Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Proposed Rules 1573 

Aviation Safety Agency (EASA) or Airbus’s 

EASA Design Organization Approval (DOA). 

After the effective date of this AD, replace all 

the applicable MLG bogie beams with a new 

or serviceable part using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

EASA; or Airbus’s EASA DOA. 

Accomplishing the actions specified in 

paragraph (k) of this AD terminates the 

requirements of this paragraph. 

(1) At the applicable time specified in 

paragraphs (i)(1)(i), (i)(1)(ii), and (i)(1)(iii) of 

this AD. 

(i) For Model A330–201, –202, –203, –223, 

–243 series airplanes, weight variant 

(WV)02x, WV05x (except WV058), and 

WV06x series: Before the accumulation of a 

life limit of 50,000 landings or 72,300 total 

flight hours, whichever occurs first from the 

first installation of a MLG bogie beam on the 

airplane. 

(ii) For Model A330–201, –202, –203, –223, 

–243 WV058 series airplanes: Before the 

accumulation of a life limit of 50,000 

landings or 57,900 total flight hours, 

whichever occurs first from the first 

installation of a MLG bogie beam on the 

airplane. 

(iii) For Model A330–301, –302, –303, 

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

airplanes, WV00x, WV01x, WV02x, and 

WV05x series: Before the accumulation of a 

life limit of 46,000 landings or 75,000 total 

flight hours, whichever occurs first from the 

first installation of a MLG bogie beam on the 

airplane. 

(2) Within 6 months after January 30, 2013 

(the effective date of AD 2012–25–12, 

Amendment 39–17293 (77 FR 75825, 

December 26, 2012). 

(j) Retained Parts Installation Limitation, 

With New Terminating Action 

This paragraph restates the requirements of 

paragraph (h) of AD 2012–25–12, 

Amendment 39–17293 (77 FR 75825, 

December 26, 2012), with new terminating 

action. For airplanes identified in paragraphs 

(c)(1) and (c)(3) of this AD, As of January 30, 

2013 (the effective date of AD 2012–25–12), 

a MLG bogie beam having any part number 

identified in paragraph (i) of this AD, may be 

installed on an airplane, provided its life has 

not exceeded the life limit specified in 

paragraphs (i)(1)(i), (i)(1)(ii), and (i)(1)(iii) of 

this AD, and is replaced with a new or 

serviceable part before reaching the life limit 

specified in paragraphs (i)(1)(i), (i)(1)(ii), and 

(i)(1)(iii) of this AD. Accomplishing the 

actions specified in paragraph (k) of this AD 

terminates the requirements of this 

paragraph. 

(k) New Maintenance or Inspection Program 

Revision 

(1) Within 3 months after the effective date 

of this AD: Revise the maintenance or 

inspection program, as applicable, by 

incorporating the information in Airbus A330 

ALS Part 1, ‘‘’Safe Life Airworthiness 

Limitation Items,’’ Revision 07, dated 

September 23, 2013; and variations to it 

listed in paragraphs (k)(1)(i) through (k)(1)(x), 

as applicable. 

(i) Airbus A330 Variation to Revision 07 of 

ALS Part 1, ‘‘Safe Life Airworthiness 

Limitations Items (SL ALI),’’ dated 

September 24, 2013 (variations reference 

0GVLG130005C0S, dated October 29, 2013). 

(ii) Airbus A330, ‘‘Safe Life Airworthiness 

Limitations Items (SL ALI),’’ Variation 7.6, 

dated February 24, 2015. 

(iii) Airbus A330, ‘‘Safe Life Airworthiness 

Limitations Items (SL ALI),’’ Variation 7.10, 

dated April 1, 2015. 

(iv) Airbus A330, ‘‘Safe Life Airworthiness 

Limitations Items (SL ALI),’’ Variation 7.18, 

dated April 1, 2015. 

