32058 Federal Register / Vol. 80, No. 108 / Friday, June 5, 2015 / Proposed Rules 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1426; Directorate 

Identifier 2013–NM–200–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

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 requires 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. Since we issued AD 97–20– 

07, we have determined that the 

inspection compliance time and 

repetitive inspection interval must be 

reduced to allow timely detection of 

cracking in the left and right wings in 

the area where the top skin attaches to 

the center spar. This proposed AD 

would reduce the inspection 

compliance time and repetitive 

inspection intervals. We are proposing 

this AD to detect and correct this 

cracking, which could reduce the 

residual strength of the top skin of the 

wings, and consequently affect the 

structural integrity of the airframe. 

DATES: We must receive comments on 

this proposed AD by July 20, 2015. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC, between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus SAS, 

Airworthiness Office—EAW, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

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

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

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 proposed 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. Comments will 

be available in the AD docket shortly 

after receipt. 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–1426; Directorate Identifier 

2013–NM–200–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On September 17, 1997, we issued AD 

97–20–07, Amendment 39–10145 (62 

FR 50251, September 25, 1997). AD 97– 

20–07 requires actions intended to 

address an unsafe condition on the 

products listed above. Since we issued 

AD 97–20–07, we have determined that 

the inspection compliance time and 

repetitive inspection interval must be 

reduced to allow timely detection of 

cracking in the left and right wings in 

the area where the top skin attaches to 

the center spar. 

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 AD 95–086–180 (later revised 

twice) to require repetitive inspections of the 

affected area and, depending on findings, 

accomplishment of applicable corrective 

action(s). 

Since [DGAC] AD 1995–086–180(B)R2 

[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 DGAC 

France AD 1995–086–180(B)R2, 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 it in Docket No. FAA– 

2015–1426. 


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Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A300–57–6044, Revision 04, including 

Appendix 01, 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. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. This service 

information is reasonably available 

because the interested parties have 

access to it through their normal course 

of business or by the means identified 

in the ADDRESSES section of this NPRM. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

We estimate that this proposed AD 

affects 47 airplanes of U.S. registry. 

The actions that are required by AD 

97–20–07, Amendment 39–10145 (62 

FR 50251, September 25, 1997), and 

retained in this proposed 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 would take 

about 5 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this proposed 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 proposed 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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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: 

Airbus: Docket No. FAA–2015–1426; 

Directorate Identifier 2013–NM–200–AD. 

(a) Comments Due Date 

We must receive comments by July 20, 

2015. 

(b) Affected ADs 

This AD replaces AD 97–20–07, 

Amendment 39–10145 (62 FR 50251, 

September 25, 1997). 

(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 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 

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, Amendment 

39–10145 (62 FR 50251, September 25, 1997), 

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 02, dated 

September 6, 1995, including Appendix 1; or 

Airbus Service Bulletin A300–57–6044, 

Revision 04, including Appendix 01, dated 

August 19, 2011. As of the effective date of 

this AD, use only Airbus Service Bulletin 

A300–57–6044, Revision 04, including 

Appendix 01, dated August 19, 2011. 

Accomplishment of the inspection required 

by paragraph (i) of this AD terminates the 

inspection requirements of this paragraph. 


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(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 

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 paragraph (g), (g)(1), or (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 02, dated 

September 6, 1995, including Appendix 01; 

or Airbus Service Bulletin A300–57–6044, 

Revision 04, including Appendix 01, dated 

August 19, 2011. As of the effective date of 

this AD, use only Airbus Service Bulletin 

A300–57–6044, Revision 04, including 

Appendix 01, 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. 

(3) If any cracking is detected or confirmed 

during any HFEC inspection required by 

paragraph (g), (g)(1), or (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 02, dated 

September 6, 1995, including Appendix 01; 

or Airbus Service Bulletin A300–57–6044, 

Revision 04, including Appendix 01, dated 

August 19, 2011. As of the effective date of 

this AD, use only Airbus Service Bulletin 

A300–57–6044, Revision 04, including 

Appendix 01, 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 02, dated September 6, 1995, 

including Appendix 01; or Airbus Service 

Bulletin A300–57–6044, Revision 04, 

including Appendix 01, dated August 19, 

2011. As of the effective date of this AD, use 

only Airbus Service Bulletin A300–57–6044, 

Revision 04, including Appendix 01, 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 02, dated September 6, 1995, 

including Appendix 01; or Airbus Service 

Bulletin A300–57–6044, Revision 04, 

including Appendix 01, dated August 19, 

2011. As of the effective date of this AD, use 

only Airbus Service Bulletin A300–57–6044, 

Revision 04, including Appendix 01, dated 

August 19, 2011. Thereafter, conduct a low 

frequency eddy current 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 02, 

dated September 6, 1995, including 

Appendix 01 references Airbus Service 

Bulletin A300–57–6041, Revision 04, 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, Amendment 

39–10145 (62 FR 50251, September 25, 1997), 

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 low 

frequency eddy current (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 02, dated 

September 6, 1995, including Appendix 01; 

or Airbus Service Bulletin A300–57–6044, 

Revision 04, including Appendix 01, dated 

August 19, 2011. As of the effective date of 

this AD, use only Airbus Service Bulletin 

A300–57–6044, Revision 04, including 

Appendix 01, 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, FAA, 

Transport Airplane Directorate. 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, 

including Appendix 01, 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 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 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, including Appendix 

01, 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. 


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(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 visual inspection 

required by paragraph (i) or (j) of this AD: 

Before further flight, confirm this finding and 

the length of this cracking by conducting an 

HFEC inspection, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–6044, Revision 04, 

including Appendix 01, 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), (k) or (l) 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, 

including Appendix 01, dated August 19, 

2011, except as specified in paragraph (o) of 

this AD. Do repetitive detailed visual 

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, including Appendix 

01, 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, including Appendix 

01, 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, 

including Appendix 01, 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 

holes 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, 

including Appendix 01, dated August 19, 

2011. 

(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, 

which is not incorporated by reference in this 

AD. 

(o) Exception to Service Information 

Specification 

Although Airbus Service Bulletin A300– 

57–6044, Revision 04, including Appendix 

01, 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) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAW, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

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

93 44 51; email account.airworth-eas@

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

You may view this 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. 

Issued in Renton, Washington, on May 19, 

2015. 

Dionne Palmero, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–13335 Filed 6–4–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1423; Directorate 

Identifier 2014–NM–173–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 757–200 Series 

Airplanes Modified by Supplemental 

Type Certificate (STC) ST01529SE or 

STC ST02278SE 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 757–200 

series airplanes modified by particular 

STCs. This proposed AD was prompted 

by reports of a main cargo door being 

blown past its full open position while 

on the ground during gusty wind 

conditions, which resulted in 

uncontrolled fall down to its closed 

position. This proposed AD would 

require installing a new placard and 

bracket, replacement of an existing 

placard, and replacement of the main 

cargo door control panel. We are 

proposing this AD to prevent damage to 

the main cargo door, which could result 

in rapid decompression, leading to inflight breakup. 

DATES: We must receive comments on 

this proposed AD by July 20, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Precision 


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