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

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


### 1574 Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Proposed Rules

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


### 1575 Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Proposed Rules

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.


### 1576 Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Proposed Rules

(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.


### 1577 Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Proposed Rules

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 andcracks 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