(v) Airbus A330, ‘‘Safe Life Airworthiness 

Limitations Items (SL ALI),’’ Variation 7.19, 

dated June 8, 2015. 

(vi) Airbus A330, ‘‘Safe Life Airworthiness 

Limitations Items (SL ALI),’’ Variation 7.20, 

dated August 28, 2015. 

(vii) Airbus A330, ‘‘Safe Life Airworthiness 

Limitations Items (SL ALI),’’ Variation 7.21, 

dated September 14, 2015. 

(viii) Airbus A330, ‘‘Safe Life 

Airworthiness Limitations Items (SL ALI),’’ 

Variation 7.22, dated June 8, 2015. 

(ix) Airbus A330, ‘‘Safe Life Airworthiness 

Limitations Items (SL ALI),’’ Variation 7.23, 

dated August 31, 2015. 

(x) Airbus A330, ‘‘Safe Life Airworthiness 

Limitations Items (SL ALI),’’ Variation 7.24, 

dated September 21, 2015. 

(2) The initial compliance times for the 

actions specified Airbus A330 ALS Part 1, 

’’Safe Life Airworthiness Limitation Items,’’ 

Revision 07, dated September 23, 2013; and 

A330 Airbus Variations listed in paragraphs 

(k)(1)(i) through (k)(1)(x) as applicable, are at 

the times specified in Airbus A330 ALS Part 

1, ’’Safe Life Airworthiness Limitation 

Items,’’ Revision 07, dated September 23, 

2013; and Airbus A330 Variations listed in 

paragraphs (k)(1)(i) through (k)(1)(x) as 

applicable, or within 90 days after the 

effective date of this AD, whichever occurs 

later. Accomplishing the actions specified in 

this paragraph terminates the requirements 

specified in paragraphs (g) through (j) of this 

AD. 

(l) New No Alternative Actions or Intervals 

After the maintenance or inspection 

program, as applicable, has been revised, as 

required by paragraph (k) of this AD, no 

alternative actions (e.g., inspections) or 

intervals may be used unless the actions or 

intervals are approved as an alternative 

method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (m) of this AD. 

(m) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1138; fax (425) 227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Contacting the Manufacturer: 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 

the EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0009, dated 

January 8, 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– 

2015–8428. 

(2) For service information identified in 

this AD, contact Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

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

airworthiness.A330–A340@airbus.com; 

Internet http://www.airbus.com. 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 

December 23, 2015. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–33173 Filed 1–12–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8427; Directorate 

Identifier 2014–NM–212–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) 2007–10– 

10 R1, for all Airbus Model A300 B4– 

600, B4–600R, and F4–600R series 


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airplanes, and Model A300 C4–605R 

Variant F airplanes (collectively called 

Model A300–600 series airplanes). AD 

2007–10–10 R1 currently requires 

revising the airworthiness limitations 

section (ALS) of the instructions for 

continued airworthiness (ICA) to 

incorporate new limitations for fuel tank 

systems. Since we issued AD 2007–10– 

10 R1, the manufacturer has issued 

more restrictive maintenance 

requirements and/or airworthiness 

limitations. This proposed AD would 

require revising the maintenance 

program or inspection program to 

incorporate revised fuel maintenance 

and inspection tasks. We are proposing 

this AD to prevent the potential of 

ignition sources inside fuel tanks, 

which, in combination with flammable 

fuel vapors caused by latent failures, 

alterations, repairs, or maintenance 

actions, could result in fuel tank 

explosions and consequent loss of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by February 29, 2016. 

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– 

8427; 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–2015–8427; Directorate Identifier 

2014–NM–212–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 December 2, 2009, we issued AD 

2007–10–10 R1, Amendment 39–16134 

(74 FR 65398, December 10, 2009). AD 

2007–10–10 R1 requires actions 

intended to address 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). 

