A300–B4 airplanes. FedEx stated that it 

will adjust its inspection actions to 

comply with the actions specified in the 

NPRM. 

We acknowledge FedEx’s comment. 

No change to this AD is necessary. 

Conclusion 

We reviewed the available data, 

including 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 

We reviewed Airbus Service Bulletin 

A300–57–6028, Revision 07, dated June 

6, 2011. The service information 

describes procedures for inspections to 

detect cracks in the bottom skin of the 

wing in the area of the cut-out for the 

pylon rear attachment fitting, and 

repair. 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. 


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Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations 21257 

Costs of Compliance 

We estimate that this AD affects 124 

airplanes of U.S. registry. 

The actions required by AD 95–18–08, 

and retained in this AD take about 6 

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 

95–18–08 is $510 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 15 work-hours and require parts 

costing $10,000, for a cost of $11,275 

per product. We have no way of 

determining the number of aircraft that 

might need these actions. 

The new requirements of this AD add 

no additional economic burden. 

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-2015-4817; 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. 

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) 

95–18–08, Amendment 39–9355 (60 FR 

47677, September 14, 1995), and adding 

the following new AD: 

2016–07–20 Airbus: Amendment 39–18465. 

Docket No. FAA–2015–4817; Directorate 

Identifier 2014–NM–115–AD. 

(a) Effective Date 

This AD becomes effective May 16, 2016. 

(b) Affected ADs 

This AD replaces AD 95–18–08, 

Amendment 39–9355 (60 FR 47677, 

September 14, 1995) (‘‘AD 95–18–08’’). 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) through (c)(4) of this AD, 

certificated in any category, all manufacturer 

serial numbers. 

(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 report that 

updated fatigue and damage tolerance 

analyses and a fleet survey found that certain 

inspection thresholds and intervals must be 

reduced to allow more timely findings of 

cracking. We are issuing this AD to detect 

and correct such fatigue-related cracking in 

the bottom skin of the wing in the area of the 

cut-out for the pylon rear attachment fitting, 

which could result in reduced structural 

integrity of the wing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspection and Corrective 

Action with Additional Repair Information 

This paragraph restates the requirements of 

paragraph (a) of AD 95–18–08, with 

additional repair contact information. Prior 

to the accumulation of 24,000 total flight 

cycles since date of manufacture of the 

airplane, or within 750 flight cycles after 

October 16, 1995 (the effective date of AD 

95–18–08), whichever occurs later, perform a 

detailed visual inspection to detect cracks in 

the bottom skin of the wing in the area of the 

cut-out for the pylon rear attachment fitting, 

in accordance with Airbus Service Bulletin 

A300–57–6028, Revision 3, dated September 

13, 1994. Repeat the inspection thereafter at 

intervals not to exceed 9,000 flight cycles. If 

any crack is detected, prior to further flight, 

repair the wing bottom skin in accordance 

with a method approved by the Manager, 

Standardization Branch, ANM–113, FAA, 

Transport Airplane Directorate, or 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). Accomplishing any 

inspection required by paragraph (h) of this 

AD terminates the inspections required by 

this paragraph. 

(h) New Requirement of This AD: Revised 

Inspection Thresholds and Intervals 

Within the applicable compliance times 

required in paragraphs (h)(1) and (h)(2) of 

this AD, do a detailed visual inspection of 

the wing bottom skin in the area of the cutout for the pylon rear attachment fitting on 

left-hand and right-hand wings, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

57–6028, Revision 07, dated June 6, 2011. 

Repeat the inspections thereafter at the 

applicable intervals required in paragraphs 

(h)(3) and (h)(4) of this AD. Accomplishing 

any inspection required by this paragraph 

terminates the inspections required by 

paragraph (g) of this AD. 

(1) For ‘‘normal range operations’’ 

airplanes having an average flight time of 1.5 

flight hours or more: Do the inspection at the 

applicable time required in paragraphs 

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

(i) For Model A300 F4–605R and F4–622R 

airplanes: Do the inspection at the later of the 

times specified in paragraphs (h)(1)(i)(A) and 

(h)(1)(i)(B) of this AD. 


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21258 Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations 

(A) Within 24,000 flight cycles or 51,800 

flight hours after first flight of the airplane, 

whichever occurs first. 

(B) Within 2,000 flight cycles or 4,300 

flight hours after the effective date of this AD, 

whichever occurs first. 

(ii) For Model A300 B4–600, B4–600R, and 

Model A300 C4–605R Variant F airplanes: Do 

the inspection at the later of the times 

specified in paragraphs (h)(1)(ii)(A) and 

(h)(1)(ii)(B) of this AD. 

(A) Within 19,100 flight cycles or 41,200 

flight hours after first flight of the airplane, 

whichever occurs first. 

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

flight hours after the effective date of this AD, 

whichever occurs first. 

(2) For ‘‘short range operations’’ airplanes 

having an average flight time of less than 1.5 

flight hours: Do the inspection at the 

applicable time required in paragraphs 

(h)(2)(i) and (h)(2)(ii) of this AD. 