Since we issued AD 2007–10–10 R1, 

Amendment 39–16134 (74 FR 65398, 

December 10, 2009), we have 

determined more restrictive 

maintenance requirements and 

airworthiness limitations are necessary. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2014–0194, 

dated October 15, 2014 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Airbus Model A300 B4–600, 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: 

Prompted by an accident * * *, the 

Federal Aviation Administration (FAA) 

published Special Federal Aviation 

Regulation (SFAR) 88, [http://rgl.faa.gov/

Regulatory_and_Guidance_Library/

rgFAR.nsf/0/EEFB3F94451DC06286256C9

3004F5E07?OpenDocument&Highlight=sfar 

88], and the Joint Aviation Authorities (JAA) 

published Interim Policy INT/POL/25/12. In 

response to these regulations, Airbus 

conducted a design review to develop Fuel 

Airworthiness Limitations (FAL) for Airbus 

on A300–600 and A300–600ST aeroplanes. 

The FAL were specified in Airbus A300– 

600 FAL document ref. 95A.1929/05 at issue 

02 and in the A300–600 [Airworthiness 

Limitation Section] ALS variation to FAL 

document issue 02 ref. 0CVLG110007/C0S 

issue 01, for A300–600 and A300–600ST 

aeroplanes. 

EASA issued [EASA] AD 2006–0201 to 

require compliance with the FAL documents 

(comprising maintenance/inspection tasks 

and Critical Design Configuration Control 

Limitations (CDCCL)). 

EASA AD 2006–0201 was superseded by 

EASA AD 2007–0095 (later revised) [which 

corresponds to FAA AD 2007–10–10 R1, 

Amendment 39–16134 (74 FR 65398, 

December 10, 2009)], which retained the 

original requirements and corrected and 

updated the compliance paragraphs 

concerning task ref. 28–18–00–03–1 and 

CDCCL’s. 

Since EASA AD 2007–0095R1 was 

published, Airbus issued A300–600 ALS Part 

5, prompted by EASA policy statement 

(EASA D2005/CPRO) which requests design 

approval holders to integrate Fuel Tank 

Safety items into an ALS document. The 

A300–600 ALS Part 5 is approved by EASA. 

Failure to comply with the items as 

identified in Airbus A300–600 ALS Part 5 

could result in a fuel tank explosion and 

consequent loss of the aeroplane. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2007–0095R1, which is superseded, and 

requires implementation of the new and 

more restrictive maintenance instructions 

and/or airworthiness limitations as specified 

in Airbus A300–600 ALS Part 5. 

The unsafe condition is the potential 

of ignition sources inside fuel tanks, 

which, in combination with flammable 

fuel vapors caused by latent failures, 

alterations, repairs, or maintenance 

actions, could result in fuel tank 

explosions and consequent loss of the 

airplane. 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– 

8427. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued A300–600 

Airworthiness Limitations Section), Part 


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5—Fuel Airworthiness Limitations, 

Revision 00, dated May 27, 2014. The 

airworthiness limitations introduce 

mandatory instructions and more 

restrictive maintenance requirements. 

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. 

This proposed AD would require 

revisions to certain operator 

maintenance documents to include new 

actions (e.g., inspections and/or critical 

design configuration Control 

Limitations (CDCCLs). Compliance with 

these actions is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired 

in the areas addressed by these 

inspections, the operator may not be 

able to accomplish the inspections 

described in the revisions. In this 

situation, to comply with 14 CFR 

91.403(c), the operator must request 

approval for an alternative method of 

compliance (AMOC) according to 

paragraph (k) of this AD. The request 

should include a description of changes 

to the required actions that will ensure 

the continued operational safety of the 

airplane. 

Notwithstanding any other 

maintenance or operational 

requirements, components that have 

been identified as airworthy or installed 

on the affected airplanes before 

accomplishment of the revision of the 

airplane maintenance or inspection 

program specified in this AD, do not 

need to be reworked in accordance with 

the CDCCLs. However, once the airplane 

maintenance or inspection program has 

been revised as required by this AD, 

future maintenance actions on these 

components must be done in 

accordance with the CDCCLs. 

Differences Between This Proposed AD 

and the MCAI or Service Information 

The MCAI specifies that if there are 

findings from the ALS inspection tasks, 

corrective actions must be accomplished 

in accordance with Airbus maintenance 

documentation. However, this AD does 

not include that requirement. Operators 

of U.S.-registered airplanes are required 

by general airworthiness and 

operational regulations to perform 

maintenance using methods that are 

acceptable to the FAA. We consider 

those methods to be adequate to address 

any corrective actions necessitated by 

the findings of ALS inspections required 

by this AD. 

This proposed AD would require 

operators to revise the maintenance or 

inspection program within 3 months 

after the effective date of this AD to 

incorporate revised fuel maintenance 

and inspection tasks. The MCAI 

specifies compliance with the tasks as of 

the effective date of the MCAI. In 

developing the compliance time for this 

action, we considered the degree of 

urgency associated with addressing the 

unsafe condition. We find 3 months an 

appropriate compliance time to 

complete these actions. This difference 

has been coordinated with the EASA. 

Costs of Compliance 

We estimate that this proposed AD 

affects 122 airplanes of U.S. registry. 

The actions required by AD 2007–10– 

10 R1, Amendment 39–16134 (74 FR 

65398, December 10, 2009), and 

retained in this proposed AD take about 

2 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 are required by AD 

2007–10–10 R1 is $170 per product. 

We also estimate that it would take 

about 1 work-hour per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost $0 per product. Based 

on these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $10,370, or $85 per product. 

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) 

2007–10–10 R1, Amendment 39–16134 

(74 FR 65398, December 10, 2009), and 

adding the following new AD: 

Airbus: Docket No. FAA–2015–8427; 

Directorate Identifier 2014–NM–212–AD. 

(a) Comments Due Date 

We must receive comments by February 

29, 2016. 


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(b) Affected ADs 

This AD replaces AD 2007–10–10 R1, 

Amendment 39–16134 (74 FR 65398, 

December 10, 2009). 

(c) Applicability 

This AD applies to 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), certificated in any 

category, all manufacturer serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05, Time Limits/Maintenance 

Checks. 

(e) Reason 

This AD was prompted by Airbus issuing 

more restrictive instructions and/or fuel 

airworthiness limitations. We are issuing this 

AD to prevent the potential of ignition 

sources inside fuel tanks, which, in 

combination with flammable fuel vapors 

caused by latent failures, alterations, repairs, 

or maintenance actions, could result in fuel 

tank explosions and consequent loss of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Revision of the Airworthiness 

Limitations Section To Incorporate Fuel 

Maintenance and Inspection Tasks, With No 

Changes 

This paragraph restates the requirements of 

paragraph (f) of AD 2007–10–10 R1, 

Amendment 39–16134 (74 FR 65398, 

December 10, 2007). Within 3 months after 

June 27, 2007 (the effective date of AD 2007– 

10–10, Amendment 39–15051 (72 FR 28827, 

May 23, 2007)), revise the ALS of the 

Instructions for Continued Airworthiness to 

incorporate Airbus A300–600 ALS Part 5— 

Fuel Airworthiness Limitations, dated May 

31, 2006, as defined in Airbus A300–600 

Fuel Airworthiness Limitations, Document 

95A.1929/05, Issue 1, dated December 19, 

2005 (approved by EASA on March 13, 

2006), Section 1, ‘‘Maintenance/Inspection 

Tasks’’ (hereafter referred to as Section 1 of 

Issue 1 of Document 95A.1929/05); or Airbus 

A300–600 Fuel Airworthiness Limitations, 

Document 95A.1929/05, Issue 2, dated May 

16, 2007, Section 1, ‘‘Maintenance/Inspection 

Tasks’’ (hereafter referred to as ‘‘Section 1 of 

Issue 2 Document 95A.1929/05’’). For all 

tasks identified in Section 1 of Issue 1 or 

Issue 2 of Document 95A.1929/05, the initial 

compliance times start from the later of the 

times specified in paragraphs (f)(1) and (f)(2) 

of this AD, and the repetitive inspections 

must be accomplished thereafter at the 

intervals specified in Section 1 of Issue 1 or 

Issue 2 of Document 95A.1929/05, except as 

provided by paragraph (g) of this AD. 