(i) For Model A300 F4–605R and F4–622R 

airplanes: Do the inspection at the later of the 

times specified in paragraphs (h)(2)(i)(A) and 

(h)(2)(i)(B) of this AD. 

(A) Within 25,900 flight cycles or 38,800 

flight hours after first flight of the airplane, 

whichever occurs first. 

(B) Within 2,100 flight cycles or 3,200 

flight hours after the effective date of this AD, 

whichever occurs first. 

(ii) For Model A300 B4–600, B4–600R, and 

Model A300 C4–605R Variant F airplanes: Do 

the inspection at the later of the times 

specified in paragraphs (h)(2)(ii)(A) and 

(h)(2)(ii)(B) of this AD. 

(A) Within 20,600 flight cycles or 30,900 

flight hours after first flight of the airplane, 

whichever occurs first. 

(B) Within 1,600 flight cycles or 2,400 

flight hours after the effective date of this AD, 

whichever occurs first. 

(3) For ‘‘normal range operations’’ 

airplanes having an average flight time of 1.5 

flight hours or more: Repeat the inspection at 

the applicable time required in paragraphs 

(h)(3)(i) and (h)(3)(ii) of this AD. 

(i) For Model A300 F4–605R and F4–622R 

airplanes: Repeat the inspection thereafter at 

intervals not to exceed 9,000 flight cycles or 

19,400 flight hours, whichever occurs first. 

(ii) For Model A300 B4–600, B4–600R, and 

Model A300 C4–605R Variant F airplanes: 

Repeat the inspection thereafter at intervals 

not to exceed 7,100 flight cycles or 15,300 

flight hours, whichever occurs first. 

(4) For ‘‘short range operations’’ airplanes 

having an average flight time of less than 1.5 

flight hours: Repeat the inspection at the 

applicable time required in paragraphs 

(h)(4)(i) and (h)(4)(ii) of this AD. 

(i) For Model A300 F4–605R and F4–622R 

airplanes: Repeat the inspection thereafter at 

intervals not to exceed 9,700 flight cycles or 

14,500 flight hours, whichever occurs first. 

(ii) For Model A300 B4–600, B4–600R, and 

Model A300 C4–605R Variant F airplanes: 

Repeat the inspection thereafter at intervals 

not to exceed 7,600 flight cycles or 11,500 

flight hours, whichever occurs first. 

(i) Definition of Average Flight Time for 

Paragraph (h) of This AD 

For the purpose of paragraph (h) of this 

AD, the Average Flight Time must be 

established as follows: 

(1) For the initial inspection, the average 

flight time is the total accumulated flight 

hours, counted from take-off to touch-down, 

divided by the total accumulated flight cycles 

at the effective date of this AD. 

(2) For the first repeated inspection 

interval, the average flight time is the total 

accumulated flight hours divided by the total 

accumulated flight cycles at the time of the 

inspection threshold. 

(3) For all inspection intervals onwards, 

the average flight time is the flight hours 

divided by the flight cycles accumulated 

between the last two inspections. 

(j) New Requirement of This AD: Corrective 

Action for Any Cracking Found 

If any crack is found during any inspection 

required by paragraph (h) 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. Accomplishing a repair does not 

constitute terminating action for the 

repetitive inspections required by paragraph 

(h) of this AD. 

(k) Credit for Previous Actions 

This paragraph provides credit for 

inspections required by paragraph (h) of this 

AD, if those actions were performed before 

the effective date of this AD using any of the 

service information identified in paragraphs 

(k)(1), (k)(2), and (k)(3) of this AD, which are 

not incorporated by reference in this AD. 

(1) Airbus Service Bulletin A300–57–6028, 

Revision 04, dated October 25, 1999. 

(2) Airbus Service Bulletin A300–57–6028, 

Revision 05, dated January 11, 2002. 

(3) Airbus Service Bulletin A300–57–6028, 

Revision 06, dated May 17, 2006. 

(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. 

(i) 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. 

(ii) AMOCs approved previously for AD 

95–18–08, are approved as AMOCs for the 

corresponding provisions of paragraph (g) of 

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. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2014–0119, dated May 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–2015–4817. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (n)(5) and (n)(6) 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. 

(3) The following service information was 

approved for IBR on May 16, 2016. 

(i) Airbus Service Bulletin A300–57–6028, 

Revision 07, dated June 6, 2011. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on October 16, 1995 (60 FR 

47677, September 14, 1995). 

(i) Airbus Service Bulletin A300–57–6028, 

Revision 3, dated September 13, 1994. Pages 

1 through 6 of this service bulletin indicate 

Revision 3 and are dated September 13, 1994; 

pages 7 through 9 indicate Revision 2 and are 

dated February 22, 1994. 

(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.airworth-eas@

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. 2016–07570 Filed 4–8–16; 8:45 am] 

BILLING CODE 4910–13–P 


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