(1) June 27, 2007 (the effective date of AD 

2007–10–10, Amendment 39–15051 (72 FR 

28827, May 23, 2007). 

(2) The date of issuance of the original 

French standard airworthiness certificate or 

the date of issuance of the original French 

export certificate of airworthiness. 

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

Operator Information Telex (OIT) SE 

999.0076/06, dated June 20, 2006, identifies 

the applicable sections of the Airbus A300– 

600 airplane maintenance manual necessary 

for accomplishing the tasks specified in 

Section 1 of Document 95A.1929/05. 

(h) Retained Revision of Initial Compliance 

Time for Task 28–18–00–03–1 

This paragraph restates the requirements of 

paragraph (g) of AD 2007–10–10 R1, 

Amendment 39–16134 (74 FR 65398, 

December 10, 2007) with no changes. For 

Task 28–18–00–03–1, ‘‘Operational check of 

lo-level/underfull/calibration sensors,’’ 

identified in Section 1 of Document 

95A.1929/05: The initial compliance time is 

the later of the times specified in paragraphs 

(h)(1) and (h)(2) of this AD. Thereafter, Task 

28–18–00–03–1 must be accomplished at the 

repetitive interval specified in Section 1 of 

Document 95A.1929/05. 

(1) Prior to the accumulation of 40,000 

total flight hours. 

(2) Within 72 months or 20,000 flight hours 

after June 27, 2007 (the effective date of AD 

2007–10–10, Amendment 39–15051 (72 FR 

28827, May 23, 2007), whichever occurs first. 

(i) Retained Revision of the ALS to 

Incorporate CDCCLs 

This paragraph restates the requirements of 

paragraph (h) of AD 2007–10–10 R1, 

Amendment 39–16134 (74 FR 65398, 

December 10, 2007) with no changes. Within 

12 months after the effective date of this AD, 

revise the ALS of the Instructions for 

Continued Airworthiness to incorporate 

Airbus A300–600 ALS Part 5—Fuel 

Airworthiness Limitations, dated May 31, 

2006, as defined in Airbus A300–600 Fuel 

Airworthiness Limitations, Document 

95A.1929/05, Issue 1, dated December 19, 

2005 (approved by the EASA on March 13, 

2006), Section 2, ‘‘Critical Design 

Configuration Control Limitations’’; or 

Airbus A300–600 Fuel Airworthiness 

Limitations, Document 95A.1929/05, Issue 2, 

dated May 16, 2007, Section 2, ‘‘Critical 

Design Configuration Control Limitations.’’ 

(j) New Requirement of This AD: Revise the 

Maintenance or Inspection Program 

Within 3 months after the effective date of 

this AD, revise the maintenance or inspection 

program, as applicable, by incorporating the 

airworthiness limitations as specified in 

Airbus A300–600 Airworthiness Limitations 

Section Part 5—Fuel Airworthiness 

Limitations, Revision 00, dated May 27, 

2014. The initial compliance times for the 

actions specified Airbus A300–600 

Airworthiness Limitations Section Part 5— 

Fuel Airworthiness Limitations, Revision 00, 

dated May 27, 2014, are at the later of the 

times specified in Airbus A300–600 

Airworthiness Limitations Section Part 5— 

Fuel Airworthiness Limitations, Revision 00, 

dated May 27, 2014, or within 3 months after 

the effective date of this AD, whichever 

occurs later. Accomplishing the revision 

required by this paragraph terminates the 

actions required by paragraphs (g) through (i) 

of this AD. 

(k) New Requirement of This AD: No 

Alternative Actions, Intervals, and/or 

Critical Design Configuration Control 

Limitations (CDCCLs) 

After the maintenance or inspection 

program has been revised as required by 

paragraph (j) of this AD, no alternative 

actions (e.g., inspections), intervals, and/or 

CDCCLs may be used unless the actions, 

intervals, and/or CDCCLs are approved as an 

alternative method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (l)(1) of this AD. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, 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 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2014–0194, dated October 15, 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–2015–8427. 

(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. 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Proposed Rules 1577 

Issued in Renton, Washington, on 

December 23, 2015. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–33175 Filed 1–12–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8429; Directorate 

Identifier 2015–NM–122–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

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 747–100, 

747–100B, 747–100B SUD, 747–200B, 

747–200C, 747–200F, 747–300, 747– 

400, 747–400D, 747–400F, 747SR, and 

747SP series airplanes. This proposed 

AD was prompted by reports of fatigue 

cracks in the station 320 crown frame 

and in window post number 3. This 

proposed AD would require repetitive 

inspections for cracks and missing 

fasteners of the station 320 crown frame, 

cracks in the web and flange surfaces of 

the forward segment of window post 

number 3, and missing fasteners and 

cracks of the window upper sill; postmodification inspections for cracks of 

the window upper sill; one-time 

fastener rework; and related 

investigative and corrective actions if 

necessary. We are proposing this AD to 

detect and correct fatigue cracking and 

missing fasteners of the station 320 

crown frame, cracking of the window 

post number 3, and cracking of the 

window upper sill, which could result 

in an in-flight decompression and a loss 

of structural integrity of the fuselage. 

DATES: We must receive comments on 

this proposed AD by February 29, 2016. 

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 Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

8429. 

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– 

8429; 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 Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Bill 

Ashforth, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 

Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6432; fax: 425– 

917–6590; email: Bill.Ashforth@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2015–8429; Directorate Identifier 2015– 

NM–122–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 because of 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 

We have received reports of fatigue 

cracks in the station 320 crown frame on 

Model 747–400 series airplanes. Other 

Model 747 airplanes, except Model 747– 

8F and 747–8 airplanes, are of a similar 

station 320 crown frame configuration. 

Inner chord cracks of 0.03- to 0.22-inch 

in length have been found on 15 

airplanes with total flight cycles ranging 

from 11,498 to 31,315. Also, a 1.8-inch 

crack was found in the outboard web of 

the frame on one airplane with 14,749 

total flight cycles. 

Cracks have also been found in 

window post number 3, which connects 

to the lower end of the inner chord of 

the station 320 crown frame. Cracks of 

0.03- to 0.11-inch in length have been 

found in window post number 3 on five 

airplanes with total flight cycles ranging 

from 12,329 to 15,772. 

Additionally, fatigue cracks that had 

extended to fully sever the inner chord 

and outboard web of the frame were 

found on the Model 747–400 fatigue test 

airplane at 38,333 total pressure cycles, 

and significant cracks were found in 

both the frame inner chord and 

outboard web at 30,500 total pressure 

cycles on the Model 747–100SR fatigue 

test airplane. 

Fatigue cracking and missing 

fasteners of the station 320 crown frame, 

cracking of the window post number 3, 

and cracking of the window upper sill 

could result in in-flight decompression 

and a loss of structural integrity of the 

fuselage. 

Related Service Information Under 

1 CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 747–53A2862, Revision 1, 

dated July 24, 2015. The service 

information describes procedures for 

inspections and corrective actions for 

cracks and missing fasteners in the 

inner chord and outboard webs of the 

station 320 crown frame, in the left and 

right side window post number 3, and 

in the upper sill structure. 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 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS